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  • Other Sources  (1,065)
  • AIRCRAFT PROPULSION AND POWER  (1,065)
  • 2020-2024
  • 2020-2020
  • 1980-1984  (1,052)
  • 1945-1949  (13)
  • 101
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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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  • 102
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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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  • 103
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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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  • 104
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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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  • 105
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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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  • 106
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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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  • 107
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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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  • 108
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    VCE test bed engine for supersonic cruise research (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Various design concepts for a variable cycle engine applicable to a supersonic, mixed mission propulsion system which would combine the merits of a turbofan at subsonic operating conditions with those of a turbojet for supersonic operating conditions are briefly examined. In particular the integration of the variable area bypass injector with the core driven (aft fan block) fan stage is discussed and the technical benefits of the configuration are summarized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Supersonic Cruise Res. 1979, Pt. 1; p 347-356
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  • 109
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    Control technology for future aircraft propulsion systems (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The need for a more sophisticated engine control system is discussed. The improvements in better thrust-to-weight ratios demand the manipulation of more control inputs. New technological solutions to the engine control problem are practiced. The digital electronic engine control (DEEC) system is a step in the evolution to digital electronic engine control. Technology issues are addressed to ensure a growth in confidence in sophisticated electronic controls for aircraft turbine engines. The need of a control system architecture which permits propulsion controls to be functionally integrated with other aircraft systems is established. Areas of technology studied include: (1) control design methodology; (2) improved modeling and simulation methods; and (3) implementation technologies. Objectives, results and future thrusts are summarized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-14 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 231-247
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  • 110
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    Airstart performance of a digital electronic engine control system on an F100 engine (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The digital electronic engine control (DEEC) system installed on an F100 engine in an F-15 aircraft was tested. The DEEC system incorporates a closed-loop air start feature in which the fuel flow is modulated to achieve the desired rate of compressor acceleration. With this logic the DEEC equipped F100 engine can achieve air starts over a larger envelope. The DEEC air start logic, the test program conducted on the F-15, and its results are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-8 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 127-139
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  • 111
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    The dynamics of a flexible bladed disc on a flexible rotor in a two-rotor system (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the development of the analysis of the transient dynamic response of a bladed disk on a flexible rotor. The rotating flexible bladed disk is considered as a module in a complete turbine engine structure. The analysis of the flexible bladed disk (FBD) module is developed for the non-equilibrated one-diameter axial mode. The FBD motion is considered as a sum of two standing axial waves constrained to the rotor. The FBD is coupled inertially and gyroscopically to its rotor support, and indirectly through connecting elements, to the adjacent rotor and/or other supporting structures. Incorporated in the basic Turbine Engine Transient Response Analysis program (TETRA), the FBD module is demonstrated with a two-rotor model where the FBD can be excited into resonance by an unbalance in the adjacent rotor and at a frequency equal to the differential rotor speed. The FBD module also allows the analysis of two flexible bladed disks in the same rotor.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 112
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    Aeroelastic formulations for turbomachines and propellers (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The task of the aeroelastic analysis is to combine the formulations of the structural dynamic and unsteady aerodynamic models in a consistent manner, to solve the resulting aeroelastic model to determine the dynamic behavior (e.g., stability, forced vibration), and to interpret those results for both qualitative trends, and quantitative detail. A review of the various formulations of the aeroelastic problem and a comparison of their relative advantages will be the subject of this paper. Specifically, the topics to be addressed are: the formulation of the aeroelastic problem, including a summary of the relations necessary to transform various diverse structural and aerodynamic models to a consistent notation for oscillatory motion; an approximate transformation for arbitrary temporal behavior; and a brief review of the applicable solution techniques.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 113
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    Real-time in-flight thrust calculation on a digital electronic engine control-equipped F100 engine in an F-15 airplane (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Computer algorithms which calculate in-flight engine and aircraft performance real-time are discussed. The first step was completed with the implementation of a real-time thrust calculation program on a digital electronic engine control (DEEC) equiped F100 engine in an F-15 aircraft. The in-flight thrust modifications that allow calculations to be performed in real-time, to compare results to predictions, are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-13 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 231-247
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  • 114
