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  • Other Sources  (219)
  • AIRCRAFT PROPULSION AND POWER  (219)
  • 2010-2014
  • 1980-1984  (219)
  • 1981  (219)
  • 1
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    Quiet propulsive-lift technology ready for civil and military applications (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The Quiet Short-Haul Research Aircraft (QSRA) was designed as research aircraft for investigating terminal-area operations with an advanced propulsive-lift aircraft. The QSRA is a modified De Havilland C-8 Buffalo. The modification to the C-8 consisted of adding a new swept wing with four top-mounted Lycoming YF-102 turbofan engines to provide high levels of propulsive-lift through upper-surface blowing. The state of the art has reached the point where consideration can be given to various applications, including military transport aircraft, civil transports, and business jets. Attention is also given to a ground attack plane with QSRA, the payload advantage resulting from applying propulsive-life technology, and aspects of takeoff performance
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 19; Apr. 198
    Format: text
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  • 2
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    Component research for future propulsion systems (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The factors affecting the helicopter market for the past, present, and future are reviewed. Acquisition cost, mission reliability, life cycle cost and civil and military aspects are reviewed. The potential for advanced vehicle configurations with substantial improvements in energy efficiency, operating economics, and characteristics to satisfy the demands of the future market are identified. Advanced propulsion systems required to support these vehicle configurations and the component technology for the engine systems are discussed. The selection of components in areas of economics and efficiency is considered.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Helicopter Propulsion Systems; 12 p
    Format: text
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  • 3
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    Investigation of performance deterioration of the CF6/JT9D high bypass ratio turbofan engines (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The extent and magnitude of performance deterioration of the Pratt and Whitney JT9D, and the General Electric CF6 engine models is presented. Overall engine and contributing module performance deterioration with respect to flight cycles and/or time are analyzed. The overall engine performance deterioration analyses are based on data obtained from historical records, special engine tests, and tests for specific effects. Hardware inspection data from overhaul shops and special module tests are the basis for the modular performance deterioration data used in the analyses. Various damage mechanisms such as seal rubs, erosion, surface roughness and thermal distortion, and how they contribute to performance deterioration are included in the modular analyses. Results indicate that early performance deterioration occurring within the first few flights of these engines is less than 1 percent in cruise specific fuel consumption (SFC), that it is event oriented, and that it is the result of increased blade tip clearances. This performance deterioration gradually increases to about 2.5 to 3.0 percent (including the initial short term deterioration) after 2500 to 3000 flights where increased blade tip clearances, airfoil quality degradation, and thermal distortion are the contributing causes.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Turbine Engine Testing; 14 p
    Format: text
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  • 4
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    Advanced turboprop installation aerodynamics (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The expected aerodynamic effects of a propfan installed on a thick supercritical wing are summarized qualitatively. Nacelle/wing and jet interactions, slipstream incremental velocity, nonuniform inflow, and swirl loss recovery are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Advan. Aerodyn. and Active Controls; p 171-181
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  • 5
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    An overview of SAE ARP 1587: Aircraft gas turbine engine monitoring system guide (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A systematic approach to developing an engine monitoring system (EMS) is outlined. An extensive shopping list of EMS capabilities and benefits are included. A team approach to developing an EMS is emphasized with a description of the responsibilities of each team member.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 377-380
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  • 6
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    Engine health monitoring systems: Tools for improved maintenance management in the 1980's (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The performance monitoring aspect of maintenance, characteristic of the engine health monitoring system are discussed. An overview of the system activities is presented and a summary of programs for improved monitoring in the 1980's are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 323-340
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  • 7
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    Who needs engine monitoring? (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Operational evaluations of engine monitoring systems (EMS) are discussed. Options for each required EMS phase are reviewed along with the guidance provided for EMS on new systems.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 209-224
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  • 8
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    Advanced turbine blade tip seal system (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An advanced blade/shroud system designed to maintain close clearance between blade tips and turbine shrouds and at the same time, be resistant to environmental effects including high temperature oxidation, hot corrosion, and thermal cycling is described. Increased efficiency and increased blade life are attained by using the advanced blade tip seal system. Features of the system include improved clearance control when blade tips preferentially wear the shrouds and a superior single crystal superalloy tip. The tip design, joint location, characterization of the single crystal tip alloy, the abrasive tip treatment, and the component and engine test are among the factors addressed. Results of wear testing, quality control plans, and the total manufacturing cycle required to fully process the blades are also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 137-152
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  • 9
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    Conservation of Strategic Aerospace Materials (COSAM) (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Research efforts to reduce the dependence of the aerospace industry on strategic metals, such as cobalt (Co), columbium (Cb), tantalum (Ta), and chromium (Cr), by providing the materials technology needed to minimize the strategic metal content of critical aerospace components for gas turbine engines are addressed. Thrusts in three technology areas are identified: near term activities in the area of strategic element substitution; intermediate-range activities in the area of materials processing; and long term, high risk activities in the area of 'new classes' of high temprature metallic materials. Specifically, the role of cobalt in nickel-base and cobalt-base superalloys vital to the aerospace industry is examined along with the mechanical and physical properties of intermetallics that will contain a minimum of the stragetic metals.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Engine Diagnostics; p 189-207
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  • 10
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    The nature of operating flight loads and their effect on propulsion system structures (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Past diagnostics studies revealed the primary causes of performance deterioration of high by-pass turbofan engines to be flight loads, erosion, and thermal distortion. The various types of airplane loads that are imposed on the engine throughout the lifetime of an airplane are examined. These include flight loads from gusts and maneuvers and ground loads from takeoff, landing, and taxi conditions. Clarification is made in definitions of the airframer's limit and ultimate design loads and the engine manufacturer's operating design loads. Finally, the influence of these loads on the propulsion system structures is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 175-188
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  • 11
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    Performance retention of the RB211 powerplant in service (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An understanding of the mechanisms of deterioration is essential in order that features to counteract performance degradation can be built into the basic design of an engine and nacelle. Furthermore, the interpretation must be continued in service for effective feedback to provide modifications which may be necessary in maintaining a satisfactory performance retention program. The in service assessment must be accurate as to magnitude and causes and this requires consideration of: (1) the powerplant as a complete entity, i.e., the engine components and nacelle including the thrust reverser; (2) measurement of performance in flight rather than by sole reliance on the scaling of test cell data to flight conditions (although some correlation should be possible); and (3) the relationship of engine parts condition to overhaul performance and in flight deterioration level of that engine. These aspects are addressed by consideration of the RB211 engine in service in both the Lockheed L1011 Tristar and Boeing 747 aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 83-102
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  • 12
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    CF6 High Pressure Compressor and Turbine Clearance Evaluations (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In the CF6 Jet Engine Diagnostics Program the causes of performance degradation were determined for each component of revenue service engines. It was found that a significant contribution to performance degradation was caused by increased airfoil tip radial clearances in the high pressure compressor and turbine areas. Since the influence of these clearances on engine performance and fuel consumption is significant, it is important to accurately establish these relatonships. It is equally important to understand the causes of clearance deterioration so that they can be reduced or eliminated. The results of factory engine tests run to enhance the understanding of the high pressure compressor and turbine clearance effects on performance are described. The causes of clearance deterioration are indicated and potential improvements in clearance control are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 19-42
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  • 13
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    JT8D engine performance retention (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The attractive performance retention characteristics of the JT8D engine are described. Because of its moderate bypass ratio and turbine temperature, and stiff structural design, the performance retention versus flight cycles of the JT8D engine sets a standard that is difficult for other engines to equal. In addition, the significant benefits of refurbishment of the JT8D engine are presented. Cold section refurbishment offers thrust specific fuel consumption improvements of up to 2 percent and payback in less than a year, making a very attractive investment option for the airlines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 63-81
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  • 14
