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  • AIRCRAFT PROPULSION AND POWER  (1,211)
  • Fisheries
  • 1975-1979  (1,213)
  • 1
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    Investigation of air stream from combustor-liner air entry holes, 3 (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Jets flowing from air entry holes of the combustor liner of a gas turbine were investigated. Cold air was supplied through the air entry holes into the primary hot gas flows. The mass flow of the primary hot gas and issuing jets was measured, and the behavior of the air jets was studied by the measurement of the temperature distribution of the gas mixture. The air jets flowing from three circular air entry holes, single streamwise long holes, and two opposing circular holes, parallel to the primary flow were studied along with the effects of jet and gas stream velocities, and of gas temperature. The discharge coefficient, the maximum penetration of the jets, the jet flow path, the mixing of the jets, and temperature distribution across the jets were investigated. Empirical expressions which describe the characteristics of the jets under the conditions of the experiments were formulated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75430 , NAL-TR-369
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    NASA TECHNICAL REPORTS
  • 2
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    Propulsion-airframe interactions predictability (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An illustration of the possible magnitude of the transonic performance prediction problem is shown. These results derived from a careful and systematic set of tests run on a jet effects model, an aerodynamic and force model, and a pressure model, evaluated test techniques and wind tunnel effects. The results were then carefully compared with flight test data where significant discrepancies in zero-lift drag were observed. A vigorous review of the test techniques identified a number of potential error sources. Some of these were thought to be aircraft roughness and protuberances, tunnel anomalies, sting/model support corrections, and hot gas effects. In addition, there were questions on model metric splitline location and magnitude of corrections for scale and Reynolds number. Flight test inlet/engine characteristics were thought to differ, also, from those of the calibration settings in the ground facilities.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Performance Prediction Methods; 20 p
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  • 3
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    Low cycle fatigue in turbines (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Behavior of certain components at low-cycle fatigue is a parameter related to the conditions of use of turbines, to the technology of engine production and to the precision of its regulation. The laboratory takes this into account using data from sophisticated tests and rigorous analyses. The production plan includes careful examination of possible causes of premature rupture. This parameter has motivated the metallurgy industry to develop new materials and new technology.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75264
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  • 4
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    Aircraft fuel conservation technology. Task force report, September 10, 1975 (1975)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An advanced technology program is described for reduced fuel consumption in air transport. Cost benefits and estimates are given for improved engine design and components, turboprop propulsion systems, active control systems, laminar flow control, and composite primary structures.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-74295
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  • 5
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    Fundamental Aspects of the Aerodynamics of Turbojet Engine Combustors (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Aerodynamic considerations in the design of high performance combustors for turbojet engines are discussed. Aerodynamic problems concerning the preparation of the fuel-air mixture, the recirculation zone where primary combustion occurs, the secondary combustion zone, and the dilution zone were examined. An aerodynamic analysis of the entire primary chamber ensemble was carried out to determine the pressure drop between entry and exit. The aerodynamics of afterburn chambers are discussed. A model which can be used to investigate the evolution of temperature, pressure, and rate and efficiency of combustion the length of the chamber was developed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75287 , ONERA-TP-1976
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  • 6
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    Approximate dynamic model of a turbojet engine (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An approximate dynamic nonlinear model of a turbojet engine is elaborated on as a tool in studying the aircraft control loop, with the turbojet engine treated as an actuating component. Approximate relationships linking the basic engine parameters and shaft speed are derived to simplify the problem, and to aid in constructing an approximate nonlinear dynamic model of turbojet engine performance useful for predicting aircraft motion.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75263
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  • 7
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    Summary of NASA aerodynamic and heat transfer studies in turbine vanes and blades (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: Aerodynamic effects of trailing edge geometry, hole size, angle, spacing, and shape have been studied in two- and three-dimensional cascades and in a warm turbine test series. Heat transfer studies have been carried out in various two- and three-dimensional test facilities in order to provide corresponding heat transfer data. Results are shown in terms of cooling effectiveness and aerodynamic efficiency for various coolant fractions, coolant-primary temperature ratios, and cooling configurations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 760917
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  • 8
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    Test engines promise less noise from small aircraft (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-NEWS-RELEASE-79-24 , P79-10025
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  • 9
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    Experimental turbofan engine for small aircraft delivered (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-NEWS-RELEASE-79-137 , P79-10137
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  • 10
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    New materials for high temperature turbines; ONERA's DS composites confronted with blade problems (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: ONERA's refractory DS composites were cited as materials required for use in advanced aircraft turbines, operating at high temperatures. These materials were found to be reliable in the construction of turbine blades. Requirements for a blade material in aircraft turbines operating at higher temperatures were compared with the actual performance as found in COTAC DS composite testing. The structure and properties of the more fully developed 74 and 741 types were specified. High temperature structural stability, impact of thermal and mechanical fatigue, oxidation resistance and coating capability were thoroughly evaluated. The problem of cooling passages in DS eutectic blades is also outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75216 , High Temp. Probl. in Gas Turbine Eng.; 19-23 Sept. 1977; Ankara
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  • 11
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    High temperature corrosion-resistant protective coatings in stationary gas turbines (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Methods currently used to deposit protective coatings in gas turbines are reviewed, and the structure of the respective coatings is examined. The corrosion behavior of such coatings is discussed on the basis of experimental data. General trends in the preparation of protective coatings are noted.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75181 , Tagung in Verbundwerkstoffe; Mar 28, 1974 - Mar 29, 1974; Constance; Germany
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  • 12
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    NASA engine system technology programs - An overview (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The various propulsion systems technology programs are examined. The Stratospheric Cruise Emission Reduction program has the objective to explore and demonstrate advanced technology fuel preparation and combustion systems which produce very low emission levels, particularly with respect to the oxides of nitrogen, during high altitude cruising flight. Other programs considered include the Quiet, Clean, General Aviation Turbofan program, the Variable Cycle Engine Technology program, the Helicopter Transmission Technology program, the Broad Specification Fuels Technology program, the Engine Component Improvement program, the Advanced Turboprop Technology program, the Supersonic Cruise Propulsion Technology program, the Materials for Advanced Turbine Engines program, and the Aeroelasticity of Turbine Engines program.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-928 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
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  • 13
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    Investigation of the jet-wake flow of a highly loaded centrifugal compressor impeller (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Investigations, aimed at developing a better understanding of the complex flow field in high performance centrifugal compressors were performed. Newly developed measuring techniques for unsteady static and total pressures as well as flow directions, and a digital data analysis system for fluctuating signals were thoroughly tested. The loss-affected mixing process of the distorted impeller discharge flow was investigated in detail, in the absolute and relative system, at impeller tip speeds up to 380 m/s. A theoretical analysis proved good coincidence of the test results with the DEAN-SENOO theory, which was extended to compressible flows.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75232
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  • 14
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    Structural analysis of hollow blades: Torsional stress analysis of hollow fan blades for aircraft jet engines (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: A torsional stress analysis of hollow fans blades by the finite element method is presented. The fans are considered to be double circular arc blades, hollowed 30 percent, and twisted by a component of the centrifugal force by the rated revolution. The effects of blade hollowing on strength and rigidity are discussed. The effects of reinforcing webs, placed in the hollowed section in varying numbers and locations, on torsional rigidity and the convergence of stresses, are reported. A forecast of the 30 percent hollowing against torsional loadings is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75718 , NAL-TR-533
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  • 15
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    Aerodynamic investigation of an air-cooled axial-flow turbine. Part 2: Rotor blade tip-clearance effects on overall turbine performance and internal gas flow conditions: Experimental results and prediction methods (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Total turbine blade performance was investigated while changing the blade tip clearance in three ways. The internal flow at the moving blade outlet point was measured. Experimental results were compared with various theoretical methods. Increased blade clearance leads to decreased turbine efficiency.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75138
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  • 16
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    A review of NASA's propulsion programs for civil aviation (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: Five NASA engine-oriented propulsion programs of major importance to civil aviation are presented and discussed. Included are programs directed at exploring propulsion-system concepts for (1) energy-conservative subsonic aircraft (improved current turbofans, advanced turbofans, and advanced turboprops), (2) supersonic cruise aircraft (variable-cycle engines), (3) general aviation aircraft (improved reciprocating engines and small gas turbines), (4) powered-lift aircraft (advanced turbofans), and (5) advanced rotorcraft. These programs reflect the opportunities still existing for significant improvements in civil aviation through the application of advanced propulsion concepts