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    Augmentor transient capability of an F100 engine equipped with a digital electronic engine control (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An F100 augmented turbofan engine equipped with digital electronic engine control (DEEC) system was evaluated. The engine was equipped with a specially modified augmentor to provide improved steady state and transient augmentor capability. The combination of the DEEC and the modified augmentor was evaluated in sea level and altitude facility tests and then in four different flight phases in an F-15 aircraft. The augmentor configuration, logic, and test results are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-11 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 171-199
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  • 115
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    Digital electronic engine control fault detection and accommodation flight evaluation (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The capabilities and performance of various fault detection and accommodation (FDA) schemes in existing and projected engine control systems were investigated. Flight tests of the digital electronic engine control (DEEC) in an F-15 aircraft show discrepancies between flight results and predictions based on simulation and altitude testing. The FDA methodology and logic in the DEEC system, and the results of the flight failures which occurred to date are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-7 , Digital Electronic Engine Control (DEEC) Flight Evaluation in n F-15 Airplane; p 107-126
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  • 116
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    Flight testing the digital electronic engine control in the F-15 airplane (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The digital electronic engine control (DEEC) is a full-authority digital engine control developed for the F100-PW-100 turbofan engine which was flight tested on an F-15 aircraft. The DEEC hardware and software throughout the F-15 flight envelope was evaluated. Real-time data reduction and data display systems were implemented. New test techniques and stronger coordination between the propulsion test engineer and pilot were developed which produced efficient use of test time, reduced pilot work load, and greatly improved quality data. The engine pressure ratio (EPR) control mode is demonstrated. It is found that the nonaugmented throttle transients and engine performance are satisfactory.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-6 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 91-105
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  • 117
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    Investigation of a nozzle instability on an F100 engine equipped with a digital electronic engine control (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An instability in the nozzle of the F100 engine, equipped with a digital electronic engine control (DEEC), was observed during a flight evaluation on an F-15 aircraft. The instability occurred in the upper left hand corner (ULMC) of the flight envelope during augmentation. The instability was not predicted by stability analysis, closed-loop simulations of the the engine, or altitude testing of the engine. The instability caused stalls and augmentor blowouts. The nozzle instability and the altitude testing are described. Linear analysis and nonlinear digital simulation test results are presented. Software modifications on further flight test are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-12 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 201-214
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  • 118
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    Effects of inlet distortion on a static pressure probe mounted on the engine hub in an F-15 airplane (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Problems encountered in obtaining good engine face pressure data were studied. A single static measurement located upstream of the engine hub in the stream flow was found to provide a pressure signal suitable for engine control. Two identical probes for measuring fan inlet static (PS2) pressure were designed and mounted on the hub of the left F100-PW-100 turbofan engine installed in the F-15 test aircraft for flight evaluation. The probe is used as a static pressure sensor for a digital engine control system.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-5 , Digital Electronic Engine Control Flight Evaluation in an F-15 Airplane; p 73-89
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  • 119
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    F-15 digital electronic engine control system description (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A digital electronic engine control (DEEC) was developed for use on the F100-PW-100 turbofan engine. This control system has full authority control, capable of moving all the controlled variables over their full ranges. The digital computational electronics and fault detection and accomodation logic maintains safe engine operation. A hydromechanical backup control (BUC) is an integral part of the fuel metering unit and provides gas generator control at a reduced performance level in the event of an electronics failure. The DEEC's features, hardware, and major logic diagrams are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-3 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 33-53
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  • 120
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    Digital electronic engine control history (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Full authority digital electronic engine controls (DEECs) were studied, developed, and ground tested because of projected benefits in operability, improved performance, reduced maintenance, improved reliability, and lower life cycle costs. The issues of operability and improved performance, however, are assessed in a flight test program. The DEEC on a F100 engine in an F-15 aircraft was demonstrated and evaluated. The events leading to the flight test program are chronicled and important management and technical results are identified.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-2 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 15-31
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  • 121
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    Advanced turboprop vibratory characteristics (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The assembly of SR5 advanced turboprop blades to develop a structural dynamic data base for swept props is reported. Steady state blade deformation under centrifugal loading and vibratory characteristics of the rotor assembly were measured. Vibration was induced through a system of piezoelectric crystals attached to the blades. Data reduction procedures are used to provide deformation, mode shape, and frequencies of the assembly at predetermined speeds.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-174708 , NAS 1.26:174708 , R84-956627-1
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  • 122