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    CF 6 engine diagnostics (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A summary of the activities which led to defining deterioration rates of the CF6 family of engines, a description of what was learned, and an identification of means of conserving fuel based upon the program findings are presented. The program to define the deterioration levels and modes for the CF6 family of engines involved four distinct phases: analysis of inbound engine test results, analysis of airline cruise data, analysis of airline test cell data resulting from testing of refurbished engines, and inspection of engine hardware.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 1-17
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  • 15
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    A-10/TF34 Turbine Engine Monitoring System (TEMS) (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The hardware and software development of the A-10/TF34 turbine engine monitoring system (TEMS) is described. The operation and interfaces of the A-10/TF34 TEMS hardware are discussed with particular emphasis on function, capabilities, and limitations. The TEMS data types are defined and the various data acquisition modes are explained. Potential data products are also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 271-283
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  • 16
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    Improving turbine engine compressor performance retention through airfoil coatings (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In order to evaluate the potential effectiveness of coatings in limiting erosive damage to compressor airfoils, an effort was initiated to evaluate candidate coatings for substrate alloys typically used in commercial engine high compressor blades. Laboratory and rig erosion testing of plasma deposited and diffusion coatings described in this paper have shown the potential of a two to four fold improvement in erosion life. The selective application of these coatings to approximately the outer third of the airfoil avoids coating the fatigue critical region of the blade, thus providing erosion resistance potentially without compromising the fatigue strength of the blade. Both the plasma and the diffusion coatings also offer the advantage of low initial cost and a multi-source production base.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 109-117
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  • 17
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    Engine condition monitoring: CF6 family 60's through the 80's (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The on condition program is described in terms of its effectiveness as a maintenance tool both at the line station as well as at home base by the early detection of engine faults, erroneous instrumentation signals and by verification of engine health. The system encompasses all known methods from manual procedures to the fully automated airborne integrated data system.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 341-356
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  • 18
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    Review of AIDS development (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The operation and implementation of the aircraft integrated data system AIDS are described. The system is described as an engineering tool with strong emphasis on analysis of recorded information. The AIDS is primarily directed to the monitoring of parameters related to: the safety of the flight; the performance of the aircraft; the performance of the flight guidance system; and the performance and condition of the engines. The system provide short term trend analysis on a trend chart that is updated by the flight engineer on every flight that lasts more than 4 flight hours. Engine data prints are automatically presented during take-off and in the case of limit excedance, e.g., the print shows an automatically reported impending hotstarts on engine nr. 1. Other significant features are reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 285-310
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  • 19
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    F100 engine diagnostic system status to date (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An engine diagnostic system, proposed for the F100 engine, was tested in five specially modified Tactical Air Command F-15 aircraft during a 16-month flight evaluation. After more than 3300 engine operating hours encompassing almost 900 flights during the flight evaluation, these aircraft provided a data base, still being analyzed, that has shown successful demonstration of the original functional characteristics. Four general design requirements, recording engine operating time/low cycle fatigue event detection, engine trim, and trend and performance data collection were demonstrated. Also, validation of maintenance actions taken and indicated needed maintenance were successfully demonstrated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 225-242
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  • 20
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    An introduction to NASA's turbine engine hot section technology (HOST) project (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An overview of research to develop and improve the accuracy of current analysis methods so that increased durability can be designed into future engines is presented. Emphasis is placed on improved accuracy in life prediction. Component design, including description of the thermal and aerodynamic environments, the material's mechanical response, the interactions between environmental and structural response, and high temperature instrumentation capable of measuring near-engine environment effects are addressed. Component tests, improved modeling of the physical phenomena, and tests to verify the proved models are also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Engine Diagnostics; p 153-173
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  • 21
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    Performance deterioration: An airline perspective (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Certain features of engine design and installation are clearly demonstrating important advantages in engine performance retention. Bearing arrangement no doubt has an important role in performance retention. Four bearings seem to be insufficient while six are probably more than are required. A well designed five-bearing system would seem to be an optimum configuration. Bearings with over-hung components such as fans, should be designed to minimize such over-hang to limit associated wobble, which in turn leads to shroud rub, or to allow closer running clearances. Almost any effort to improve stiffness and generally reduce flexing of the engine structure will pay off significantly in performance retention, even at a weight penalty. For this reason cowl load sharing to provide additional rigidity at a low cost in additional weight and complexity is favored.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 103-108
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  • 22
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    Bladed-shrouded-disc aeroelastic analyses: Computer program updates in NASTRAN level 17.7 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In October 1979, a computer program based on the state-of-the-art compressor and structural technologies applied to bladed-shrouded-disc was developed. The program was more operational in NASTRAN Level 16. The bladed disc computer program was updated for operation in NASTRAN Level 17.7. The supersonic cascade unsteady aerodynamics routine UCAS, delivered as part of the NASTRAN Level 16 program was recorded to improve its execution time. These improvements are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165428 , NAS 1.26:165428 , D2536-941006
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  • 23
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    Energy efficient engine high-pressure turbine supersonic cascade technology report (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The performance of two vane endwall geometries and three blade sections for the high-pressure turbine was evaluated in terms of the efficiency requirements of the Energy Efficient Engine high-pressure turbine component. The van endwall designs featured a straight wall and S-wall configuration. The blade designs included a base blade, straightback blade, and overcambered blade. Test results indicated that the S-wall vane configuration and the base blade configuration offered the most promising performance characteristics for the Energy Efficient Engine high-pressure turbine component.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165567 , NAS 1.26:165567 , PWA-5594-152
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  • 24
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    Performance of semi-transportation-cooled liner in high-temperature-rise combustors (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results from tests with the Lamilloy combustor liner are compared with results obtained from a conventionally designed, film cooled, step-louver liner. Operation of the Lamilloy liner with counterrotating swirl combustor fuel modules with mixing venturis was possible to a fuel-air ratio of 0.065 without obtaining excessive liner metal temperatures. At the 0.065 fuel-air condition the average liner metal temperature was 140 K and the maximum local temperature 280 K above the inlet air temperature. Combustion efficiency, pattern factor, and smoke data are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1806 , E-494
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  • 25
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    Exhaust emission survey of an F100 afterburning turbofan engine at simulated altitude flight conditions (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Emissions of carbon monoxide, total oxides of nitrogen, unburned hydrocarbons, and carbon dioxide from an F100, afterburning, two spool turbofan engine at simulated flight conditions are reported. For each flight condition emission measurements were made for two or three power levels from intermediate power (nonafterburning) through maximum afterburning. The data showed that emissions vary with flight speed, altitude, power level, and radial position across the nozzle. Carbon monoxide emissions were low for intermediate power (nonafterburning) and partial afterburning, but regions of high carbon monoxide were present downstream of the flame holder at maximum afterburning. Unburned hydrocarbon emissions were low for most of the simulated flight conditions. The local NOX concentrations and their variability with power level increased with increasing flight Mach number at constant altitude, and decreased with increasing altitude at constant Mach number. Carbon dioxide emissions were proportional to local fuel air ratio for all conditions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81656 , E-673
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  • 26
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    Aerodynamic and acoustic behavior of a YF-12 inlet at static conditions (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An aeroacoustic test program to determine the cause of YF-12 inlet noise suppression was performed with a YF-12 aircraft at ground static conditions. Data obtained over a wide range of engine speeds and inlet configurations are reported. Acoustic measurements were made in the far field and aerodynamic and acoustic measurements were made inside the inlet. The J-58 test engine was removed from the aircraft and tested separately with a bellmouth inlet. The far field noise level was significantly lower for the YF-12 inlet than for the bellmouth inlet at engine speeds above 5500 rpm. There was no evidence that noise suppression was caused by flow choking. Multiple pure tones were reduced and the spectral peak near the blade passing frequency disappeared in the region of the spike support struts at engine speeds between 6000 and 6600 rpm.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-163106 , LR-29623
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  • 27
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    Spectral flame radiance from a tubular-can combustor (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to determine the effects of fuel type, fuel-air ratio, and inlet-air pressure on the spectral flame radiance emanating from a JT8D can combustor. Spectral radiance measurements from 1.55 to 5.5 micrometers of wavelength were recorded and analyzed to determine soot concentration and flame temperature at various axial locations in the combustor. Two fuels differing in volatility, viscosity, and chemical composition were used in this investigation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1722 , E-509