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-43 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
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  • 17
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    Eight-bladed propeller design could bring back turboprop airplanes (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: P77-10204 , NASA-NEWS-RELEASE-77-206
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  • 18
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    Protection of cooled blades of complex internal structure (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The problem of general protection of cooled blades of complex internal structure was solved by a method called SF technique which makes possible the protection of both external and internal surfaces, as well as those of the orifices of cooling air, whatever their diameter. The SF method is most often applied in the case of pack process, at controlled or high activity; it can be of use on previously uncoated parts, but also on pieces already coated by a thermochemical, chemical or PVD method. The respective thickness of external and internal coatings may be precisely predetermined, no parasitic particle being liable to remain inside the parts after application of the protecting treatment. Results obtained to date by application of this method are illustrated by the presentation and examination of a various selection of advanced turbo engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75217 , AGARD-CP-229 , Conf. on High Temp. Probl. in Gas Turbine Engines; Sep 19, 1977 - Sep 23, 1977; Ankara
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  • 19
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    Procedure for pressure contact on high-power semiconductor devices free of thermal fatigue (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: To eliminate thermal fatigue, a procedure for manufacturing semiconductor power devices with pure pressure contact without solid binding was developed. Pressure contact without the use of a solid binding to avoid a limitation of the maximum surface in the contact was examined. A silicon wafer covered with a relatively thick metal layer is imbedded with the aid of a soft silver foil between two identically sized hard contact discs (molybdenum or tungsten) which are rotationally symmetrical. The advantages of this concept are shown for large diameters. The pressure contact was tested successfully in many devices in a large variety of applications.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75733 , BMFT-FB-T-78-02
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  • 20
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    Overview of NASA general aviation program (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: The NASA efforts devoted to new technology for general aviation are summarized. Areas covered include: (1) improved safety through improved crashworthy structural design, spin resistance, and improved operations around uncontrolled airports; (2) reduced environmental impact for both reciprocating and turbine engines; and (3) research for improvement in the performance of both aerodynamic and system components.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center The Rotary Combust. Engine; p 1-11
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  • 21
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    Effect of Flame Stabilizer Design on Performance and Exhaust Pollutants of a Two-Row Swirl-Can Combustor Operated to Near-Stoichiometric Conditions (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Emissions and performance characteristics were determined for two full annulus modular combustors operated to near stoichiometric fuel air ratios. The tests were conducted to obtain stoichiometric data at inlet air temperatures from 756 to 894 K and to determine the effects of a flat plate circular flame stabilizer with upstream fuel injection and a contraswirl flame stabilizer with downstream fuel injection. Levels of unburned hydrocarbons were below 0.50 gram per kilogram of fuel for both combustors and thus there was no detectable difference in the two methods of fuel injection. The contraswirl flame stabilizer did not produce the level of mixing obtained with a flat plate circular flame stabilizer. It did produce higher levels of oxides of nitrogen, which peaked at a fuel air ratio of 0.037. For the flat plate circular flame stabilizer, oxides of nitrogen emission levels were still increasing with fuel air ratio to the maximum tested value of 0.045.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3495 , E-8317
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  • 22
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    Alternatives for Jet Engine Control (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Approaches are developed as alternatives to current design methods which rely heavily on linear quadratic and Riccati equation methods. The main alternatives are discussed in two broad categories, local multivariable frequency domain methods and global nonlinear optimal methods.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-146531
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  • 23
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    Reducing secondary losses by blowing cold air in a turbine (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Local blowing on the profile suction side of the turbine guide wheel blades can be effective in preventing the propagation of secondary flows that is, the transport of casing and hub boundary layers by pressure gradients. Some preliminary results on how the blowing should be accomplished in order to influence the secondary flows in the desired manner are given. The effectiveness of blowing is demonstrated. Blowing is also seen to be more effective than using boundary layer slots as far as diminishing losses in the rim zones is concerned.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75185 , PAPER-76-164 , DGLR Jahrestagung; Sep 14, 1976 - Sep 16, 1976; Munich
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  • 24
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    Predicted exhaust emissions from a methanol and jet fueled gas turbine combustor (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A computer model of a gas turbine combustor has been used to predict the kinetic combustion and pollutant formation processes for methanol and simulated jet fuel. Use of the kinetic reaction mechanisms has also allowed a study of ignition delay and flammability limit of these two fuels. The NOX emissions for methanol were predicted to be from 69 to 92% lower than those for jet fuel at the same equivalence ratio which is in agreement with experimentally observed results. The high heat of vaporization of methanol lowers both the combustor inlet mixture temperatures and the final combustion temperatures. The lower combustion temperatures lead to low NOX emissions while the lower inlet mixture temperatures increase methanol's ignition delay. This increase in ignition delay dictates the lean flammability limit of methanol to be 0.8, while jet fuel is shown to combust at 0.4.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1266
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  • 25
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    Application of real-time engine simulations to the development of propulsion system controls (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The development of digital controls for turbojet and turbofan engines can be facilitated by the use of real-time computer simulations of the engines. The engine simulation provides a 'test-bed' for evaluating new control laws and for checking and 'debugging' control software and hardware prior to engine testing. This paper describes the development and use of real-time, hybrid computer simulations of the Pratt & Whitney TF30-P-3 and F100-PW-100 augmented turbofans in support of a number of controls research programs at the Lewis Research Center. The role of engine simulations in solving the propulsion systems integration problem is also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1176
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  • 26
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    Turbine engine altitude chamber and flight testing with liquid hydrogen (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: In the late fifties the Lewis Research Center evaluated experimentally the use of hydrogen using three different turbojet engines in altitude test chambers. One of these engines was later flown experimentally using liquid hydrogen fuel. This paper is a brief overview of the significant aspects of this exploratory research and gives a few implications of the results to modern turbine engines. A subsequent contract dealing with a positive displacement pump operating on liquid hydrogen is discussed and some aspects of liquid hydrogen propellant systems, reflected by rocket booster experience are treated briefly. Areas requiring further research and technology effort are delineated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: International Symposium on Hydrogen in Air Transportation; Sept. 11-14, 1979; Stuttgart
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  • 27
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    Identification and dual adaptive control of a turbojet engine (1979)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The objective of this paper is to utilize the design methods of modern control theory to realize a 'dual-adaptive' feedback control unit for a highly non-linear single spool airbreathing turbojet engine. Using a very detailed and accurate simulation of the non-linear engine as the data source, linear operating point models of unspecified dimension are identified. Feedback control laws are designed at each operating point for a prespecified set of sampling rates using sampled-data output regulator theory. The control system sampling rate is determined by an adaptive sampling algorithm in correspondence with turbojet engine performance. The result is a 'dual-adpative' control law that is functionally dependent upon the sampling rate selected and environmental operating conditions. Simulation transients demonstrate the utility of the dual-adaptive design to improve on-board computer utilization while maintaining acceptable levels of engine performance.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Symposium on Identification and System Parameter Estimation; Sept. 24-28, 1979; Darmstadt
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  • 28
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    Characterization of a swept-strut hydrogen fuel-injector for scramjet applications (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Results of an experimental investigation of a swept-strut hydrogen fuel-injector simulating the center strut of a three strut scramjet module at Mach 6 flight conditions are presented. Detailed wall pressure distributions from over 100 separate tests with overall fuel flow from 0.1 to 1.3 times stoichiometric and test gas stagnation temperature from 1100 to 2400 K were recorded. The distance for pressure rise from the point of injection was found to increase with increasing test stagnation temperature. This trend indicates that chemical kinetics in the immediate region of perpendicular injection are not likely to be the mechanism controlling the onset of pressure rise. A fluid dynamic mechanism is suggested involving separation of the boundary layer downstream of injection which is forced upstream from the trailing edge by pressure rise due to combustion occurring in the base region of the strut. The results obtained indicate that the swept-strut fuel-injector concept can be adapted to a wide range of flight conditions by varying the amount of perpendicular fuel injection.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Joint Army-Navy-NASA-Air Force, Interagency Propulsion Committee Combustion Meeting; Sept. 1978; Newport, RI
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    NASA TECHNICAL REPORTS
  • 29
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    Correlation of combustor acoustic power levels inferred from internal fluctuating pressure measurements (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Combustion chamber acoustic power levels inferred from internal fluctuating pressure measurements are correlated with operating conditions and chamber geometries over a wide range. The variables include considerations of chamber design (can, annular, and reverse-flow annular) and size, number of fuel nozzles, burner staging and fuel split, airflow and heat release rates, and chamber inlet pressure and temperature levels. The correlated data include those obtained with combustion component development rigs as well as engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 30