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    Low-cost single-crystal turbine blades, volume 2 (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The overall objectives of Project 3 were to develop the exothermic casting process to produce uncooled single-crystal (SC) HP turbine blades in MAR-M 247 and higher strength derivative alloys and to validate the materials process and components through extensive mechanical property testing, rig testing, and 200 hours of endurance engine testing. These Program objectives were achieved. The exothermic casting process was successfully developed into a low-cost nonproperietary method for producing single-crystal castings. Single-crystal MAR-M 247 and two derivatives DS alloys developed during this project, NASAIR 100 and SC Alloy 3, were fully characterized through mechanical property testing. SC MAR-M 247 shows no significant improvement in strength over directionally solidified (DS) MAR-M 247, but the derivative alloys, NASAIR 100 and Alloy 3, show significant tensile and fatigue improvements. Firtree testing, holography, and strain-gauge rig testing were used to determine the effects of the anisotropic characteristics of single-crystal materials. No undesirable characteristics were found. In general, the single-crystal material behaved similarly to DS MAR-M 247. Two complete engine sets of SC HP turbine blades were cast using the exothermic casting process and fully machined. These blades were successfully engine-tested.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-174652 , NAS 1.26:174652 , G-21-4314-2
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  • 123
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    On optimal design for the blade-root/hub interface in jet engines (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two major problems identified with the design of the blade-root/hub interface are discussed. The first is the so-called friction contact problem which has two special features: unilateral contact and Coulomb's friction. One of the difficulties in this problem is that the portions of contact and sticking/sliding surfaces are not known a priori. The second is the shape optimization problem which is characterized either by the minimization of the maximum contact pressure or by the minimization of the equivalent stress on the boundary. Design variables are the shapes of the blade-root and the hub. It is noted that friction contact and shape optimization problems are strongly coupled in the present design problem.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 14 p
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  • 124
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    Optimization of cascade blade mistuning under flutter and forced response constraints (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the development of modern turbomachinery, problems of flutter instabilities and excessive forced response of a cascade of blades that were encountered have often turned out to be extremely difficult to eliminate. The study of these instabilities and the forced response is complicated by the presence of mistuning; that is, small differences among the individual blades. The theory of mistuned cascade behavior shows that mistuning can have a beneficial effect on the stability of the rotor. This beneficial effect is produced by the coupling between the more stable and less stable flutter modes introduced by mistuning. The effect of mistuning on the forced response can be either beneficial or adverse. Kaza and Kielb have studied the effects of two types of mistuning on the flutter and forced response: alternate mistuning where alternte blades are identical and random mistuning. The objective is to investigate other patterns of mistuning which maximize the beneficial effects on the flutter and forced response of the cascade. Numerical optimization techniques are employed to obtain optimal mistuning patterns. The optimization program seeks to minimize the amount of mistuning required to satisfy constraints on flutter speed and forced response.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Recent Experiences in Multidisciplinary Analysis and Optimization, Part 1; 15 p
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  • 125
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    Mechanical behavior of thermal barrier coatings for gas turbine blades (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Plasma-sprayed thermal barrier coatings (TBCs) will enable turbine components to operate at higher temperatures and lower cooling gas flow rates; thereby improving their efficiency. Future developments are limited by precise knowledge of the material properties and failure mechanisms of the coating system. Details of this nature are needed for realistic modeling of the coating system which will, in turn, promote advancements in coating technology. Complementary experiments and analytical modeling which were undertaken in order to define and measure the important failure processes for plasma-sprayed coatings are presented. The experimental portion includes two different tests which were developed to measure coating properties. These are termed tensile adhesion and acoustic emission tests. The analytical modeling section details a finite element method which was used to calculate the stress distribution in the coating system. Some preliminary results are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Engine Hot Section Technology, 1984; 12 p
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  • 126
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    Turbine Airfoil Deposition Models (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Gas turbine failures associated with sea-salt ingestion and sulfur-containing fuel impurities have directed attention to alkali sulfate deposition and the associated hot corrosion of gas turbine (GT) blades under some GT operating conditions. These salt deposits form thin, molten films which undermine the protective metal oxide coating normally found on GT blades. The prediction of molten salt deposition, flow and oxide dissolution, and their effects on the lifetime of turbine blades are examined. Goals include rationalizing and helping to predict corrosion patterns on operational GT rotor blades and stators, and ultimately providing some of the tools required to design laboratory simulators and future corrosion-resistant high-performance engines. Necessary background developments are reviewed first, and then recent results and tentative conclusions are presented along with a brief account of the present research plans.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Engine Hot Section Technology, 1984; 22 p
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  • 127
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    Response of a small-turboshaft-engine compression system to inlet temperature distortion (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted into the response of a small-turboshaft-engine compression system to steady-state and transient inlet temperature distortions. Transient temperature ramps range from less than 100 K/sec to above 610 K/sec and generated instantaneous temperatures to 420 K above ambient. Steady-state temperature distortion levels were limited by the engine hardware temperature list. Simple analysis of the steady-state distortion data indicated that a particle separator at the engine inlet permitted higher levels of temperature distortion before onset of compressor surge than would be expected without the separator.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-83765 , E-2198 , NAS 1.26:83765 , USAAVSCOM-TR-84-C-13
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  • 128