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  • 28
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    Integrated control system for a gas turbine engine (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A control system for a turbofan engine receives signals from a number of engine sensors and from the engine operator, and generates control signals. One control signal regulates the fan exhaust nozzle area in order to control inlet throat Mach number to maintain a low level of engine noise. Additional control signals regulate fuel flow to control engine thrust and fan pitch to control fan speed. A number of schedules are utilized to maintain a predetermined relationship between the controlled parameters and a number of fixed and calculated limits can override the control signals to prevent unsatisfactory engine performance.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 29
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    Apparatus for sensor failure detection and correction in a gas turbine engine control system (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A gas turbine engine control system maintains a selected level of engine performance despite the failure or abnormal operation of one or more engine parameter sensors. The control system employs a continuously updated engine model which simulates engine performance and generates signals representing real time estimates of the engine parameter sensor signals. The estimate signals are transmitted to a control computational unit which utilizes them in lieu of the actual engine parameter sensor signals to control the operation of the engine. The estimate signals are also compared with the corresponding actual engine parameter sensor signals and the resulting difference signals are utilized to update the engine model. If a particular difference signal exceeds specific tolerance limits, the difference signal is inhibited from updating the model and a sensor failure indication is provided to the engine operator.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 30
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    Model aerodynamic test results for two variable cycle engine coannular exhaust systems at simulated takeoff and cruise conditions. Comprehensive data report. Volume 3: Graphical data book 2 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Graphical data from wind tunnel tests of variable cycle engine coannular exhaust nozzles are given. Specifically, aerodynamic data for takeoff conditions are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159819-VOL-3-BK-2 , PWA-5550-50-VOL-3-BK-2
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  • 31
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    Model aerodynamic test results for two variable cycle engine coannular exhaust systems at simulated takeoff and cruise conditions. Comprehensive data report. Volume 3: Graphical data book 1 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A graphical presentation of the aerodynamic data acquired during coannular nozzle performance wind tunnel tests is given. The graphical data consist of plots of nozzle gross thrust coefficient, fan nozzle discharge coefficient, and primary nozzle discharge coefficient. Normalized model component static pressure distributions are presented as a function of primary total pressure, fan total pressure, and ambient static pressure for selected operating conditions. In addition, the supersonic cruise configuration data include plots of nozzle efficiency and secondary-to-fan total pressure pumping characteristics. Supersonic and subsonic cruise data are given.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159819-VOL-3-BK-1 , PWA-5550-50-VOL-3-BK-1
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  • 32
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    Model aerodynamic test results for two variable cycle engine coannular exhaust systems at simulated takeoff and cruise conditions. Comprehensive data report. Volume 2: Tabulated aerodynamic data book 3 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tabulated data from wind tunnel tests evaluating the aerodynamic performance of coannular exhaust nozzles are given for test runs 37 through 65.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159819-VOL-2-BK-3 , PWA-5550-5-VOL-2-BK-3
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  • 33
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    Model aerodynamic test results for two variable cycle engine coannular exhaust systems at simulated takeoff and cruise conditions. Comprehensive data report. Volume 2: Tabulated aerodynamic data book 2 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tabulated aerodynamic data from coannular nozzle performance tests are given for test runs 26 through 37. The data include nozzle thrust coefficient parameters, nozzle discharge coefficients, and static pressure tap measurements.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159819-VOL-2-BK-2 , PWA-5550-50-VOL-2-BK-2
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  • 34
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    Model aerodynamic test results for two variable cycle engine coannular exhaust systems at simulated takeoff and cruise conditions. Comprehensive data report. Volume 1: Design layouts (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The design layouts and detailed design drawings of coannular exhaust nozzle models for a supersonic propulsion system are presented. The layout drawings show the assembly of the component parts for each configuration. A listing of the component parts is also given.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159819-VOL-1 , PWA-5550-50-VOL-1
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  • 35
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    Model aerodynamic test results for two variable cycle engine coannular exhaust systems at simulated takeoff and cruise conditions. Comprehensive data report. Volume 2: Tabulated aeroynamic data book 1 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tabulated data from wind tunnel tests conducted to evaluate the aerodynamic performance of an advanced coannular exhaust nozzle for a future supersonic propulsion system are presented. Tests were conducted with two test configurations: (1) a short flap mechanism for fan stream control with an isentropic contoured flow splitter, and (2) an iris fan nozzle with a conical flow splitter. Both designs feature a translating primary plug and an auxiliary inlet ejector. Tests were conducted at takeoff and simulated cruise conditions. Data were acquired at Mach numbers of 0, 0.36, 0.9, and 2.0 for a wide range of nozzle operating conditions. At simulated supersonic cruise, both configurations demonstrated good performance, comparable to levels assumed in earlier advanced supersonic propulsion studies. However, at subsonic cruise, both configurations exhibited performance that was 6 to 7.5 percent less than the study assumptions. At takeoff conditions, the iris configuration performance approached the assumed levels, while the short flap design was 4 to 6 percent less. Data are provided through test run 25.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159819-VOL-2-BK-1 , PWA-5550-50-VOL-2-BK-1
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  • 36
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    Combustor liner durability analysis (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An 18 month combustor liner durability analysis program was conducted to evaluate the use of advanced three dimensional transient heat transfer and nonlinear stress-strain analyses for modeling the cyclic thermomechanical response of a simulated combustor liner specimen. Cyclic life prediction technology for creep/fatigue interaction is evaluated for a variety of state-of-the-art tools for crack initiation and propagation. The sensitivity of the initiation models to a change in the operating conditions is also assessed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165250 , PWA-5684-19
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  • 37
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    Thermal-barrier-coated turbine blade study (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of coating TBC on a CF6-50 stage 2 high-pressure turbine blade were analyzed with respect to changes in the mean bulk temperature, cooling air requirements, and high-cycle fatigue. Localized spallation was found to have a possible deleterious effect on low-cycle fatigue life. New blade design concepts were developed to take optimum advantage of TBCs. Process and material development work and rig evaluations were undertaken which identified the most promising combination as ZrO2 containing 8 w/o Y2O3 applied by air plasma spray onto a Ni22Cr-10Al-1Y bond layer. The bond layer was applied by a low-pressure, high-velocity plasma spray process onto the base alloy. During the initial startup cycles the blades experienced localized leading edge spallation caused by foreign objects.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165351 , SRD-81-083
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  • 38
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    Development of low modulus material for use in ceramic gas path seal applications (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Three candidate materials were examined: Brunsbond (R) Pad; plasma sprayed porous NiCrAlY; and plasma sprayed low modulus microcracked zirconia. Evaluation consisted of mechanical, thermophysical, and oxidation resistance testing along with optical microscopy and a feasibility demonstration of attaching the material to a suitable substrate. The goals of the program were the following: feasibility of fastening or depositing the low modulus system onto a broad range of substrate alloys; feasibility of depositing or forming the low modulus system to a thickness of 0.19 cm to 0.38 cm; potential to attain a modulus of elasticity in the range of 3.4 to 6.9 GPa (0.5 to 1.0 MSI), and an ultimate strength of 17.2 MPa (2.5 ksi); suitable thermal conductivity; and static oxidation life of at least 1000 hours at 1311 K. The results of the program indicate that all three systems offer attractive properties as a strain isolator material.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165469 , R81-915188-13
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  • 39
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    An experimental study of combustion: The turbulent structure of a reacting shear layer formed at a rearward-facing step (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A premixed propane-air flame is stabilized in a turbulent free shear layer formed at a rearward-facing step. The mean and rms averages of the turbulent velocity flow field were determined by LDV for both reacting and non-reacting flows. The reaching flow was visualized by high speed schlieren photography. Large scale structures dominate the reacting shear layer. The growth of the large scale structures is tied to the propagation of the flame. The linear growth rate of the reacting shear layer defined by the mean velocity profiles is unchanged by combustion but the virtual origin is shifted downstream. The reacting shear layer based on the mean velocity profiles is shifted toward the recirculation zone and the reattachments lengths are shortened by 30%.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165427
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  • 40
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    Experimental study of the effects of secondary air on the emissions and stability of a lean premixed combustor (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were run using a perforated plate flameholder with a relatively short attached recirculation zone and a vee gutter flameholder with a relatively long attached recirculation zone. Combustor streamlines were traced in cold flow tests at ambient pressure. The amount of secondary air entrainment in the recirculation zones of the flameholders was determined by tracer gas testing at cold flow ambient pressure conditions. Combustion tests were caried out at entrance conditions of 0.5 MPa/630K and emission of NOx, CO and unburned hydrocarbons were measured along with lean stability and flashback limits. The degree of entrainment increases as dilution air injection decreases. Flashback appears to be a function of overall equivalence ratio and resistance to flashback increases with increasing combustor entrance velocity. Lean stability limit appears to be a function of both primary zone and flameholder recirculation zone equivalence ratios and resistance to lean blowout increases with increasing combustor entrance velocity.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165422 , GASL-TR-258