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    Effects of film injection on performance of a cooled turbine (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Some of the most dramatic increases in the performance of turbojet and turbofan aircraft engines have been obtained as a result of increased thermodynamic cycle temperatures made possible by the use of film cooling techniques. The realization of the potential performance gains, however, is only possible if the quantity of cooling air and the aerodynamic mixing losses resulting from the injection of coolant in the form of film on the flowpath surfaces are minimized. Such a minimization requires a more complete understanding of the relationship between cooling and aerodynamics. A review is conducted of tests which have been conducted to determine the effects of coolant injection on turbine performance. The results obtained in the tests are compared with an analytical technique developed for predicting coolant injection effects. Particular attention is given to the effects of turbine cooling on overall cycle thermodynamic efficiency, taking into account incremental changes in turbine thermodynamic efficiency for various incremental changes in coolant flow rate.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion and Energetics Panel Meeting; Sept. 19-23, 1977; Ankara; Turkey
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  • 31
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    A review of NASA's propulsion programs for aviation (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: A review of five NASA engine-oriented propulsion programs of major importance to civil aviation are presented and discussed. Included are programs directed at exploring propulsion system concepts for (1) energy conservation subsonic aircraft (improved current turbofans, advanced turbofans, and advanced turboprops); (2) supersonic cruise aircraft (variable cycle engines); (3) general aviation aircraft (improved reciprocating engines and small gas turbines); (4) powered lift aircraft (advanced turbofans); and (5) advanced rotorcraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-73831 , Aerospace Sci. Meeting; 16-18 Jan.; Huntsville, AL; United States
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    NASA TECHNICAL REPORTS
  • 32
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    Effect of fuel properties on performance of a single aircraft turbojet combustor (1975)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The performance of a single-can JT8D combustor was investigated with a number of fuels exhibiting wide variations in chemical composition and volatility. Performance parameters investigated were combustion efficiency, emissions of CO, unburned hydrocarbons and NOx, as well as liner temperatures and smoke. At the simulated idle condition no significant differences in performance were observed. At cruise, liner temperatures and smoke increased sharply with decreasing hydrogen content of the fuel. No significant differences were observed in the performance of an oil-shale derived JP-5 and a petroleum-based Jet A fuel except for emissions of NOx which were higher with the oil-shale JP-5. The difference is attributed to the higher concentration of fuel-bound nitrogen in the oil-shale JP-5.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Combustion Institute, Fall Meeting; October 20, 21, 1975; Palo Alto, CA
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    NASA TECHNICAL REPORTS
  • 33
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    An early glimpse at long-term subsonic commercial turbofan technology requirements (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: This paper reports on the exploratory investigation and initial findings of the study of future turbofan concepts to conserve fuel. To date, these studies have indicated a potential reduction in cruise thrust specific fuel consumption in 1990 turbofans of approximately 15% relative to present day new engines through advances in internal aerodynamics, structure-mechanics, and materials. Advanced materials also offer the potential for fuel savings through engine weight reduction. Further studies are required to balance fuel consumption reduction with sound airlines operational economics.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1207
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  • 34
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    Turbofan compressor dynamics during afterburner transients (1975)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The effects of afterburner light-off and shut-down transients on the compressor stability are investigated. The reported experimental results are based on detailed high-response pressure and temperature measurements on the TF30-P-3 turbofan engine. The tests were performed in an altitude test chamber simulating high-altitude engine operation. It is shown that during both types of transients, flow breaks down in the forward part of the fan-bypass duct. At a sufficiently low engine inlet pressure this resulted in a compressor stall. Complete flow breakdown within the compressor was preceded by a rotating stall. At some locations in the compressor, rotating stall cells initially extended only through part of the blade span. For the shut-down transient the time between first and last detected occurrence of rotating stall is related to the flow Reynolds number. An attempt was made to deduce the number and speed of propagation of rotating stall cells.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NATO, AGARD, Symposium on Unsteady Phenomena in Turbomachinery; Sept. 22-26, 1975; Monterey, CA
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  • 35
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    Gas turbine combustor stabilization by heat recirculation (1975)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The feasibility of heat recirculation for stabilization of lean mixtures and emission reduction has been studied in detail for a typical aircraft gas turbine combustor. Thermodynamic calculations have indicated temperature and heat recirculation rates for operation of the combustor over a range of combustion zone equivalence ratios and for varying modes of desired engine operation. Calculations indicate the feasibility of stabilizing the combustion zone at equivalence ratios as low as 0.2 with achievable heat recirculation rates. Detailed chemical kinetic calculations suggest that combustor heat release is maintained with reaction completion substantially before the NO forming reactions, even though CO is rapidly oxidized in this same region.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1304
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  • 36
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    Propulsion system structural integration and engine integrity; Proceedings of the Symposium, U.S. Naval Postgraduate School, Monterey, Calif., September 3-6, 1974 (1975)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Current problems involving the structural integrity of propulsion systems, and proposed approaches to solving them, are reviewed. Areas investigated include the stall hammershock at the engine inlet, distortion-induced vibration in fan and compressor blading, modeling engine static structures with conical-shell finite elements, design and development of low-cost, self-contained bearing lubrication systems for turbine engines, and roller bearing slip and skidding damage. Individual items are announced in this issue.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion system structural integration and engine integrity; Symposium; Sept. 3-6, 1974; Monterey, CA
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  • 37
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    Application of real-time engine simulations to the development of propulsion system controls (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: The development of digital controls for turbojet and turbofan engines is presented by the use of real-time computer simulations of the engines. The engine simulation provides a test-bed for evaluating new control laws and for checking and debugging control software and hardware prior to engine testing. The development and use of real-time, hybrid computer simulations of the Pratt and Whitney TF30-P-3 and F100-PW-100 augmented turbofans are described in support of a number of controls research programs at the Lewis Research Center. The role of engine simulations in solving the propulsion systems integration problem is also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71764 , E-8416
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  • 38
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    Experimental verification of film-cooling concepts on a turbine vane (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: Film cooling concepts applied to gas turbine vanes were investigated. The filming cooling air was ejected from a single row of holes on the convex surface and a double row of holes of the concave surface. Tests were conducted at a gas temperature of 1260 K, a gas pressure of 3 atmospheres, and a coolant temperature of 280 K. Mass velocity ratios were varied between 0 and 2.0. Data were taken without film cooling holes, with film cooling holes but without blowing, and with blowing. A small amount of blowing into a nonturbulent boundary layer caused an increase in vane temperatures. Film cooling when combined with convection cooling was verified to be more effective than either film or convection cooling alone.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71777 , E-8435
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  • 39
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    Flow visualization of discrete hole film cooling for gas turbine applications (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: Film injection from discrete holes in a three row staggered array with 5-diameter spacing is studied. The boundary layer thickness-to-hole diameter ratio and Reynolds number are typical of gas turbine film cooling applications. Two different injection locations are studied to evaluate the effect of boundary layer thickness on film penetration and mixing. Detailed streaklines showing the turbulent motion of the injected air are obtained by photographing neutrally buoyant helium filled soap bubbles which follow the flow field. The bubble streaklines passing downstream injection locations are clearly identifiable and can be traced back to their origin. Visualization of surface temperature patterns obtained from infrared photographs of a similar film cooled surface are also included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71766 , E-8418
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  • 40
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    Metal matrix composites for aircraft propulsion systems (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: Studies of advanced aircraft propulsion systems have indicated that performance gains and operating costs are possible through the application of metal matrix composites. Compressor fan blades and turbine blades have been identified as components with high payoff potential as a result of these studies. This paper will present the current status of development of five candidate materials for such applications. Boron fiber/aluminum, boron fiber/titanium, and silicon carbide fiber/titanium composites are considered for lightweight compressor fan blades. Directionally solidified eutectic superalloy and tungsten wire/superalloy composites are considered for application to turbine blades for use temperatures to 1100 C (2000 F).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71685 , E-8280 , Apr 14, 1975 - Apr 18, 1975; Boston, MA; United States
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  • 41
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    Interactive multi-mode blade impact analysis (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: The theoretical methodology used in developing an analysis for the response of turbine engine fan blades subjected to soft-body (bird) impacts is reported, and the computer program developed using this methodology as its basis is described. This computer program is an outgrowth of two programs that were previously developed for the purpose of studying problems of a similar nature (a 3-mode beam impact analysis and a multi-mode beam impact analysis). The present program utilizes an improved missile model that is interactively coupled with blade motion which is more consistent with actual observations. It takes into account local deformation at the impact area, blade camber effects, and the spreading of the impacted missile mass on the blade surface. In addition, it accommodates plate-type mode shapes. The analysis capability in this computer program represents a significant improvement in the development of the methodology for evaluating potential fan blade materials and designs with regard to foreign object impact resistance.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159462