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    Channel flow modeling of impingement cooling of a rotating turbine blade (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Local heat transfer distributions in impingement cooling have been measured by Kreatsoulas and Prieser for a range of conditions which model those in actual turbine blades, including the effects of rotation. These data were reported as local Nusselt numbers, but referred to coolant supply conditions. By means of a channel flow modeling of the flow in the supply and impingement passages, the same data are here presented in terms of local Nusselt number distributions such as are used in design. The results in this form are compared to the nonrotating impingement results of Chupp and to the rotating but nonimpingement results of Morris. Rotation reduces the mean Nusselt numbers from these found by Chupp by about 30 percent, and introduces important radial variations which are sensitive to rotation and to leading edge stagger angle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-177206 , NAS 1.26:177206 , GTPDL-181
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  • 129
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    Preliminary design of a supersonic cruise aircraft high-pressure turbine (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Development of the supersonic cruise aircraft engine continued in this National Aeronautics and Space Administration (NASA) sponsored Pratt and Whitney program for the Preliminary Design of an Advanced High-Pressure Turbine. Airfoil cooling concepts and the technology required to implement these concepts received particular emphasis. Previous supersonic cruise aircraft mission studies were reviewed and the Variable Stream Control Engine (VSCE) was chosen as the candidate or the preliminary turbine design. The design was evaluated for the supersonic cruise mission. The advanced technology to be generated from these designs showed benefits in the supersonic cruise application and subsonic cruise application. The preliminary design incorporates advanced single crystal materials, thermal barrier coatings, and oxidation resistant coatings for both the vane and blade. The 1990 technology vane and blade designs have cooled turbine efficiency of 92.3 percent, 8.05 percent Wae cooling and a 10,000 hour life. An alternate design with 1986 technology has 91.9 percent efficiency and 12.43 percent Wae cooling at the same life. To achieve these performance and life results, technology programs must be pursued to provide the 1990's technology assumed for this study.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-174878 , NAS 1.26:174878 , PWA-5923-14
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    Turbofan aft duct suppressor study program listing and user's guide (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A description of the structure of the Annular Flow Duct Program (AFDP) for the calculation of acoustic suppression due to treatment in a finite length annular duct carrying sheared flow is presented. Although most appropriate for engine exhaust ducts, this program can be used to study sound propagation in any duct that maintains annular geometry over a considerable length of the duct. The program is based on the modal analysis of sound propagation in ducts with axial segments of different wall impedances. For specified duct geometry, wall impedance, flow and acoustic conditions in the duct (including mode amplitude distribution of the source) and duct termination reflection characteristics, the program calculates the suppression due to the treatment in the duct. The presence of forward and backward traveling modes in the duct due to the reflection and redistribution of modes at segment interfaces and duct end terminations are taken into account in the calculations. The effects of thin wall boundary layers (with a linear or mean flow velocity profile) on the acoustic propagation are also included in the program. A functional description of the major subroutines is included and a sample run is provided with an explanation of the output.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-175067 , NAS 1.26:175067
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  • 131
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    Digital electronic engine control F-15 overview (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A flight test evaluation of the digital elctronic engine control (DEEC) system was conducted. An overview of the flight program is presented. The roles of the participating parties, the system, and the flight program objectives are described. The test program approach is discussed, and the engine performance benefits are summarized. A description of the follow-on programs is included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-1 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 1-14
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  • 132
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    Backup control airstart performance on a digital electronic engine control-equipped F100-engine (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The air start capability of a backup control (BUC) was tested for a digital electronic engine control (DEEC) equipped F100 engine, which was installed in an F-15 aircraft. Two air start schedules were tested. Using the group 1 start schedule, based on a 40 sec timer, an air speed of 300 knots was required to ensure successful 40 and 25% BUC mode spooldown airstarts. If core rotor speed (N2) was less than 40% a stall would occur when the start bleed closed, 40 sec after initiation of the air start. All jet fuel starter (JFS) assisted air starts were successful with the group 1 start schedule. For the group 2 schedule, the time between pressurization and start bleed closure ranged between 50 sec and 72 sec. Idle rps was lower than the desired 65% for air starts at higher altitudes and lower air speeds.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-10 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 157-170
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  • 133
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    Flight evaluation of a hydromechanical backup control for the digital electronic engine control system in an F100 engine (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The backup control (BUC) features, the operation of the BUC system, the BUC control logic, and the BUC flight test results are described. The flight test results include: (1) transfers to the BUC at military and maximum power settings; (2) a military power acceleration showing comparisons bvetween flight and simulation for BUC and primary modes; (3) steady-state idle power showing idle compressor speeds at different flight conditions; and (4) idle-to-military power BUC transients showing where cpmpressor stalls occurred for different ramp rates and idle speeds. All the BUC transfers which occur during the DEEC flight program are initiated by the pilot. Automatic transfers to the BUC do not occur.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-9 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 141-155
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  • 134
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    NASA Lewis F100 engine testing (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two builds of an F100 engine model derivative (EMD) engine were evaluated for improvements in engine components and digital electronic engine control (DEEC) logic. Two DEEC flight logics were verified throughout the flight envelope in support of flight clearance for the F100 engine model derivative program (EMPD). A nozzle instability and a faster augmentor transient capability was investigated in support of the F-15 DEEC flight program. Off schedule coupled system mode fan flutter, DEEC nose-boom pressure correlation, DEEC station six pressure comparison, and a new fan inlet variable vane (CIVV) schedule are identified.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-4 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 55-71