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  • 41
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    Engine health monitoring: An advanced system (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The advanced propulsion monitoring system is described. The system was developed in order to fulfill a growing need for effective engine health monitoring. This need is generated by military requirements for increased performance and efficiency in more complex propulsion systems, while maintaining or improving the cost to operate. This program represents a vital technological step in the advancement of the state of the art for monitoring systems in terms of reliability, flexibility, accuracy, and provision of user oriented results. It draws heavily on the technology and control theory developed for modern, complex, electronically controlled engines and utilizes engine information which is a by-product of such a system.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 357-375
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  • 42
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    Helicopter propulsion system reliability and engine monitoring assessments (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The major short life, unreliable, and high maintenance engine and power components and subsystems in current civil helicopters were identified. Categories included both reciprocating and turbine engines, single and multiple engine configurations, single and tandem trotor vehicles, and light, medium, and heavy helicopters. The major focus was on the following parameters: accident rate data; maintenance rate data; and direct operator input.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 311-322
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  • 43
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    Advanced oxide dispersion strengthened sheet alloys for improved combustor durability (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Burner design modifications that will take advantage of the improved creep and cyclic oxidation resistance of oxide dispersion strengthened (ODS) alloys while accommodating the reduced fatigue properties of these materials were evaluated based on preliminary analysis and life predictions, on construction and repair feasibility, and on maintenance and direct operating costs. Two designs - the film cooled, segmented louver and the transpiration cooled, segmented twin Wall - were selected for low cycle fatigue (LCF) component testing. Detailed thermal and structural analysis of these designs established the strain range and temprature at critical locations resulting in predicted lives of 10,000 cycles for MA 956 alloy. The ODs alloys, MA 956 and HDA 8077, demonstrated a 167 C (300 F) temperature advantage over Hastelloy X alloy in creep strength and oxidation resistance. The MA 956 alloy was selected for mechanical property and component test evaluations. The MA 956 alloy was superior to Hastelloy X in LCF component testing of the film cooled, segmented louver design.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 119-136
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  • 44
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    JT9D jet engine diagnostics program (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Performance deterioration in the JT9D-7 is a flight sensitive phenomenon caused by one short term and two long term wear modes. The short term deterioration occurs primarily during airplane acceptance testing and therefore does not affect airline operation. The long term wear takes place continuously over the engine life so that the performance loss can be minimized by a sound maintenance program. Short term deterioration is primarily due to flight load induced blade and gas path seal wear which result in increased gas path running clearances. The wear occurs in all engine modules but has the most deleterious effect on the low pressure compressor and high pressure turbine performance. The wear occurs during conditions that combine minimum axisymmetric running clearances and maximum engine distortion or asymmetric closure.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Engine Diagnostics; p 43-61
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  • 45
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    Structures performance, benefit, cost-study (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: New technology concepts and structural analysis development needs which could lead to improved life cycle cost for future high-bypass turbofans were studied. The NASA-GE energy efficient engine technology is used as a base to assess the concept benefits. Recommended programs are identified for attaining these generic structural and other beneficial technologies.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165456 , R81AEG393
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  • 46
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    Advanced subsonic transport propulsion (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A brief review of the current NASA Energy Efficient Engine (E(3)) Project is presented. Included in this review are the factors that influenced the design of these turbofan engines and the advanced technology incorporated in them to reduce fuel consumption and improve environmental characteristics. In addition, factors such as the continuing spiral in fuel cost, that could influence future aircraft propulsion systems beyond those represented by the E(3) engines, are also discussed. Advanced technologies that will address these influencing factors and provide viable future propulsion systems are described. The potential importance of other propulsion system types, such as geared fans and turboshaft engines, is presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-82696 , E-979 , Intern. Air Transportation Conf.; Atlantic City, NJ; United States
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  • 47
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    Mechanical properties of turbine blade alloys in hydrogen at elevated temperatures (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The mechanical properties of single crystal turbine blade alloys in a gaseous hydrogen environment were determined. These alloys are proposed for use in space propulsion systems in pure or partial high pressure hydrogen environments at elevated temperatures. Mechanical property tests included: tensile, creep, low fatigue (LCF), and crack growth. Specimens were in both transverse and longitudinal directions relative to the casting solidification direction. Testing was conducted on solid specimens exposed to externally pressurized environments of gaseous hydrogen and hydrogen-enriched steam.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-161842 , FR-14844
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  • 48
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    Entrainment and thrust augmentation in pulsatile ejector flows (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This study comprised direct thrust measurements, flow visualization by use of a spark shadowgraph technique, and mean and fluctuating velocity measurements with a pitot tube and linearized constant temperature hot-wire anemometry respectively. A gain in thrust of as much as 10 to 15% was observed for the pulsatile ejector flow as compared to the steady flow configuration. From the velocity profile measurements, it is concluded that this enhanced augmentation for pulsatile flow as compared to a nonpulsatile one was accomplished by a corresponding increased entrainment by the primary jet flow. It is also concluded that the augmentation and total entrainment by a constant area ejector critically depends upon the inlet geometry of the ejector. Experiments were performed to evaluate the influence of primary jet to ejector area ratio, ejector length, and presence of a diffuser on pulsatile ejector performance.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-164715 , JPL-PUB-81-36
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  • 49
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    Turbojet engine blade damping (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The potentials of various sources of nonaerodynamic damping in engine blading are evaluated through a combination of advanced analysis and testing. The sources studied include material hysteresis, dry friction at shroud and root disk interfaces as well as at platform type external dampers. A limited seris of tests was conducted to evaluate damping capacities of composite materials (B/AL, B/AL/Ti) and thermal barrier coatings. Further, basic experiments were performed on titanium specimens to establish the characteristics of sliding friction and to determine material damping constants J and n. All the tests were conducted on single blades. Mathematical models were develthe several mechanisms of damping. Procedures to apply this data to predict damping levels in an assembly of blades are developed and discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165406 , REPT-R81-91441031
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  • 50
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    End wall flows in rotors and stators of a single stage compressor (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A solution of the flow in the rotor end wall region, including the effects of tip clearance flow, is presented. A method for leakage flow measurement at the tip of a compressor rotor blade is discussed. Measurements are given for a rotor hub wall boundary layer.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-164635 , PSU/TURBO-R81-7
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  • 51
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    Turbine blade tip durability analysis (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An air-cooled turbine blade from an aircraft gas turbine engine chosen for its history of cracking was subjected to advanced analytical and life-prediction techniques. The utility of advanced structural analysis techniques and advanced life-prediction techniques in the life assessment of hot section components are verified. Three dimensional heat transfer and stress analyses were applied to the turbine blade mission cycle and the results were input into advanced life-prediction theories. Shortcut analytical techniques were developed. The proposed life-prediction theories are evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165268 , R81AEG372
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  • 52
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    Cold-air investigation of first stage of 4-1/2-stage, fan drive turbine with average stage-loading factor of 4.66 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The design procedure and the development of the blading geometry for the 4 and 1/2 stage turbine are discussed. Results obtained with the first stage, operated as a single stage turbine, are presented. A free vortex design meets the design requirements without incurring problems such as excessive turning, negative reaction, or high Mach number. Cold air tests of the single stage turbine showed that the turbine developed design work (stage loading factor of 5.26) at an efficiency of 0.86, which was the efficiency predicted by a reference method. The mass flow at this condition was 0.88, which occurred at design speed and a pressure ratio of 1.407, corresponding to a stage loading factor of 4.35. The efficiency at this condition was 0.003 higher than that predicted by the reference method.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1780 , E-461
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  • 53
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    Application of the MNA design method to a nonlinear turbofan engine (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Using nonlinear digital simulation as a representative model of the dynamic operation of the QCSEE turbofan engine, a feedback control system is designed by variable frequency design techniques. Transfer functions are generated for each of five power level settings covering the range of operation from approach power to full throttle (62.5% to 100% full power). These transfer functions are then used by an interactive control system design synthesis program to provide a closed loop feedback control using the multivariable Nyquist array and extensions to multivariable Bode diagrams and Nichols charts.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-163855