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  • 42
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    Energy efficient engine. Flight propulsion system preliminary analysis and design (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The characteristics of an advanced Flight Propulsion System (FPS) suitable for introduction in the late 1980's to early 1990's, were defined. It was determined that NASA goals for efficiency, environmental considerations, and economics could be met or exceeded with the possible exception of NOx emission. In evaluating the FPS, all aspects were considered including component design, performance, weight, initial cost, maintenance cost, engine-system integration (including nacelle), and aircraft integration considerations. In terms of the NASA goals, the current FPS installed specific fuel consumption was reduced 14.2% from that of the CF6-50C reference engine. When integrated into an advanced, subsonic, study transport, the FPS produced a fuel-burn savings of 15 to 23% and a direct operating cost reduction of 5 to 12% depending on the mission and study-aircraft characteristics relative to the reference engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159859 , NAS 1.26:159859 , R80AEG396
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  • 43
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    Design of a turbojet engine controller via eigenvalue/eigenvector assignment - A new sensitivity formulation (1979)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This brief paper summarizes the approach the authors will take in designing a feedback controller for the F-100 turbofan engine. The technique to be utilized simultaneously realizes dominant closed-loop eigenvalues, approximates specified modal behavior, and achieves low eigensystem sensitivity with respect to certain plant parameter variations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Joint Automatic Control Conference; Jun 17, 1979 - Jun 21, 1979; Denver, CO
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  • 44
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    Optimum subsonic, high-angle-of-attack nacelles (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The optimum design of nacelles that operate over a wide range of aerodynamic conditions and their inlets is described. For low speed operation the optimum internal surface velocity distributions and skin friction distributions are described for three categories of inlets: those with BLC, and those with blow in door slots and retractable slats. At cruise speed the effect of factors that reduce the nacelle external surface area and the local skin friction is illustrated. These factors are cruise Mach number, inlet throat size, fan-face Mach number, and nacelle contour. The interrelation of these cruise speed factors with the design requirements for good low speed performance is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81491 , E-406 , Congr. of the Intern. Council of the Aeron. Sci.; Oct 13, 1980 - Oct 17, 1980; Munich; Germany*United States|Oct 13, 1980 - Oct 16, 1980; Los Angeles, CA; United States
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  • 45
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    Theory of deposition of condensible impurities on surfaces immersed in combustion gases (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The components resulting from the deposition of inorganic salts (e.g., Na2S04) and oxides present in the combustion products from gas turbine engines were investigated. Emphasis was placed on the effects of multicomponent vapor transport, thermophoretic transport of vapor and small particles to actively cooled surfaces, variable fluid properties within mass transfer boundary layers, and free stream turbulence.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159716 , SAR-6
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  • 46
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    Quiet powered-lift propulsion (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Latest results of programs exploring new propulsion technology for powered-lift aircraft systems are presented. Topics discussed include results from the 'quiet clean short-haul experimental engine' program and progress reports on the 'quiet short-haul research aircraft' and 'tilt-rotor research aircraft' programs. In addition to these NASA programs, the Air Force AMST YC 14 and YC 15 programs were reviewed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CP-2077 , E-9906 , Nov 14, 1978 - Nov 15, 1978; Cleveland, OH; United States
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  • 47
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    Quiet Clean Short-haul Experimental Engine (QCSEE) whirl test of cam/harmonic pitch change actuation system (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A variable pitch fan actuation system, which incorporates a remote nacelle mounted blade angle regulator, was tested. The regulator drives a rotating fan mounted mechanical actuator through a flexible shaft and differential gear train. The actuator incorporates a high ratio harmonic drive attached to a multitrack spherical cam which changes blade pitch through individual cam follower arms attached to each blade trunnion. Testing of the actuator on a whirl rig, is reported. Results of tests conducted to verify that the unit satisfied the design requirements and was structurally adequate for use in an engine test are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135140 , HSER-7002
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  • 48
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    Experimental studies of the formation/deposition of sodium sulfate in/from combustion gases (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An optical polarization (ellipsometric) technique was developed for measuring rapidly growing and evaporating transparent liquid condensate films (e.g., boric oxide) on solid surfaces exposed to combustion product gases. Results for the B2O3 deposition rate from BCl3-seeded propane/air flames are shown to agree well with the results of earlier interference measurements, and also with theoretical CVD predictions. Evaporation rates (from platinum ribbons into seeded propane air flames) are estimated using the polarization technique. It appears that, compared with the interference method, the polarization technique places less stringent requirements on surface quality, which may justify the added optical components needed for such measurements. It is concluded that the complementary optical methods of polarization (ellipsometry) and interference hold considerable promise for application to the rapid measurement of condensation and evaporation rates in high temperature (e.g., combustion product) environments.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159753 , SAR-4
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  • 49
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    JT8D and JT9D jet engine performance improvement program. Task 1: Feasibility analysis (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: JT8D and JT9D component performance improvement concepts which have a high probability of incorporation into production engines were identified and ranked. An evaluation method based on airline payback period was developed for the purpose of identifying the most promising concepts. The method used available test data and analytical models along with conceptual/preliminary designs to predict the performance improvements, weight, installation characteristics, cost for new production and retrofit, maintenance cost, and qualitative characteristics of candidate concepts. These results were used to arrive at the concept payback period, which is the time required for an airline to recover the investment cost of concept implementation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159449 , PWA-5518-38
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  • 50
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    The analysis of propellers including interaction effects (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Analytical and experimental studies were undertaken on propellers operating in the unsteady flow field produced by interaction effects due to the fuselage, wing, and nacelles. Methods were developed and verified experimentally for determining the velocity field in which a propeller operates as well as its aerodynamic and dynamic response to this unsteady environment. Methods are presented for predicting and net thrust of a propeller-wing-body combination as well as the unsteady thrust and torque acting on the propeller. Sample calculations as well as wind tunnel and flight test results are presented which illustrate the sensitivity of a propeller to the flow field in which it is operating.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-158111 , SAE Business Aircraft Meeting; Apr 03, 1979 - Apr 06, 1979; Wichita, KS; United States
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  • 51
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    Analysis of radiation patterns of interaction tones generated by inlet rods in the JT15D engine (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Interaction tones were intentionally generated by circumferential arrays of equally spaced rods that protrude radially from the inlet wall near the face of the 28-blade fan. Arrays of 28 and 41 rods, selected to give specific far field radiation properties, were tested. The expected properties were readily apparent in the measured radiation patterns. A more detailed analysis of the test data showed both the precision and limitations of the applied acoustic theory. Rods protruding 23 percent of the radius predominantly generated only lowest radial order modes, as expected. Measured and predicted radiation patterns were generally in good agreement. The agreement, however, depended on a significant degree of implied refraction due to inlet velocity gradients. Refraction, if present, would impact static-flight noise comparisons.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-79074 , E-9891 , Aeroacoustics Conf.; Mar 12, 1978 - Mar 14, 1978; Seattle, WA; United States
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  • 52
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    The NASA high pressure facility and turbine test rig (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A description of the facility and turbine test rig is presented. Also discussed is the turbine cooling test program.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-79054 , E-9863 , Project SQUID (ONR) Workshop on Cooling Probl. in Aircraft Gas Turbines; Sep 27, 1978 - Sep 28, 1978; Monterey, CA; United States
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  • 53
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    Calculation of CO concentration for liquid fueled gas turbine combustor (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The extensive computation time required for the numerical integration of the differential equations obtained in studies of the concentrations of pollutants emitted by gas turbine combustors, can be reduced significantly by assuming the heat releasing hydrocarbon reactions to be in local equilibrium. In determining the CO and NO concentrations produced in spray combustion, it is, therefore, tempting to use the same local equilibrium assumption in order to simplify the kinetic calculations. An investigation of the validity of the local equilibrium assumption is conducted by using a simple analytical model, and then by actually carrying out the kinetic and local equilibrium calculations for typical case.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Spring Technical Meeting; Apr 03, 1978 - Apr 04, 1978; West Lafayette, IN
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  • 54