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  • 135
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    Energy Efficient Engine (E3) combustion system component technology performance report (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Energy Efficient Engine (E3) combustor effort was conducted as part of the overall NASA/GE E3 Program. This effort included the selection of an advanced double-annular combustion system design. The primary intent of this effort was to evolve a design that meets the stringent emissions and life goals of the E3, as well as all of the usual performance requirements of combustion systems for modern turbofan engines. Numerous detailed design studies were conducted to define the features of the combustion system design. Development test hardware was fabricated, and an extensive testing effort was undertaken to evaluate the combustion system subcomponents in order to verify and refine the design. Technology derived from this effort was incorporated into the engine combustion hardware design. The advanced engine combustion system was then evaluated in component testing to verify the design intent. What evolved from this effort was an advanced combustion system capable of satisfying all of the combustion system design objectives and requirements of the E3.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-168274 , NAS 1.26:168274 , R82AEB401
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  • 136
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    Energy Efficient Engine combustor test hardware detailed design report (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Energy Efficient Engine (E3) Combustor Development effort was conducted as part of the overall NASA/GE E3 Program. This effort included the selection of an advanced double-annular combustion system design. The primary intent was to evolve a design which meets the stringent emissions and life goals of the E3 as well as all of the usual performance requirements of combustion systems for modern turbofan engines. Numerous detailed design studies were conducted to define the features of the combustion system design. Development test hardware was fabricated, and an extensive testing effort was undertaken to evaluate the combustion system subcomponents in order to verify and refine the design. Technology derived from this development effort will be incorporated into the engine combustion system hardware design. This advanced engine combustion system will then be evaluated in component testing to verify the design intent. What is evolving from this development effort is an advanced combustion system capable of satisfying all of the combustion system design objectives and requirements of the E3. Fuel nozzle, diffuser, starting, and emissions design studies are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-168301 , NAS 1.26:168301 , R82AEB472
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  • 137
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    Energy Efficient Engine high pressure turbine component test performance report (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The high pressure turbine for the General Electric Energy Efficient Engine is a two stage design of moderate loading. Results of detailed system studies led to selection of this configuration as the most appropriate in meeting the efficiency goals of the component development program. To verify the design features of the high pressure turbine, a full scale warm air turbine test rig with cooling flows simulated was run. Prior to this testing, an annular cascade test was run to select vane unguided turn for the first stage nozzle. Results of this test showed that the base configuration exceeded the lower unguided turning configuration by 0.48 percent in vane kinetic energy efficiency. The air turbine test program, consisting of extensive mapping and cooling flow variation as well as design point evaluation, demonstrated a design point efficiency level of 90.0 percent based on the thermodynamic definition. In terms of General Electric cycle definition, this efficiency was 92.5 percent. Based on this test, it is concluded that efficiency goals for the Flight Propulsion System were met.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-168289 , NAS 1.26:168289 , R82AEB406
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  • 138
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    Energy Efficient Engine exhaust mixer model technology report addendum; phase 3 test program (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Phase 3 exhaust mixer test program was conducted to explore the trends established during previous Phases 1 and 2. Combinations of mixer design parameters were tested. Phase 3 testing showed that the best performance achievable within tailpipe length and diameter constraints is 2.55 percent better than an optimized separate flow base line. A reduced penetration design achieved about the same overall performance level at a substantially lower level of excess pressure loss but with a small reduction in mixing. To improve reliability of the data, the hot and cold flow thrust coefficient analysis used in Phases 1 and 2 was augmented by calculating percent mixing from traverse data. Relative change in percent mixing between configurations was determined from thrust and flow coefficient increments. The calculation procedure developed was found to be a useful tool in assessing mixer performance. Detailed flow field data were obtained to facilitate calibration of computer codes.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-174799 , NAS 1.26:174799 , PWA-5594-271-ADD
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  • 139
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    Constitutive modeling for isotropic materials (HOST) (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of the first year of work on a program to validate unified constitutive models for isotropic materials utilized in high temperature regions of gas turbine engines and to demonstrate their usefulness in computing stress-strain-time-temperature histories in complex three-dimensional structural components. The unified theories combine all inelastic strain-rate components in a single term avoiding, for example, treating plasticity and creep as separate response phenomena. An extensive review of existing unified theories is given and numerical methods for integrating these stiff time-temperature-dependent constitutive equations are discussed. Two particular models, those developed by Bodner and Partom and by Walker, were selected for more detailed development and evaluation against experimental tensile, creep and cyclic strain tests on specimens of a cast nickel base alloy, B19000+Hf. Initial results comparing computed and test results for tensile and cyclic straining for temperature from ambient to 982 C and strain rates from 10(exp-7) 10(exp-3) s(exp-1) are given. Some preliminary date correlations are presented also for highly non-proportional biaxial loading which demonstrate an increase in biaxial cyclic hardening rate over uniaxial or proportional loading conditions. Initial work has begun on the implementation of both constitutive models in the MARC finite element computer code.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-174718 , SWRI-06-7576/13 , NAS 1.26:174718