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  • 54
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    Cooled variable nozzle radial turbine for rotor craft applications (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An advanced, small 2.27 kb/sec (5 lbs/sec), high temperature, variable area radial turbine was studied for a rotor craft application. Variable capacity cycles including single-shaft and free-turbine engine configurations were analyzed to define an optimum engine design configuration. Parametric optimizations were made on cooled and uncooled rotor configurations. A detailed structural and heat transfer analysis was conducted to provide a 4000-hour life HP turbine with material properties of the 1988 time frame. A pivoted vane and a moveable sidewall geometry were analyzed. Cooling and variable geometry penalties were included in the cycle analysis. A variable geometry free-turbine engine configuration with a design 1477K (2200 F) inlet temperature and a compressor pressure ratio of 16:1 was selected. An uncooled HP radial turbine rotor with a moveable sidewall nozzle showed the highest performance potential for a time weighted duty cycle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165397 , NAS 1.26:165397 , REPT-1759
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  • 55
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    Static noise tests on modified augmentor wing jet STOL research aircraft (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Noise measurements were made to determine if recent modifications made to the bifurcated jetpipe to increase engine thrust had at the same time reduced the noise level. The noise field was measured by a 6-microphone array positioned on a 30.5m (100 ft) sideline between 90 and 150 degrees from the left engine inlet. Noise levels were recorded at three flap angles over a range of engine thrust settings from flight idle to emergency power and plotted in one-third octave band spectra. Little attenuation was observed at maximum power, but significant attenuation was achieved at approach and cruise power levels.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81231 , NAS 1.15:81231
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  • 56
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    Flight evaluation of an engine static pressure noseprobe in an F-15 airplane (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The flight testing of an inlet static pressure probe and instrumented inlet case produced results consistent with sea-level and altitude stand testing. The F-15 flight test verified the basic relationship of total to static pressure ratio versus corrected airflow and automatic distortion downmatch with the engine pressure ratio control mode. Additionally, the backup control inlet case statics demonstrated sufficient accuracy for backup control fuel flow scheduling, and the station 6 manifolded production probe was in agreement with the flight test station 6 tota pressure probes.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-163109 , NAS 1.26:163109 , FR-14915
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  • 57
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    Technology and benefits of aircraft counter rotation propellers (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are reported of a NASA sponsored analytical investigation into the merits of advanced counter rotation propellers for Mach 0.80 commercial transport application. Propeller and gearbox performance, acoustics, vibration characteristics, weight, cost and maintenance requirements for a variety of design parameters and special features were considered. Fuel savings in the neighborhood of 8 percent relative to single rotation configurations are feasible through swirl recovery and lighter gearboxes. This is the net gain which includes a 5 percent acoustic treatment weight penalty to offset the broader frequency spectrum noise produced by counter rotation blading.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-82983 , E-1414 , NAS 1.15:82983
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  • 58
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    Thermal expansion accommodation in a jet engine frame (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Design advancements to enhance stress accommodation in gas turbine engine frames are described. Consideration is given to mechanical stiffness to maintain an adequate spring rate, and to thermal stresses in both ambient and transient modes. Noting that thermal stresses occur due to differing temperatures at different parts of the frame, the matching of the thermal expansion rates of different structural materials is emphasized. Adequate stiffness is necessary to avoid dynamic reactions leading to case cracking as a result of normal imbalances of moving parts. Stress and deflection analysis of a total frame concept using a three-dimensional finite element stress analysis computer program, with modelling of all frame components, is presented, and illustrations are provided.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 59
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    Energy efficient engine, high-pressure turbine cooling model technology report (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two dimensional flow visualization model tests were used to substantiate the flow stability benefits derived from the use of turning vanes in the root and tip turn flow areas. Results indicate the need for corner fillets and flow injection into the acute corner formed by the intersection of the rib and simulated airfoil suction surface in order to minimize recirculation (stagnation) of flow in that region. Three dimensional flow visualization model tests verified the actual blade coolant passage design.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165374 , PWA-5594-159
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  • 60
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    High-response measurements of a turbofan engine during nonrecoverable stall (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: High response measurements of a Pratt and Whitney F100(3) turbofan engine at a simulated Mach number and altitude of 1.2 and 3000 m (10,000 ft) respectively were recorded during a nonrecoverable stall. The nonrecoverable stall occurred as a result of incorrect scheduling of the high compressor variable vanes (RCVV) during an experimental engine control investigation. Recorded data indicates rotating stall originating in the high pressure compressor. From this region the disturbance propagates upstream into the fan and downstream throughout the core compressor. The rotating stall remained in the core compressor until the engine was shutdown. The fan exhibited some rotating stall, but the amplitude of the pressure oscillations were less severe. Data indicates that the fan was able to recover from the stall. Fan turbine inlet temperature (FTIT) had been decreasing until stall developed in the high-pressure compressor. From this time, FTIT increased towards its maximum temperature limit. The rising FTIT during nonrecoverable stall may be the result of incomplete combustion in the combustor and additional combustion occurring through the turbine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81759 , E-822
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  • 61
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    Comparison of NASA and contractor results from aeroacoustic tests of QCSEE OTW engine (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamics and acoustics of the over-the-wing (OTW) Quiet, Clean, Short Haul Experimental Engine (QCSEE) were tested. A boilerplate (nonflight weight), high-throat Mach number, acoustically treated inlet and a D-shaped OTW exhaust nozzle with variable position side doors were used. Some acoustic directivity results for the type "D" nozzle and acoustic effects of variations in the nozzle side door positions are included. It was found that the results are in agreement with those previously obtained.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81761 , E-824
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  • 62
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    Propulsion system study for Small Transport Aircraft Technology (STAT) (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Propulsion system technologies applicable to the generation of commuter airline aircraft expected to enter service in the 1990's are identified and evaluated in terms of their impact on aircraft operating economics and fuel consumption. The most promising technologies in the areas of engine, propeller, gearbox, and nacelle design are recommended for future research. Each item under consideration is evaluated relative to a modern baseline engine, the General Electric CT7-5, in a current technology aircraft flying a fixed range and payload. The analysis is presented for two aircraft sizes (30 and 50 passenger), over a range of mission lengths (100 to 1100 km) and fuel costs ($264 to $396 per cu m).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165330 , R80AEG068
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    Energy efficient engine, low-pressure turbine boundary layer program (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was conducted to investigate development of boundary layers under the influence of velocity distributions simulating the suction side of two state-of-the-art turbine airfoils: a forward loaded airfoil (squared-off design) and an aft loaded airfoil (aft-loaded design). These velocity distributions were simulated in a boundary layer wind tunnel. Detailed measurements of boundary layer mean velocity and turbulence intensity profiles were obtained for an inlet turbulence level of 2.4 percent and an exit Reynolds number of 800,000. Flush-mounted hot film probes identified the boundary layer transition regimes in the adverse pressure gradient regions for both velocity distributions. Wall intermittency data showed good agreement with the correlations of Dhawan and Narasimha for the intermittency factor distribution in transitional flow regimes.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165338 , PWA-5594-141
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  • 64
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    Semi-actuator disk theory for compressor choke flutter (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mathematical anaysis predict the unsteady aerodynamic utilizing semi actuator theory environment for a cascade of airfoils harmonically oscillating in choked flow was developed. A normal shock is located in the blade passage, its position depending on the time dependent geometry, and pressure perturbations of the system. In addition to shock dynamics, the model includes the effect of compressibility, interblade phase lag, and an unsteady flow field upstream and downstream of the cascade. Calculated unsteady aerodynamics were compared with isolated airfoil wind tunnel data, and choke flutter onset boundaries were compared with data from testing of an F100 high pressure compressor stage.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-3426 , FR-12976
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  • 65
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    Design of a V/STOL propulsion system for a large-scale fighter model (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Modifications were made to the existing Large-Scale STOL fighter model to simulate a V/STOL configuration. Modifications include the substitutions of two dimensional lift/cruise exhaust nozzles in the nacelles, and the addition of a third J97 engine in the fuselage to suppy a remote exhaust nozzle simulating a Remote Augmented Lift System. A preliminary design of the inlet and exhaust ducting for the third engine was developed and a detailed design was completed of the hot exhaust ducting and remote nozzle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-166162 , R81AEG257
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  • 66