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    Reduction of aircraft gas turbine engine pollutant emissions - A status report (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: In mid-1971, NASA began a major program in emission reduction technology, which would consist of a continuing in-house effort on low emission combustor concepts and of contracted research programs with the major aircraft engine manufacturers. A description is presented of the design approaches taken by the manufacturers involved in the contracted programs. Current results are compared with EPA standards, and some of the engine related factors are briefly considered. In addition, some results from fundamental technology programs which indicate the emission levels which may be approached by advanced low emission combustors of the future are also discussed. It is found that special engine design features represent at least a partial solution to reducing aircraft emissions for engines of the future.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Annual Meeting of the Air Pollution Control Association; Jun 26, 1978 - Jun 30, 1978; Houston, TX
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  • 55
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    The effect of cycle variables on the emissions and performance of lean premixed gas turbine primary zone combustor (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Experiments were conducted in which a stream of premixed propane and air was burned under conditions representative of gas-turbine operation. Emissions of NOx, CO, and unburned hydrocarbons were measured over a range of combustor inlet temperature (600-1000 K), pressure (5-30 atm), and residence time (1-3 msec) at equivalence ratios from 0.7 down to the lean stability limit. At inlet temperatures of 800 and 1000 K, NOx emissions displayed little sensitivity to pressure. At an inlet temperature of 600 K, observed NOx levels dropped markedly with decreasing pressure for pressures below 20 atm. NOx levels were proportional to combustor residence time, and formation rate was principally a function of adiabatic flame temperature. For adiabatic flame temperatures of 2050 K and higher, CO reached chemical equilibrium within 2 msec. Unburned hydrocarbon species dropped to a negligible level within 2 msec regardless of inlet temperature, pressure, or equivalence ratio. For a combustor residence time of 2.5 msec, combustion inefficiency became less than 0.01% at an adiabatic flame temperature of 2050 K. The maximum combustion inefficiency observed was of the order of 1% and corresponded to conditions near the lean stability limit.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-1039 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
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  • 56
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    Combustor concepts for aircraft gas turbine low-power emissions reduction (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Three combustor concepts have been designed and tested to demonstrate significant reductions in aircraft engine idle pollutant emissions. Each concept used a different approach for pollutant reductions: the Hot Wall Combustor employs a thermal barrier coating and impingement cooled liners, the Recuperative Cooling Combustor preheats the air before entering the combustion chamber, and the Catalytic Converter Combustor is composed of a conventional primary zone followed by a catalytic bed for pollutant cleanup. The designs are discussed in detail and test results are presented for a range of aircraft engine idle conditions. The results indicate that ultra-low levels of unburned hydrocarbons and carbon monoxide emissions can be achieved with this technology.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-999 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
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  • 57
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    Design and preliminary results of a semitranspiration cooled /Lamilloy/ liner for a high-pressure high-temperature combustor (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A Lamilloy combustor liner has been designed, fabricated and tested in a combustor at pressures up to 8 atmospheres. The liner was fabricated of a three layer Lamilloy structure and designed to replace a conventional step-louver liner. The liner will be used in a combustor that provides hot gases to a turbine cooling test facility at pressures up to 40 atmospheres. The Lamilloy liner was tested extensively at lower pressures and demonstrated lower metal temperatures than the conventional liner, while at the same time requiring about 40 percent less cooling air flow. Tests conducted at combustor exit temperatures in excess of 2200 K have not indicated any cooling or durability problems with the Lamilloy liner.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-997 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
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  • 58
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    General aviation internal combustion engine research programs at NASA-Lewis Research Center (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An update is presented of non-turbine general aviation engine programs underway at the NASA-Lewis Research Center in Cleveland, Ohio. The program encompasses conventional, lightweight diesel and rotary engines. Its three major thrusts are: (a) reduced SFC's; (b) improved fuels tolerance; and (c) reducing emissions. Current and planned future programs in such areas as lean operation, improved fuel management, advanced cooling techniques and advanced engine concepts, are described. These are expected to lay the technology base, by the mid to late 1980's, for engines whose life cycle fuel costs are 30 to 50% lower than today's conventional engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-932 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
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  • 59
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    On the use of relative velocity exponents for jet engine exhaust noise (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The effect of flight on jet engine exhaust noise has often been presented in terms of a relative velocity exponent, n, as a function of radiation angle. The value of n is given by the OASPL reduction due to relative velocity divided by 10 times the logarithm of the ratio of relative jet velocity to absolute jet velocity. It is shown in this paper that the exponent n is positive for pure subsonic jet mixing noise and varies, in a systematic manner, as a function of flight conditions and jet velocity. On the basis of calculations from simple empirical models for jet mixing noise, shock noise and internally-generated noise, it is shown that when other sources are present, the resulting range of n is increased over the range for jet mixing noise, and in some cases negative values of n are obtained.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Meeting of the Acoustical Society of America; May 16, 1978 - May 19, 1978; Providence, RI
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  • 60
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    State-of-the-art of turbofan engine noise control (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A description is presented of some of the recent advances in the technology of turbofan engine noise reduction, taking into account turbomachinery noise sources, new fans for low noise, fan and core noise suppression, and a new program for improving static noise testing of fans and engines. The problem of jet noise has been substantially reduced in connection with the lower jet velocities employed in the case of the high bypass turbofan engines. The dominant noise sources are now related to the turbomachinery with the fan stage, the compressor, and the turbine. Since the fan stage is the primary source of turbomachinery noise, it has been considered in a major part of the investigations designed to reduce turbofan engine noise.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: In: NOISE-CON 77; National Conference on Noise Control Engineering; Oct 17, 1977 - Oct 19, 1977; Hampton, VA
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  • 61
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    Gas path sealing in turbine engines (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Survey of gas path seals is presented with particular attention given to sealing clearance effects on engine component efficiency. The effects on compressor pressure ratio and stall margin are pointed out. Various case-rotor relative displacements, which affect gas path seal clearances, are identified. Forces produced by nonuniform sealing clearances and their effect on rotor stability are discussed qualitatively, and recent work on turbine-blade-tip sealing for high temperatures is described. The need for active clearance control and for engine structural analysis is discussed. The functions of the internal-flow system and its seals are reviewed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Power, Energetics, and Propulsion Panel Meeting on Seal Technology in Gas Turbine Engines, London; Apr 06, 1978 - Apr 07, 1978; London
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  • 62
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    Effect of airstream velocity on mean drop diameters of water sprays produced by pressure and air atomizing nozzles (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A scanning radiometer was used to determine the effect of airstream velocity on the mean drop diameter of water sprays produced by pressure atomizing and air atomizing fuel nozzles used in previous combustion studies. Increasing airstream velocity from 23 to 53.4 meters per second reduced the Sauter mean diameter by approximately 50 percent with both types of fuel nozzles. The use of a sonic cup attached to the tip of an air assist nozzle reduced the Sauter mean diameter by approximately 40 percent. Test conditions included airstream velocities of 23 to 53.4 meters per second at 293 K and atmospheric pressure.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Winter Annual Meeting; Nov 27, 1977 - Dec 02, 1977; Atlanta, GA
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  • 63
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    General aviation energy-conservation research programs at NASA-Lewis Research Center (1977)
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    Publication Date: 2019-07-13
    Description: A review is presented of non-turbine general aviation engine programs underway at the NASA-Lewis Research Center in Cleveland, Ohio. The program encompasses conventional, lightweight diesel and rotary engines. Its three major thrusts are, in order of priority: (1) reduced SFCs; (2) improved fuels tolerance; and (3) reducing emissions. Current and planned future programs in such areas as lean operation, improved fuel management, advanced cooling techniques and advanced engine concepts, are described. These are expected to lay the technology base, by the mid to latter 1980s, for engines whose total fuel costs are as much as 30% lower than today's conventional engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Conference on Energy Conservation in General Aviation; Oct 10, 1977 - Oct 11, 1977; Kalamazoo, MI
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  • 64
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    Output feedback regulator design for jet engine control systems (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A multivariable control design procedure based on the output feedback regulator formulation is described and applied to an F100 turbofan engine model. Full order model dynamics, are incorporated in the example design. The effect of actuator dynamics on closed loop performance is investigated. Also, the importance of turbine inlet temperature as an element of the dynamic feedback is studied. Step responses are given to indicate the improvement in system performance with this control. Calculation times for all experiments are given in CPU seconds for comparison purposes.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: National Electronics Conference; Oct 13, 1977 - Oct 14, 1977; Chicago, IL
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  • 65
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    Effectiveness of an inlet flow turbulence control device to simulate flight fan noise in an anechoic chamber (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A hemispherical inlet flow control device was tested on a 50.8 cm. (20-inch) diameter fan stage in the NASA-Lewis Anechoic Chamber. The control device used honeycomb and wire mesh to reduce turbulence intensities entering the fan. Far field acoustic power level results showed about a 5 dB reduction in blade passing tone and about 10 dB reduction in multiple pure tone sound power at 90% design fan speed with the inlet device in place. Hot film cross probes were inserted in the inlet to obtain data for two components of the turbulence at 65 and 90% design fan speed. Without the flow control device the axial intensities were below 1.0%, while the circumferential intensities were almost twice this value. The inflow control device significantly reduced the circumferential turbulence intensities and also reduced the axial length scale.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Meeting of the Acoustical Society of America; Dec 13, 1977 - Dec 16, 1977; Miami Beach, FL