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  • 140
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    Fuel system technology overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Fuel system research and technology studies are being conducted to investigate the correlations and interactions of aircraft fuel system design and environment with applicable characteristics of the fuel. Topics include: (1) analysis of in-flight fuel temperatures; (2) fuel systems for high freezing point fuels; (3) experimental study of low temperature pumpability; (4) full scale fuel tank simulation; and (5) rapid freezing point measurement.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 195-203
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  • 141
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    Combustion technology overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An overview of combustor technology developments required for use of broadened property fuels in jet aircraft is presented. The intent of current investigations is to determine the extent to which fuel properties can be varied, to obtain a data base of combustion - fuel quality effects, and to determine the trade-offs associated with broadened property fuels. Subcomponents of in-service combustors such as fuel injectors and liners, as well as air distributions and stoichiometry, are being altered to determine the extent to which fuel flexibility can be extended. Finally, very advanced technology consisting of new combustor concepts is being evolved to optimize the fuel flexibility of gas turbine combustors.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 67-73
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  • 142
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    Fuels research: Fuel thermal stability overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Alternative fuels or crude supplies are examined with respect to satisfying aviation fuel needs for the next 50 years. The thermal stability of potential future fuels is discussed and the effects of these characteristics on aircraft fuel systems are examined. Advanced fuel system technology and design guidelines for future fuels with lower thermal stability are reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 161-168
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  • 143
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    Preliminary studies of combustor sensitivity to alternative fuels (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Combustion problems associated with using alternative fuels ground power and aeropropulsion applications were studied. Rectangular sections designed to simulate large annular combustor test conditions were examined. The effects of using alternative fuels with reduced hydrogen content, increased aromatic content, and a broad variation in fuel property characteristics were also studied. Data of special interest were collected which include: flame radiation characteristics in the various combustor zones; the correponding increase in liner temperature from increased radiant heat flux; the effect of fuel bound nitrogen on oxides of nitrogen (NO sub x) emissions; and the overall total effect of fuel variations on exhaust emissions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 153-160
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  • 144
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    Outlook for alternative energy sources (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Predictions are made concerning the development of alternative energy sources in the light of the present national energy situation. Particular emphasis is given to the impact of alternative fuels development on aviation fuels. The future outlook for aircraft fuels is that for the near term, there possibly will be no major fuel changes, but minor specification changes may be possible if supplies decrease. In the midterm, a broad cut fuel may be used if current development efforts are successful. As synfuel production levels increase beyond the 1990's there may be some mixtures of petroleum-based and synfuel products with the possibility of some shale distillate and indirect coal liquefaction products near the year 2000.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 5-9
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  • 145
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    F100 exhaust nozzle area control (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The details of the F100 nozzle mechanism design are highlighted, placing particular emphasis upon the evolution of design constraints or drivers from initial concept through current operational deployment. A kinematic description of the area control mechanism is given, and several environmental constraints which complicate the normal mechanism design process are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center Proc. of the 14th Aerospace Mech. Symp.; p 211-223
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  • 146
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    Positive displacement type general-aviation engines: Summary and concluding remarks (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The activities of programs investigating various aspects of aircraft internal combustion engines are briefly described including developments in fuel injection technology, cooling systems and drag reduction, turbocharger technology, and stratified-charge rotary engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 313-314
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  • 147
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    Advanced rotary engine studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A review of rotary engine developments relevant to a stratified charge rotary aircraft engine is presented. Advantages in module size and weight, fuel efficiency, reliability, and multi-fuel capability are discussed along with developments in turbocharging, increased mean effective pressure, improved apex seal/trochoid wear surfacing materials, and high strength and temperature aluminum casting alloys. A carbureted prototype aircraft engine is also described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 287-311
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  • 148
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    AiResearch QCGAT engine: Acoustic test results (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The noise levels of the quiet, general aviation turbofan (QCGAT) engine were measured in ground static noise tests. The static noise levels were found to be markedly lower than the demonstrably quiet AiResearch model TFE731 engine. The measured QCGAT noise levels were correlated with analytical noise source predictions to derive free-field component noise predictions. These component noise sources were used to predict the QCGAT flyover noise levels at FAR Part 36 conditions. The predicted flyover noise levels are about 10 decibels lower than the current quietest business jets.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 65-100
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  • 149
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    Propellers at high speeds (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 67-76
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  • 150