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    Structures, performance, benefit, cost study (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aircraft engine structures were studied to identify the advanced structural technologies that would provide the most benefits to future aircraft operations. A series of studies identified engine systems with the greatest potential for improvements. Based on these studies, six advanced generic structural concepts were selected and conceptually designed. The benefits of each concept were quantitatively assessed in terms of thrust specific fuel consumption, weight, cost, maintenance cost, fuel burned and direct operating cost plus interest. The probability of success of each concept was also determined. The concepts were ranked and the three most promising were selected for further study which consisted of identifying and comprehensively outlining the advanced technologies required to develop these concepts for aircraft engine application. Analytic, fabrication, and test technology developments are required. The technology programs outlined emphasize the need to provide basic, fundamental understanding of technology to obtain the benefit goals.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165313 , PWA-5706-16
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  • 67
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    Analysis of effect of flameholder characteristics on lean, premixed, partially vaporized fuel-air mixtures quality and nitrogen oxides emissions (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis was conducted of the effect of flameholding devices on the precombustion fuel-air characteristics and on oxides of nitrogen (NOx) emissions for combustion of premixed partially vaporized mixtures. The analysis includes the interrelationships of flameholder droplet collection efficiency, reatomization efficiency and blockage, and the initial droplet size distribution and accounts for the contribution of droplet combustion in partially vaporized mixtures to NOx emissions. Application of the analytical procedures is illustrated and parametric predictions of NOx emissions are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1842 , E-563
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  • 68
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    Top-mounted inlet system feasibility for transonic-supersonic fighter aircraft (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The more salient findings are presented of recent top inlet performance evaluations aimed at assessing the feasibility of top-mounted inlet systems for transonic-supersonic fighter aircraft applications. Top inlet flow field and engine-inlet performance test data show the influence of key aircraft configuration variables-inlet longitudinal position, wing leading-edge extension planform area, canopy-dorsal integration, and variable incidence canards-on top inlet performance over the Mach range of 0.6 to 2.0. Top inlet performance data are compared with those or more conventional inlet/airframe integrations in an effort to assess the viability of top-mounted inlet systems relative to conventional inlet installations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81292 , A-8575
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  • 69
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    Performance deterioration based on simulated aerodynamic loads test, JT9D jet engine diagnostics program (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An engine was specially prepared with extensive instrumentation to monitor performance, case temperatures, and clearance changes. A special loading device was used to apply known loads on the engine by the use of cables placed around the flight inlet. These loads simulated the estimated aerodynamic pressure distributions that occur on the inlet in various segments of a typical airplane flight. Test results indicate that the engine lost 1.3 percent in take-off thrust specific fuel consumption (TSFC) during the course of the test effort. Permanent clearance changes due to the loads accounted for 1.1 percent; increase in low pressure compressor airfoil roughness and thermal distortion in the high pressure turbine accounted for 0.2 percent. Pretest predicted performance loss due to clearance changes was 0.9 percent in TSFC. Therefore, the agreement between measurement and prediction is considered to be excellent.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165297 , PWA-5512-75
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  • 70
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    Propeller propulsion integration, phase 1 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A bibliography was compiled of all readily available sources of propeller analytical and experimental studies conducted during the 1930 through 1960 period. A propeller test stand was developed for the measurement of thrust and torque characteristics of full scale general aviation propellers and installed in the LaRC 30 x 60 foot full scale wind tunnel. A tunnel entry was made during the January through February 1980 period. Several propellers were tested, but unforseen difficulties with the shaft thrust torque balance severely degraded the data quality.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-163921 , MSSU-EIRS-ASE-81-4
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  • 71
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    Energy efficient engine. Core engine bearings, drives and configuration: Detailed design report (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The detailed design of the forward and aft sumps, the accessory drive system, the lubrication system, and the piping/manifold configuration to be employed in the core engine test of the Energy Efficient Engine is addressed. The design goals for the above components were established based on the requirements of the test cell engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165376 , NAS 1.26:165376 , R81AEG307
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  • 72
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    Energy efficient engine high-pressure turbine single crystal vane and blade fabrication technology report (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective of the High-Pressure Turbine Fabrication Program was to demonstrate the application and feasibility of Pratt & Whitney Aircraft-developed two-piece, single crystal casting and bonding technology on the turbine blade and vane configurations required for the high-pressure turbine in the Energy Efficient Engine. During the first phase of the program, casting feasibility was demonstrated. Several blade and vane halves were made for the bonding trials, plus solid blades and vanes were successfully cast for materials evaluation tests. Specimens exhibited the required microstructure and chemical composition. Bonding feasibility was demonstrated in the second phase of the effort. Bonding yields of 75 percent for the vane and 30 percent for the blade were achieved, and methods for improving these yield percentages were identified. A bond process was established for PWA 1480 single crystal material which incorporated a transient liquid phase interlayer. Bond properties were substantiated and sensitivities determined. Tooling die materials were identified, and an advanced differential thermal expansion tooling concept was incorporated into the bond process.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165400 , NAS 1.26:165400 , PWA-5594-152
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  • 73
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    Energy efficient engine low-pressure compressor component test hardware detailed design report (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic and mechanical design description of the low pressure compressor component of the Energy Efficient Engine were used. The component was designed to meet the requirements of the Flight Propulsion System while maintaining a low cost approach in providing a low pressure compressor design for the Integrated Core/Low Spool test required in the Energy Efficient Engine Program. The resulting low pressure compressor component design meets or exceeds all design goals with the exception of surge margin. In addition, the expense of hardware fabrication for the Integrated Core/Low Spool test has been minimized through the use of existing minor part hardware.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165354 , NAS 1.26:165354 , PWA-5594-157
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  • 74
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    Aerodynamic evaluation of circulation control propellers (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic compatibility of fixed-pitch circulation-control (CC) propellers with the performance characteristics and requirements of a 1600 kg (3600 lb) single-engine variable-pitch propeller general aviation airplane was evaluated. The initial results with elliptical-shaped CC airfoils indicated that the feasibility of application to fixed-pitch propellers was doubtful for the class of airplane investigated (cruise speed of about 300 km/hr) and improbable for higher-speed airplanes. Supplemental data for a cambered circulation-control supercritical airfoil, which became available after completion of the initial evaluation, were subsequently analyzed and are included in the Addendum to this report. With the much superior aerodynamic characteristics of the CC-supercritical airfoil, elimination of variable pitch appears aerodynamically feasible for low-speed airplanes through the use of a moderate amount of upper-surface blowing near the trailing edge during cruise. Overall feasibility depends upon results of structural and systems-type analyses.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165748 , NAS 1.26:165748
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  • 75
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    Energy efficient engine fan component detailed design report (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The fan component which was designed for the energy efficient engine is an advanced high performance, single stage system and is based on technology advancements in aerodynamics and structure mechanics. Two fan components were designed, both meeting the integrated core/low spool engine efficiency goal of 84.5%. The primary configuration, envisioned for a future flight propulsion system, features a shroudless, hollow blade and offers a predicted efficiency of 87.3%. A more conventional blade was designed, as a back up, for the integrated core/low spool demonstrator engine. The alternate blade configuration has a predicted efficiency of 86.3% for the future flight propulsion system. Both fan configurations meet goals established for efficiency surge margin, structural integrity and durability.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165466 , NAS 1.26:165466 , PWA-5594-165
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  • 76
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    Study of controlled diffusion stator blading. 1. Aerodynamic and mechanical design report (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Pratt & Whitney Aircraft is conducting a test program for NASA in order to demonstrate that a controlled-diffusion stator provides low losses at high loadings and Mach numbers. The technology has shown great promise in wind tunnel tests. Details of the design of the controlled diffusion stator vanes and the multiple-circular-arc rotor blades are presented. The stage, including stator and rotor, was designed to be suitable for the first-stage of an advanced multistage, high-pressure compressor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165500 , PWA-5698-28
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  • 77
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    Research and development program for non-linear structural modeling with advanced time-temperature dependent constitutive relationships (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results of a 20-month research and development program for nonlinear structural modeling with advanced time-temperature constitutive relationships are reported. The program included: (1) the evaluation of a number of viscoplastic constitutive models in the published literature; (2) incorporation of three of the most appropriate constitutive models into the MARC nonlinear finite element program; (3) calibration of the three constitutive models against experimental data using Hastelloy-X material; and (4) application of the most appropriate constitutive model to a three dimensional finite element analysis of a cylindrical combustor liner louver test specimen to establish the capability of the viscoplastic model to predict component structural response.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165533 , PWA-5700-50
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  • 78