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  • 66
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    Combustor fluctuating pressure measurements in-engine and in a component test facility - A preliminary comparison (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Combustor internal fluctuating pressure and far-field noise generated in a YF-102 turbofan engine are investigated; combustor internal measurements are also made in a duct-component test facility operating over a range of conditions encompassing those characteristic of the aircraft engine. Although directly measured spectra for the engine and the duct-component test facility show discrepancies, the results of coherence function, transfer function and phase relationship comparisons suggest that the internal dynamics of the combustor as an acoustic source may be preserved in a component test facility.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Meeting of the Acoustical Society of America; Dec 13, 1977 - Dec 16, 1977; Miami Beach, FL
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  • 67
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    An empirical model for inverted-velocity-profile jet noise prediction (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: It is known that the noise generated by inverted-velocity-profile coaxial (without center plug) and coannular (with center plug) nozzles should be modeled as the combined contributions of various source regions and noise generation mechanisms. In this paper, an empirical noise-prediction model is described which considers the noise generated by two jet-mixing regions and two potential regions of shock/turbulence interaction. Results calculated from the empirical model are compared with model-scale experimental data for static and simulated flight conditions. These comparisons are made for cases where both streams are subsonic, where the outer stream is supersonic with the inner stream subsonic, and where both streams are supersonic. The cases considered cover a range of inner-to-outer-stream area ratios and include both coaxial and coannular nozzles. It is shown that the model gives reasonable predictions of absolute noise spectra and even better predictions of incremental changes.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Meeting of the Acoustical Society of America; Dec 13, 1977 - Dec 16, 1977; Miami Beach, FL
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  • 68
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    Noise of deflectors used for flow attachment with STOL-OTW configurations (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Future STOL aircraft may utilize engine-over-the-wing (OTW) installations in which the exhaust nozzles are located above and separated from the upper surface of the wing. An external jet-flow deflector can be used with such installations to provide flow attachment to the wing/flap surfaces for lift augmentation. In the present work, the deflector noise in the flyover plane measured with several model-scale nozzle/deflector/wing configurations is examined. The deflector-associated noise is correlated in terms of velocity and geometry parameters. The data also indicate that the effective overall sound pressure level of the deflector-associated noise peaks in the forward quadrant near 40 deg from the inlet axis.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Meeting of the Acoustical Society of America; Dec 13, 1977 - Dec 16, 1977; Miami Beach, FL
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  • 69
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    Failure detection and correction for turbofan engines (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: In this paper, a failure detection and correction strategy for turbofan engines is discussed. This strategy allows continuing control of the engines in the event of a sensor failure. An extended Kalman filter is used to provide the best estimate of the state of the engine based on currently available sensor outputs. Should a sensor failure occur the control is based on the best estimate rather than the sensor output. The extended Kalman filter consists of essentially two parts, a nonlinear model of the engine and up-date logic which causes the model to track the actual engine. Details on the model and up-date logic are presented. To allow implementation, approximations are made to the feedback gain matrix which result in a single feedback matrix which is suitable for use over the entire flight envelope. The effect of these approximations on stability and response is discussed. Results from a detailed nonlinear simulation indicate that good control can be maintained even under multiple failures.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Joint Automatic Control Conference; Jun 22, 1977 - Jun 24, 1977; San Francisco, CA; US
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  • 70
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    Design of turbofan engine controls using output feedback regulator theory (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A multivariable control design procedure based on output feedback regulator (OFR) theory is applied to the F100 turbofan engine. Results for the OFR design are compared to a design based on linear quadratic regulator (LQR) theory. This LQR design was obtained as part of the F100 Multivariable Control Synthesis (MVCS) program. In the MVCS program the LQR feedback control was designed in a reduced dimension state space and then applied to the original system. However, the OFR feedback control is designed in the full order state space and thus eliminates any need for model reduction techniques. Using the performance measure and control structure of the MVCS program LQR design, an equivalent OFR feedback control is obtained. The flexibility of the OFR as a control design procedure is demonstrated and differing feedback control structures are evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Joint Automatic Control Conference; Jun 22, 1977 - Jun 24, 1977; San Francisco, CA
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  • 71
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    Optimal controls for an advanced turbofan engine (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Linear optimal control theory is applied to the control synthesis of a high bypass ratio, variable pitch, turbofan engine. The basic control philosophy is to use only a low order dynamic model of the plant coupled with the concept of integral-output states so as to maintain control simplicity yet guarantee integral control of thrust, turbine temperature and other important engine outputs. Linear simulation results indicate that the control system developed provides rapid control of small thrust perturbations and quickly eliminates the effect of unmodelled thrust and temperature disturbances. Large thrust accelerations are obtained in about one half second while the control maintains negligible overshoot in temperature and stall margins.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Joint Automatic Control Conference; Jun 22, 1977 - Jun 24, 1977; San Francisco, CA
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  • 72
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    The application of the Routh approximation method to turbofan engine models (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The Routh approximation technique is applied in the frequency domain to a 16th order state variable turbofan engine model. The results obtained motivate the extension of the frequency domain formulation of the Routh method to the time domain to handle the state variable formulation directly. The time domain formulation is derived and a new characterization, which specifies all possible Routh similarity transformations, is given. This characterization is computed by the solution of two eigenvalue-eigenvector problems. The application of the time domain Routh technique to the state variable engine model is described and some results are given. Additional computational problems are discussed including an optimization procedure which can improve the approximation accuracy by taking advantage of the transformation characterization.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Joint Automatic Control Conference; Jun 22, 1977 - Jun 24, 1977; San Francisco, CA
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  • 73
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    Minimum-time acceleration of aircraft turbofan engines (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Minimum-time accelerations of the F100 turbofan engine are presented. A piecewise-linear engine model, having three state variables and four control variables, is used to obtain the minimum-time solutions. The linear model which applies at a given time in the trajectory is determined by calculating a normalized 'distance' from the current state to the equilibrium state associated with each linear model. The linear model associated with the closest equilibrium point is then used. The control histories for the minimum-time solutions are used as input to a nonlinear simulation of the F100 engine to verify the accuracy of the piecewise-linear solutions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Joint Automatic Control Conference; Jun 22, 1977 - Jun 24, 1977; San Francisco, CA
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  • 74
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    Frequency domain compensation of a DYNGEN turbofan engine model (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Following Rosenbrock's ideas regarding the advantages of dominance in linear multivariable control systems, a new graphical technique is used for the design of compensators that achieve dominance. The technique is illustrated with an application to the problem of designing compensators for a linear turbofan-engine model. The resulting design is put into perspective by examining it in the light of two other multivariable frequency-domain methods. One, MacFarlane's method of characteristic loci, is used to realize a final design for stability and low interaction. The other is a direct technique based upon the algebraic expansion of the determinant of the return difference in terms of it's elements. Results from simulations carried out on the NASA DYNGEN software are included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Joint Automatic Control Conference; Jun 22, 1977 - Jun 24, 1977; San Francisco, CA
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  • 75
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    Preliminary QCSEE program - Test results (1977)
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    Publication Date: 2019-07-13
    Description: Preliminary results are reported for the Quiet Clean Short-haul Experimental Engine (QCSEE) program initiated by NASA in 1974 to develop propulsion system technology suitable for powered-lift short-range commercial aircraft. The QCSEE technology also has applications to the proposed U.S. Navy V/STOL aircraft. Emphasis in the QCSEE program is placed on developing engines with low noise characteristics; in addition, the power plants are required to conform to EPA 1979 pollutant emissions standards. Thrust performance, fan design, and thrust/weight ratio are discussed for both the over-the-wing and under-the-wing engine configurations under study.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 771008 , Aerospace Meeting; Nov 14, 1977 - Nov 17, 1977; Los Angeles, CA
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  • 76
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    Stress analysis study in cooled radial inflow turbine (1978)
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    Publication Date: 2019-07-13
    Description: With increased turbine inlet temperatures, numerical methods of thermal and stress analysis are becoming more valuable in the design of air-cooled turbines. This paper presents a study of the stresses associated with different cooling patterns in a radial inflow turbine rotor. The finite element method is used in the stress calculations taking into consideration centrifugal, thermal and aerodynamic loading. The effects of temperature distribution and the presence of internal cooling passages are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-94 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
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  • 77