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    High-freezing-point fuel studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Considerable progress in developing the experimental and analytical techniques needed to design airplanes to accommodate fuels with less stringent low temperature specifications is reported. A computer technique for calculating fuel temperature profiles in full tanks was developed. The computer program is being extended to include the case of partially empty tanks. Ultimately, the completed package is to be incorporated into an aircraft fuel tank thermal analyser code to permit the designer to fly various thermal exposure patterns, study fuel temperatures versus time, and determine holdup.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 205-219
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  • 151
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    Fuel/engine/airframe tradeoff study, phase 1 (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effects of broadening the specifications for JP-4 and JP-8 fueled on the performance and cost of all USAF aircraft presently using JP-4 as well as those expected to be introduced into the force structure by 1983 are investigated. Test results indicated that there was no impact on engine performance, turbine durability, and coking, however there was a small maintenance cost increase as a result of a small combustor life decrease. Using JP-4 as standard fuel will avoid the use of high demand middle distillate fuels and give producers flexibility. Extensive use of JP-8 in the United States will increase middle distillate demand and cause a slight increase in engine hot-section maintenance. It is also concluded that the maximum allowable freeze point of JP-4 or JP-8 cannot be increased without degrading system performance and safety as critical conditions are approached.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 41-47
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  • 152
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    Current jet fuel trends (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Data concerning the properties of commercial jet fuels during the period between 1974 and 1979 are discussed. During this period the average aromatics content of fuels increased from 16% to 17.5%. It is evident that the arrival of Alaska North Slope crude in 1977 had a significant impact upon the aromatics content of jet fuel supply at West Coast points with less effect upon the entire United States domestic market. This increase in aromatics has not been accompanied by a corresponding reduction in burning quality as measured by smoke point. There has been a reduction of .6 smoke point on the average. Looking at hydrogen content as a measure of burning quality, the all refinery average calculated hydrogen for 1978 was approximately 13.7%. The relationship between hydrogen content and aromatics content shows a slope of .043% reduction in hydrogen for 1% increase in aromatics.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 11-14
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  • 153
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    NASA/General Electric broad-specification fuels combustion technology program, phase 1 (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of broad specification fuels in aircraft turbine engine combustion systems was examined. Three different combustor design concepts were evaluated for their ability to use broad specification fuels while meeting several specific emissions, performance, and durability goals. These combustor concepts covered a range from those having limited complexity and relatively low technical risk to those having high potential for achieving all of the program goals at the expense of increased technical risk.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 109-113
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  • 154
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    Air Force fuel mainburner/turbine effects programs (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A program for the determination of fuel property effects on aircraft gas turbine engine mainburners and turbines is discussed. The six engines selected as test candidates are the J79, J85, J57, TF30, TF39, and F100. Fuels election is the responsibility of the contractors with two fuels as exceptions. The petroleum JP-4 is to be used as a baseline in all tests. The shale JP-4 is to be used in nearly all tests. Fuel properties are to be correlated with combustion system performance paramters. In addition, life predictions are to be made for combustor and turbine hardware. These predictions are to be based on a typical mission for each system, measured metal temperatures and temperature gradients, and oxidation/corrosion effects.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 99-103
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  • 155
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    The broadened-specification fuels combustion technology program at Pratt and Whitney Aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The impact of the use of broadened specification fuels on combustor design was investigated. Particular emphasis was placed on establishing the viability of various combustor modifications to permit the use of broadened specification fuels while meeting exhaust emissions and performance specifications and maintaining acceptable combustor operational and durability characteristics. Three different combustor concepts will be evaluated. Various design modifications on the operating capability of each of the combustor concepts with experimental referee broadened specification Fuel. The modifications that were evaluated included perturbations of the combustor airflow schedules to alter local stoichiometry and residence time histories revisions to the fuel injectors, and variations in liner cooling including the use of thermal barrier coatings and/or advanced cooling concepts.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 105-108
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  • 156
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    An overview of NASA research on positive displacement general-aviation engines (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The research and technology program related to improved and advanced general aviation engines is described. Current research is directed at the near-term improvement of conventional air-cooled spark-ignition piston engines and at future alternative engine systems based on all-new spark-ignition piston engines, lightweight diesels, and rotary combustion engines that show potential for meeting program goals in the midterm and long-term future. The conventional piston engine activities involve efforts on applying existing technology to improve fuel economy, investigation of key processes to permit leaner operation and reduce drag, and the development of cost effective technology to permit flight at high-altitudes where fuel economy and safety are improved. The advanced engine concepts activities include engine conceptual design studies and enabling technology efforts on the critical or key technology items.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 227-229
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  • 157
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    Summary of NASA QCGAT program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The application of large turbofan engine technology to small general aviation turbofan engines to achieve low noise, low emissions, and acceptable fuel consumption is described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 189-193