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    Energy efficient engine shroudless, hollow fan blade technology report (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Shroudless, Hollow Fan Blade Technology program was structured to support the design, fabrication, and subsequent evaluation of advanced hollow and shroudless blades for the Energy Efficient Engine fan component. Rockwell International was initially selected to produce hollow airfoil specimens employing the superplastic forming/diffusion bonding (SPF/DB) fabrication technique. Rockwell demonstrated that a titanium hollow structure could be fabricated utilizing SPF/DB manufacturing methods. However, some problems such as sharp internal cavity radii and unsatisfactory secondary bonding of the edge and root details prevented production of the required quantity of fatigue test specimens. Subsequently, TRW was selected to (1) produce hollow airfoil test specimens utilizing a laminate-core/hot isostatic press/diffusion bond approach, and (2) manufacture full-size hollow prototype fan blades utilizing the technology that evolved from the specimen fabrication effort. TRW established elements of blade design and defined laminate-core/hot isostatic press/diffusion bonding fabrication techniques to produce test specimens. This fabrication technology was utilized to produce full size hollow fan blades in which the HIP'ed parts were cambered/twisted/isothermally forged, finish machined, and delivered to Pratt & Whitney Aircraft and NASA for further evaluation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165586 , NAS 1.26:165586 , PWA-5594-199
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  • 79
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    Aeroelastic characteristics of a cascade of mistuned blades in subsonic and supersonic flows (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: An investigation of the effects of mistuning on flutter and forced response of a cascade in subsonic and supersonic flows is presented. The aerodynamic and structural coupling between the bending and torsional motions and the aerodynamic coupling between the blades are included. It is shown that frequency mistuning always has a beneficial effect on flutter. Additionally, the results indicate that frequency mistuning may have either a beneficial or an adverse effect on forced response, depending on the engine order of the excitation and Mach number.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 81-DET-122 , American Society of Mechanical Engineers, Design Engineering Technical Conference; Sept. 20-23, 1981; Hartford, CT
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  • 80
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    Simplified off-design performance model of a day turbofan engine cycle (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The specific thrust and fuel-air ratio for a dry turbofan engine cycle were calculated for several power levels over a range of altitudes and Mach numbers. The engine has a design fan pressure ratio of 2.9, compressor pressure ratio of 8.0, and bypass ratio of 0.6. Nominal engine component curves were picked to approximate the calculated data to construct a simplified model of the off-design performance of the engine. The model was then used to construct a simplified design-point engine model for the full-power condition.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-83204
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  • 81
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    Study of an engine flow diverter system for a large scale ejector powered aircraft model (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Requirements were established for a conceptual design study to analyze and design an engine flow diverter system and to include accommodations for an ejector system in an existing 3/4 scale fighter model equipped with YJ-79 engines. Model constraints were identified and cost-effective limited modification was proposed to accept the ejectors, ducting and flow diverter valves. Complete system performance was calculated and a versatile computer program capable of analyzing any ejector system was developed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-166163
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  • 82
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    Blade loss transient dynamics analysis. Volume 3: User's manual for TETRA program (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The users manual for TETRA contains program logic, flow charts, error messages, input sheets, modeling instructions, option descriptions, input variable descriptions, and demonstration problems. The process of obtaining a NASTRAN 17.5 generated modal input file for TETRA is also described with a worked sample.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165373-VOL-3 , R81AEG381-VOL-3
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  • 83
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    Blade loss transient dynamics analysis, volume 2. Task 2: Theoretical and analytical development. Task 3: Experimental verification (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The component element method was used to develop a transient dynamic analysis computer program which is essentially based on modal synthesis combined with a central, finite difference, numerical integration scheme. The methodology leads to a modular or building-block technique that is amenable to computer programming. To verify the analytical method, turbine engine transient response analysis (TETRA), was applied to two blade-out test vehicles that had been previously instrumented and tested. Comparison of the time dependent test data with those predicted by TETRA led to recommendations for refinement or extension of the analytical method to improve its accuracy and overcome its shortcomings. The development of working equations, their discretization, numerical solution scheme, the modular concept of engine modelling, the program logical structure and some illustrated results are discussed. The blade-loss test vehicles (rig full engine), the type of measured data, and the engine structural model are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165373-VOL-2 , R81AEG381-VOL-2
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  • 84
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    Blade loss transient dynamics analysis, volume 1. Task 1: Survey and perspective (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analytical technique was developed to predict the behavior of a rotor system subjected to sudden unbalance. The technique is implemented in the Turbine Engine Transient Rotor Analysis (TETRA) computer program using the component element method. The analysis was particularly aimed toward blade-loss phenomena in gas turbine engines. A dual-rotor, casing, and pylon structure can be modeled by the computer program. Blade tip rubs, Coriolis forces, and mechanical clearances are included. The analytical system was verified by modeling and simulating actual test conditions for a rig test as well as a full-engine, blade-release demonstration.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165373-VOL-1 , R81AEG381-VOL-1
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  • 85
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    Two-stage combustion for reducing pollutant emissions from gas turbine combustors (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Combustion and emission results are presented for a premix combustor fueled with admixtures of JP5 with neat H2 and of JP5 with simulated partial-oxidation product gas. The combustor was operated with inlet-air state conditions typical of cruise power for high performance aviation engines. Ultralow NOx, CO and HC emissions and extended lean burning limits were achieved simultaneously. Laboratory scale studies of the non-catalyzed rich-burning characteristics of several paraffin-series hydrocarbon fuels and of JP5 showed sooting limits at equivalence ratios of about 2.0 and that in order to achieve very rich sootless burning it is necessary to premix the reactants thoroughly and to use high levels of air preheat. The application of two-stage combustion for the reduction of fuel NOx was reviewed. An experimental combustor designed and constructed for two-stage combustion experiments is described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-163877 , JPL-PUB-80-63
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  • 86
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    Flight evaluation of a simplified gross thrust calculation technique using an F100 turbofan engine in an F-15 airplane (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A simplified gross thrust calculation technique was evaluated in flight tests on an F-15 aircraft using prototype F100-PW-100 engines. The technique relies on afterburner duct pressure measurements and empirical corrections to an ideal one-dimensional analysis to determine thrust. In-flight gross thrust calculated by the simplified method is compared to gross thrust calculated by the engine manufacturer's gas generator model. The evaluation was conducted at Mach numbers from 0.6 to 1.5 and at altitudes from 6000 meters to 13,700 meters. The flight evaluation shows that the simplified gross thrust method and the gas generator method agreed within plus or minus 3 percent. The discrepancies between the data generally fell within an uncertainty band derived from instrumentation errors and recording system resolution.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1782 , H-1118
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  • 87
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    Analysis of high load dampers (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: High load damping requirements for modern jet engines are discussed. The design of damping systems which could satisfy these requirements is also discusseed. In order to evaluate high load damping requirements, engines in three major classes were studied; large transport engines, small general aviation engines, and military engines. Four damper concepts applicable to these engines were evaluated; multi-ring, cartridge, curved beam, and viscous/friction. The most promising damper concept was selected for each engine and performance was assessed relative to conventional dampers and in light of projected damping requirements for advanced jet engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165503 , NAS 1.26:165503 , PWA-5779-10
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  • 88
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    Exhaust emissions survey of a turbofan engine for flame holder swirl type augmentors at simulated altitude flight conditions (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Emissions of carbon dioxide, total oxides of nitrogen, unburned hydrocarbons, and carbon monoxide from an F100 afterburning two spool turbofan engine at simulated flight conditions are reported. Tests were run at Mach 0.8 at altitudes of 10.97 and 13.71 km (36,000 and 45,000 ft), and at Mach 1.2 at 13.71 km (45,000 ft). Emission measurements were made from intermediate power (nonafterburning) through maximum afterburning, using a single point gas sample probe traversed across the horizontal diameter of the exhaust nozzle. The data show that emissions vary with flight speed, altitude, power level, and radial position across the nozzle. Carbon monoxide emissions were low for intermediate and partial afterburning power. Unburned hydrocarbons were near zero for most of the simulated flight conditions. At maximum afterburning, there were regions of NOx deficiency in regions of high CO. The results suggest that the low NOx levels observed in the tests are a result of interaction with high CO in the thermal converter. CO2 emissions were proportional to local fuel air ratio for all test conditions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-82787 , E-955 , NAS 1.15:82787
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  • 89