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    The effect of ambient conditions on the emissions of an idling gas turbine (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Changes in ambient conditions - pressure, temperature, and humidity - affect the exhaust emissions of a gas turbine engine. Such variations must be compensated for during engine certification. The results of a test program employing a JT8D-17 combustor are presented which quantize the effect of carefully controlled changes on unburned hydrocarbons, carbon monoxide, and oxides of nitrogen at simulated idle operating conditions. Analytical results are given to explain the observed hydrocarbon and carbon monoxide behavior. It is shown that for a complete range of possible ambient variations, significant changes do occur in the amount of pollutants emitted by an idling gas turbine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-3 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
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  • 78
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    A study of axial compressor blade optimization for operation in the low Reynolds number regime (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Original and previously published experimental data is presented in this study of axial compressor blade optimization for use in the subcritical Reynolds number region. Three methods of increasing cascade performance at these low Rc are presented, discussed, and compared: (1) use of sharp-leading-edge profiles, (2) trip wires or roughness elements, and (3) high free-stream turbulence. The original data was collected in the VKI C-1 cascade wind tunnel; during these tests blade chord Reynolds number was varied from 250,000 down to about 17,000. Each technique demonstrated an increase in low Reynolds number (based on chord) performance for certain profiles, with the sharp-leading-edge profile as the potential optimum. Axial compressors or pumps that must operate for a significant amount of their design life under low Reynolds number conditions might benefit substantially from these methods.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-245 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
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  • 79
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    Alternatives for jet engine control (1978)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: General goals of the research were classified into two categories. The first category involves the use of modern multivariable frequency domain methods for control of engine models in the neighborhood of a quiescent point. The second category involves the use of nonlinear modelling and optimization techniques for control of engine models over a more extensive part of the flight envelope. In the frequency domain category, works were published in the areas of low-interaction design, polynomial design, and multiple setpoint studies. A number of these ideas progressed to the point at which they are starting to attract practical interest. In the nonlinear category, advances were made both in engine modelling and in the details associated with software for determination of time optimal controls. Nonlinear models for a two spool turbofan engine were expanded and refined; and a promising new approach to automatic model generation was placed under study. A two time scale scheme was developed to do two-dimensional dynamic programming, and an outward spiral sweep technique has greatly speeded convergence times in time optimal calculations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-157578
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  • 80
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    A computer program for full-coverage film-cooled blading analysis including the effects of a thermal barrier coating (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The program input, coolant flow and heat transfer model, and the program output are discussed. As an example, sections of the suction and pressure sides of a high temperature, high pressure turbine vane are analyzed to show the effects of a thermal barrier coating. Compared to the uncoated design, the coating halves the required coolant flow, while simultaneously reducing metal outer temperatures by over 111 K.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78951 , AVRADCOM-TR-78-31(PL) , E-9696 , Winter Ann. Meeting of ASME; Dec 10, 1978 - Dec 15, 1978; San Francisco
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  • 81
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    Fuel conservative aircraft engine technology (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Technology developments for more fuel-efficiency subsonic transport aircraft are reported. Three major propulsion projects were considered: (1) engine component improvement - directed at current engines; (2) energy efficient engine - directed at new turbofan engines; and (3) advanced turboprops - directed at technology for advanced turboprop-powered aircraft. Each project is reviewed and some of the technologies and recent accomplishments are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78962 , E-9719 , Congr. of the Intern. Council of Aeronautical Sci.; Sep 10, 1978 - Sep 16, 1978; Lisbon; Portugal
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  • 82
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    Inlet-engine matching for SCAR including application of a bicone variable geometry inlet (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Airflow characteristics of variable cycle engines (VCE) designed for Mach 2.32 can have transonic airflow requirements as high as 1.6 times the cruise airflow. This is a formidable requirement for conventional, high performance, axisymmetric, translating centerbody mixed compression inlets. An alternate inlet is defined, where the second cone of a two cone center body collapses to the initial cone angle to provide a large off-design airflow capability, and incorporates modest centerbody translation to minimize spillage drag. Estimates of transonic spillage drag are competitive with those of conventional translating centerbody inlets. The inlet's cruise performance exhibits very low bleed requirements with good recovery and high angle of attack capability.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78955 , E-9706 , Propulsion Conf.; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; United States
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  • 83
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    Liquid-cooling technology for gas turbines review and status (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A review of research related to liquid cooling of gas turbines was conducted and an assessment of the state of the art was made. Various methods of liquid cooling turbines were reviewed. Examples and results with test and demonstrator turbines utilizing these methods along with the advantages and disadvantages of the various methods are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78906 , AVRADCOM-TR-78-26(PL) , E-9517-1 , Intersoc. Energy Conversion Eng. Conf.; Aug 20, 1978 - Aug 25, 1978; San Diego, CA; United States
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  • 84
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    End-wall boundary layer prediction for axial compressors (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An integral boundary layer procedure was developed for the computation of viscous and secondary flows along the annulus walls of an axial compressor. The procedure is an outgrowth and extension of the pitch-averaged methods of Mellor and Horlock. In the present work secondary flow theory is used to develop approximations for the velocity profiles inside a rotating blade row and for the blade force deficit terms in the momentum integral equations. The computer code based on this procedure was iteratively coupled to a quasi-one-dimensional model for the external inviscid flow. Computed results are compared with measurements in a compressor cascade.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78928 , E-9668 , Fluid and Plasma Dynamics Conf.; Jul 10, 1978 - Jul 12, 1978; Seattle
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  • 85
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    Emittance and absorptance of NASA ceramic thermal barrier coating system (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Spectral emittance measurements were made on a two-layer ceramic thermal barrier coating system consisting of a metal substrate, a NiCrAly bond coating and a yttria-stabilized zirconia ceramic coating. Spectral emittance data were obtained for the coating system at temperatures of 300 to 1590 K, ceramic thickness of zero to 0.076 centimeter, and wavelengths of 0.4 to 14.6 micrometers. The data were transformed into total hemispherical emittance values and correlated with respect to ceramic coating thickness and temperature using multiple regression curve fitting techniques. The results show that the ceramic thermal barrier coating system is highly reflective and significantly reduces radiation heat loads on cooled gas turbine engine components. Calculation of the radiant heat transfer within the nonisothermal, translucent ceramic coating material shows that the gas-side ceramic coating surface temperature can be used in heat transfer analysis of radiation heat loads on the coating system.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1190 , E-9474 , Intern. Conf. on Met. Coatings; Apr 03, 1978 - Apr 07, 1978; San Francisco
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  • 86
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    Combustor concepts for aircraft gas turbine low-power emissions reduction (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Several combustor concepts were designed and tested to demonstrate significant reductions in aircraft engine idle pollutant emissions. Each concept used a different approach for pollutant reductions: the hot wall combustor employs a thermal barrier coating and impingement cooled liners; the recuperative cooling combustor preheats the air before entering the combustion chamber; and the catalytic converter combustor is composed of a conventional primary zone followed by a catalytic bed for pollutant cleanup. The designs are discussed in detail and test results are presented for a range of aircraft engine idle conditions. The results indicate that ultralow levels of unburned hydrocarbons and carbon monoxide emissions can be achieved.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78875 , AVRADCOM-TR-78-23(PL) , AIAA PAPER 78-999 , Propulsion Conf.; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; United States
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  • 87
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    Research on the statically thrusting propeller (1978)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Methods for calculating the induced flow at propeller blades were analyzed by treating the wake formation as an initial problem in time. An unsteady vortex lattice technique was applied to the wake formation and the vortex core size was studied.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-157214
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  • 88
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    Development of a plasma sprayed ceramic gas path seal for high pressure turbine application (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Development of the plasma sprayed graded, layered ZRO2/CoCrAlY seal system for gas turbine engine blade tip seal applications up to 1589 K (2400 F) surface temperature was continued. The effect of changing ZRO2/CoCrAlY ratios in the intermediate layers on thermal stresses was evaluated analytically with the goal of identifying the materials combinations which would minimize thermal stresses in the seal system. Three methods of inducing compressive residual stresses in the sprayed seal materials to offset tensile thermal stresses were analyzed. The most promising method, thermal prestraining, was selected based upon potential, feasibility and complexity considerations. The plasma spray equipment was modified to heat, control and monitor the substrate temperature during spraying. Specimens were fabricated and experimentally evaluated to: (1) substantiate the capability of the thermal prestrain method to develop compressive residual stresses in the sprayed structure and (2) define the effect of spraying on a heated substate on abradability, erosion and thermal shock characteristics of the seal system. Thermal stress analysis, including residual stresses and material properties variations, was performed and correlated with thermal shock test results. Seal system performance was assessed and recommendations for further development were made.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135387 , PWA-5569-12
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  • 89