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    Energy Efficient Engine Exhaust Mixer Model Technology (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An exhaust mixer test program was conducted to define the technology required for the Energy Efficient Engine Program. The model configurations of 1/10 scale were tested in two phases. A parametric study of mixer design options, the impact of residual low pressure turbine swirl, and integration of the mixer with the structural pylon of the nacelle were investigated. The improvement of the mixer itself was also studied. Nozzle performance characteristics were obtained along with exit profiles and oil smear photographs. The sensitivity of nozzle performance to tailpipe length, lobe number, mixer penetration, and mixer modifications like scalloping and cutbacks were established. Residual turbine swirl was found detrimental to exhaust system performance and the low pressure turbine system for Energy Efficient Engine was designed so that no swirl would enter the mixer. The impact of mixer/plug gap was also established, along with importance of scalloping, cutbacks, hoods, and plug angles on high penetration mixers.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165459 , NAS 1.26:165459 , PWA-5594-164
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  • 90
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    Advanced Low-Emissions Catalytic-Combustor Program, phase 1 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Six catalytic combustor concepts were defined, analyzed, and evaluated. Major design considerations included low emissions, performance, safety, durability, installations, operations and development. On the basis of these considerations the two most promising concepts were selected. Refined analysis and preliminary design work was conducted on these two concepts. The selected concepts were required to fit within the combustor chamber dimensions of the reference engine. This is achieved by using a dump diffuser discharging into a plenum chamber between the compressor discharge and the turbine inlet, with the combustors overlaying the prediffuser and the rear of the compressor. To enhance maintainability, the outer combustor case for each concept is designed to translate forward for accessibility to the catalytic reactor, liners and high pressure turbine area. The catalytic reactor is self-contained with air-cooled canning on a resilient mounting. Both selected concepts employed integrated engine-starting approaches to raise the catalytic reactor up to operating conditions. Advanced liner schemes are used to minimize required cooling air. The two selected concepts respectively employ fuel-rich initial thermal reaction followed by rapid quench and subsequent fuel-lean catalytic reaction of carbon monoxide, and, fuel-lean thermal reaction of some fuel in a continuously operating pilot combustor with fuel-lean catalytic reaction of remaining fuel in a radially-staged main combustor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159656 , NAS 1.26:159656 , PWA-5589-19 , ESL-TR-79-23
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    NASA TECHNICAL REPORTS
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    Optimization of thrust algorithm calibration for Computing System (TCS) for Thrust the NASA Highly Maneuverable Aircraft Technology (HiMAT) vehicle's propulsion system (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A simplified gross thrust computing technique for the HiMAT J85-GE-21 engine using altitude facility data was evaluated. The results over the full engine envelope for both the standard engine mode and the open nozzle engine mode are presented. Results using afterburner casing static pressure taps are compared to those using liner static pressure taps. It is found that the technique is very accurate for both the standard and open nozzle engine modes. The difference in the algorithm accuracy for a calibration based on data from one test condition was small compared to a calibration based on data from all of the test conditions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-163121 , NAS 1.26:163121 , A011/FR
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    NASA TECHNICAL REPORTS
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    Effects of fan inlet temperature disturbances on the stability of a turbofan engine (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of steady-state and time-dependent fan inlet total temperature disturbances on the stability of a TF30-P-3 turbofan engine were determined. Disturbances were induced by a gaseous-hydrogen-fueled burner system installed upstream of the fan inlet. Data were obtained at a fan inlet Reynolds number index of 0.50 and at a low-pressure-rotor corrected speed of 90 percent of military speed. All tests were conducted with a 90 deg extent of the fan inlet circumference exposed to above-average temperatures.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-82699 , E-982
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    NASA TECHNICAL REPORTS
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    Energy efficient engine sector combustor rig test program (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Under the NASA-sponsored Energy Efficient Engine program, Pratt & Whitney Aircraft has successfully completed a comprehensive combustor rig test using a 90-degree sector of an advanced two-stage combustor with a segmented liner. Initial testing utilized a combustor with a conventional louvered liner and demonstrated that the Energy Efficient Engine two-stage combustor configuration is a viable system for controlling exhaust emissions, with the capability to meet all aerothermal performance goals. Goals for both carbon monoxide and unburned hydrocarbons were surpassed and the goal for oxides of nitrogen was closely approached. In another series of tests, an advanced segmented liner configuration with a unique counter-parallel FINWALL cooling system was evaluated at engine sea level takeoff pressure and temperature levels. These tests verified the structural integrity of this liner design. Overall, the results from the program have provided a high level of confidence to proceed with the scheduled Combustor Component Rig Test Program.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-167913 , NAS 1.26:167913 , PWA-5594-180
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    NASA TECHNICAL REPORTS
  • 94
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    Thrust reverser for a long duct fan engine (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A bypass duct outer cowl includes a fixed cascade disposed between axially spaced fixed cowl portions and a translatable cowl sleeve and blocker doors movably disposed on the respective radially outer and inner sides of the cascade. Actuation and linkage structure located entirely within the outer cowl provides for selectively moving the cowl sleeve rearwardly and rotating the blocker doors to a position across the bypass duct to cause the fan airflow to pass through the cascade in a thrust reversing manner.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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    Experimental program for the evaluation of turbofan/turboshaft c conversion technology (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A TF34 turbofan engine is being modified to produce shaft power from an output coupling on the fan disk when variable inlet guide vanes are closed to reduce fan airflow. The engine, called a convertible engine, could be used on advanced rotorcraft such as X-wing, ABC (Advanced Blade Concept), and Folding Tilt Rotor, and on V/STOL craft in which two engines are cross-coupled. The engine will be tested on an outdoor static test stand at NASA Lewis Research Center. Steady-state tests will be made to measure performance in turbofan, turboshaft, and combined power output modes. Transient tests will be made to determine the response to the engine and a new digital engine control system for several types of rapid changes in thrust and shaft loads. The paper describes the engine modifications, the test facility equipment, proposed testing techniques for several types of tests, and typical test results predicted from engine performance computer programs.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-82988 , E-1420 , NAS 1.15:82988 , AHS-RWP-19 , AD-A233790 , Rotary Wing Propulsion System Specialist Meeting; Nov 16, 1982 - Nov 18, 1982; Williamsburg, VA; United States
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    Army/NASA small turboshaft engine digital controls research program (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The emphasis of a program to conduct digital controls research for small turboshaft engines is on engine test evaluation of advanced control logic using a flexible microprocessor based digital control system designed specifically for research on advanced control logic. Control software is stored in programmable memory. New control algorithms may be stored in a floppy disk and loaded directly into memory. This feature facilitates comparative evaluation of different advanced control modes. The central processor in the digital control is an Intel 8086 16 bit microprocessor. Control software is programmed in assembly language. Software checkout is accomplished prior to engine test by connecting the digital control to a real time hybrid computer simulation of the engine. The engine currently installed in the facility has a hydromechanical control modified to allow electrohydraulic fuel metering and VG actuation by the digital control. Simulation results are presented which show that the modern control reduces the transient rotor speed droop caused by unanticipated load changes such as cyclic pitch or wind gust transients.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-82979 , E-1408 , NAS 1.15:82979 , AVRADCOM-TR-82-C-14 , AHS-RWP-7 , Rotary Wing Propulsion System Specialist Meeting; Nov 16, 1982 - Nov 18, 1982; Williamsburg, VA; United States
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    Analysis, design, fabrication and testing of an optical tip clearance sensor (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Analyses and the design, fabrication, and testing of an optical tip clearance sensor with intended application in aircraft propulsion control systems are reported. The design of a sensor test rig, evaluation of optical sensor components at elevated temperatures, sensor design principles, sensor test results at room temperature, and estimations of sensor accuracy at temperatures of an aircraft engine environment are discussed. Room temperature testing indicated possible measurement accuracies of less than 12.7 microns (0.5 mils). Ways to improve performance at engine operating temperatures are recommended. The potential of this tip clearance sensor is assessed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165265 , NAS 1.26:165265 , R81AEG215
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    NASA TECHNICAL REPORTS
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    Application of computer generated color graphic techniques to the processing and display of three dimensional fluid dynamic data (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: (Previously announced in STAR as N81-29782)
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Computers in flow predictions and fluid dynamics experiments; Nov 15, 1981 - Nov 20, 1981; Washington, DC
    Format: text
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  • 99
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    Measurement of aerodynamic work during fan flutter (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: (Previously announced in STAR as N81-25080)
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Fluid/structure interactions in turbomachinery; Nov 15, 1981 - Nov 20, 1981; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 100
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    Advanced subsonic transport propulsion (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Examination of future subsonic commercial aircraft propulsion trends begins with a brief review of the current NASA Energy Efficient Engine (E3) Project. Included in this review are the factors that influenced the design of these turbofan engines and the advanced technology incorporated in them to reduce fuel consumption and improve environmental characteristics. In addition, factors such as the continuing spiral in fuel cost, that could influence future aircraft propulsion systems beyond those represented by the E3 engines, are also discussed. Advanced technologies that will address these influencing factors and provide viable future propulsion systems are described. And finally, the potential importance of other propulsion system types, such as geared fans and turboshaft engines, is presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 81-0811 , International Air Transportation Conference; May 26, 1981 - May 28, 1981; Atlantic City, NJ
    Format: text
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    NASA TECHNICAL REPORTS
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