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    General aviation internal-combustion engine research programs at NASA-Lewis Research Center (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An update is presented of non-turbine general aviation engine programs. The program encompasses conventional, lightweight diesel and rotary engines. It's three major thrusts are: (1) reduced SFC's; (2) improved fuels tolerance; and (3) reduced emissions. Current and planned future programs in such areas as lean operation, improved fuel management, advanced cooling techniques and advanced engine concepts, are described. These are expected to lay the technology base, by the mid to latter 1980's, for engines whose life cycle fuel costs are 30 to 50% lower than today's conventional engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78891 , E-9628 , Propulsion Conf.; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; United States
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  • 90
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    On the use of relative velocity exponents for jet engine exhaust noise (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effect of flight on jet engine exhaust noise has often been presented in terms of a relative velocity exponent, n, as a function of radiation angle. The value of n is given by the OASPL reduction due to relative velocity divided by 10 times the logarithm of the ratio of relative jet velocity to absolute jet velocity. In such terms, classical subsonic jet noise theory would result in a value of n being approximately 7 at 90 degree angle to the jet axis with n decreasing, but remaining positive, as the inlet axis is approached and increasing as the jet axis is approached. However, flight tests have shown a wide range of results, including negative values of n in some cases. In this paper it is shown that the exponent n is positive for pure subsonic jet mixing noise and varies, in a systematic manner, as a function of flight conditions and jet velocity.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78873 , E-9605 , Meeting of Acoust. Soc. of Am.; May 16, 1978 - May 19, 1978; Providence, RI; United States
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  • 91
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    Design and preliminary results of a semitranspiration cooled (Lamilloy) liner for a high-pressure high-temperature combustor (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A Lamilloy combustor liner was designed, fabricated and tested in a combustor at pressures up to 8 atmospheres. The liner was fabricated of a three layer Lamilloy structure and designed to replace a conventional step louver liner. The liner is to be used in a combustor that provides hot gases to a turbine cooling test facility at pressures up to 40 atmospheres. The Lamilloy liner was tested extensively at lower pressures and demonstrated lower metal temperatures than the conventional liner, while at the same time requiring about 40 percent less cooling air flow. Tests conducted at combustor exit temperatures in excess of 2200 K have not indicated any cooling or durability problems with the Lamilloy linear.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78874 , E-9607 , Propulsion Conf.; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; United States
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  • 92
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    Reduction of aircraft gas turbine engine pollutant emissions (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: To accomplish simultaneous reduction of unburned hydrocarbons, carbon monoxide, and oxides of nitrogen, required major modifications to the combustor. The modification most commonly used was a staged combustion technique. While these designs are more complicated than production combustors, no insurmountable operational difficulties were encountered in either high pressure rig or engine tests which could not be resolved with additional normal development. The emission reduction results indicate that reductions in unburned hydrocarbons were sufficient to satisfy both near and far-termed EPA requirements. Although substantial reductions were observed, the success in achieving the CO and NOx standards was mixed and depended heavily on the engine/engine cycle on which it was employed. Technology for near term CO reduction was satisfactory or marginally satisfactory. Considerable doubt exists if this technology will satisfy all far-term requirements.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78870 , E-9601 , Ann. Meeting of the Air Pollution Control Assoc.; Jun 26, 1978 - Jun 30, 1978; Houston, TX; United States
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  • 93
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    Impact behavior of filament wound graphite/epoxy fan blades (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The fabrication and impact tests of graphite/epoxy filament wound fan blades are discussed. Blades which were spin tested at tip speeds up to 305 meters per second retained their structural integrity. Two blades were each impacted with a 454 gram slice of a 908 gram simulated bird at a tip speed of 263 meters per second and impact angles of 22 and 32 deg. The impact tests were recorded with high-speed movie film. The blade which was impacted at 22 deg sustained some root delamination but remained intact. The 32 deg impact separated the blade from the root. No local damage other than leading edge debonding was observed for either blade. Results of a failure mode analysis are also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78845 , E-9562 , Natl. SAMPE Symp. and Exhibition; May 02, 1978 - May 04, 1978; Anaheim, CA; United States
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  • 94
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    F100(3) parallel compressor computer code and user's manual (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Pratt & Whitney Aircraft multiple segment parallel compressor model has been modified to include the influence of variable compressor vane geometry on the sensitivity to circumferential flow distortion. Further, performance characteristics of the F100 (3) compression system have been incorporated into the model on a blade row basis. In this modified form, the distortion's circumferential location is referenced relative to the variable vane controlling sensors of the F100 (3) engine so that the proper solution can be obtained regardless of distortion orientation. This feature is particularly important for the analysis of inlet temperature distortion. Compatibility with fixed geometry compressor applications has been maintained in the model.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135388 , PWA-5549-8
    Format: application/pdf
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  • 95
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    Gas Path Sealing in Turbine Engines (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A survey of gas path seals is presented with particular attention given to sealing clearance effects on engine component efficiency. The effects on compressor pressure ratio and stall margin are pointed out. Various case-rotor relative displacements, which affect gas path seal clearances, are identified. Forces produced by nonuniform sealing clearances and their effect on rotor stability are discussed qualitatively, and recent work on turbine-blade-tip sealing for high temperature is described. The need for active clearance control and for engine structural analysis is discussed. The functions of the internal-flow system and its seals are reviewed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-73890 , E-9505 , AGARD Power, Energetics, and Propulsion Panel Meeting on Seal Technol. in Gas Turbine Engines; Apr 06, 1978 - Apr 07, 1978; London
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  • 96
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    High temperature environmental effects on metals (1977)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The gas turbine engine was used as an example to predict high temperature environmental attack on metals. Environmental attack in a gas turbine engine derives from high temperature, combustion products of the air and fuel burned, and impurities. Of all the modes of attack associated with impurity effects, hot corrosion was the most complicated mechanistically. Solutions to the hot corrosion problem were sought semi-empirically in: (1) improved alloys or ceramics; (2) protective surface coating; (3) use of additives to the engine environment; and (4) air/fuel cleanup to eliminate harmful impurities.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-73878 , Sagamore Army Materials Res., Conf. Risk and Failure Analysis for Reliability; Aug 22, 1977 - Aug 26, 1977; Bolton Landing, NY; United States
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  • 97
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    Theoretical and experimental study of aerodynamics, heat transfer and performance of a radial turbine (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A two-dimensional finite difference numerical technique is presented to determine the temperature distribution in a solid blade of a radial turbine guide vane. A computer program is written in FORTRAN 4 for the IBM 370/165 computer. The computer results obtained from these programs have a similar behavior and trend as those obtained by experimental results.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-152105
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  • 98
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    Predicted inlet gas temperatures for tungsten fiber reinforced superalloy turbine blades (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Tungsten fiber reinforced superalloy composite (TFRS) impingement cooled turbine blade inlet gas temperatures were calculated taking into account material spanwise strength, thermal conductivity, material oxidation resistance, fiber-matrix interaction, and coolant flow. Measured values of TFRS thermal conductivities are presented. Calculations indicate that blades made of 30 volume percent fiber content TFRS having a 12,000 N-m/kg stress-to-density ratio while operating at 40 atmospheres and a 0.06 coolant flow ratio could permit a turbine blade inlet gas temperature of over 1900K. This is more than 150K greater than similar superalloy blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-73842 , Intern. Conf. on Composite Materials; Apr 16, 1978 - Apr 20, 1978; Toronto; Canada
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  • 99
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    F-15/nonaxisymmetric nozzle system integration study support program (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Nozzle and cooling methods were defined and analyzed to provide a viable system for demonstration 2-D nozzle technology on the F-15 aircraft. Two candidate cooling systems applied to each nozzle were evaluated. The F-100 engine mount and case modifications requirements were analyzed and the actuation and control system requirements for two dimensional nozzles were defined. Nozzle performance changes relative to the axisymmetric baseline nozzle were evaluated and performance and weight characteristics for axisymmetric reference configurations were estimated. The infrared radiation characteristics of these nozzles installed on the F-100 engine were predicted. A full scale development plan with associated costs to carry the F100 engine/two-dimensional (2-D) nozzle through flight tests was defined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135252 , FR-9232
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  • 100
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    Investigation of the unsteady pressure distribution on the blades of an axial flow fan (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The unsteady response of a stator blade caused by the interaction of the stator with the wakes of an upstream rotor was investigated. Unsteady pressure distributions were measured using a blade instrumented with a series miniature pressure transducers. The influence of several geometrical and flow parameters - rotor/stator spacing, stator solidity and stator incidence angle - were studied to determine the unsteady response of the stator to these parameters. A major influence on the stator unsteady response is due to the stator solidity. At high solidities the blade-to-blade interference has a larger contribution. While the range of rotor/stator spacings investigated had a minor influence, the effect of stator incidence angle is significant. The data indicate the existence of an optimum positive incidence which minimizes the unsteady response.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-155771
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