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  • 158
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    New opportunities for future, small, General-Aviation Turbine Engines (GATE) (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The results of four independent contracted studies to explore the opportunities for future small turbine engines are summarized in a composite overview. Candidate advanced technologies are screened, various cycles and staging arrangements are parametrically evaluated, and optimum conceptual engines are identified for a range of 300 to 600 horsepower applications. Engine improvements of 20 percent in specific fuel consumption and 40 percent in engine cost were forecast using high risk technologies that could be technically demonstrated by 1988. The ensuing economic benefits are in the neighborhood of 20 to 30 percent for twin-engine aircraft currently powered by piston engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 195-219
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    Avco Lycoming quiet clean general aviation turbofan engine (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A fan module was developed using an existing turboshaft engine. The fan was designed using the latest in large engine noise control technology. A mixer was added to reduce the already low exhaust gas velocity. A nacelle incorporating sound treatment was provided for the test engine. A noise prediction model was used through the design process to evaluate the various design alternatives. Acoustic tests were then made to verify the prediction and identify the noise characteristics of the fan, core, jet, and sound treatment. Analysis of the recorded data yielded close agreement with the expected results. Core noise, as was expected, was the predominant source of noise for the quiet clean general aviation turbofan (QCGAT) engine. Flyover noise predictions were made which indicated that the Avco Lycoming QCGAT engine would meet the goals set for the QCGAT program.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 155-187
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  • 160
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    Low speed propellers: Impact of advanced technologies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Sensitivity studies performed to evaluate the potential of several advanced technological elements on propeller performance, noise, weight, and cost for general aviation aircraft are discussed. Studies indicate that the application of advanced technologies to general aviation propellers can reduce fuel consumption in future aircraft an average of ten percent, meeting current regulatory noise limits. Through the use of composite blade construction, up to 25 percent propeller weight reduction can be achieved. This weight reduction in addition to seven percent propeller efficiency improvements through application of advanced technologies result in four percent reduction in direct operating costs, ten percent reduction in aircraft acquisition cost, and seven percent lower gross weight for general aviation aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 327-343
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  • 161
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    NASA propeller noise research (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The research in propeller noise prediction, noise/performance optimization, and interior reduction is described. Selected results are presented to illustrate the status of the technology and the direction of future research.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 405-420
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  • 162
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    Advanced propeller aerodynamic analysis (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The analytical approaches as well as the capabilities of three advanced analyses for predicting propeller aerodynamic performance are presented. It is shown that two of these analyses use a lifting line representation for the propeller blades, and the third uses a lifting surface representation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 375-385
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  • 163
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    NASA propeller technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A program on propeller technology applicable to both low and high speed general aviation aircraft is summarized, and the overall program objectives and approach are outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 315-325
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  • 164
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    Lightweight diesel aircraft engines for general aviation (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A methodical design study was conducted to arrive at new diesel engine configurations and applicable advanced technologies. Two engines are discussed and the description of each engine includes concept drawings. A performance analysis, stress and weight prediction, and a cost study were also conducted. This information was then applied to two airplane concepts, a six-place twin and a four-place single engine aircraft. The aircraft study consisted of installation drawings, computer generated performance data, aircraft operating costs and drawings of the resulting airplanes. The performance data shows a vast improvement over current gasoline-powered aircraft. At the completion of this basic study, the program was expanded to evaluate a third engine configuration. This third engine incorporates the best features of the original two, and its design is currently in progress. Preliminary information on this engine is presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 247-285
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  • 165
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    Avco Lycoming QCGAT program design cycle, demonstrated performance and emissions (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A high bypass ratio, twin spool turbofan engine of modular design which incorporates a front fan module driven by a modified LTS101 core engine was tested. The engine is housed in a nacelle incorporating full length fan ducting with sound treatment in both the inlet and fan discharge flow paths. Design goals of components and results of component tests are presented together with full engine test results. The rationale behind the combustor design selected for the engine is presented as well as the emissions test results. Total system (engine and nacelle) test results are included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 135-154
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  • 166
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    Effect of fuel molecular structure on soot formation in gas turbine combustion (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effect of fuel variations at the same hydrogen content on the formation of soot in a gas turbine combustor was studied. Six fuels were burned to a combustor over a matrix of about 50 test conditions with test conditions ranging over 500-1800 kPa (5-18 atm) pressure and 500-1000 K burner inlet temperature; fuel-air ratios were varied from 0.008-0.024. Flame radiation measurements were made through a sapphire window toward the end of the primary zone. The hydrogen content of the six test fuels ranged from 12.80 to 12.88%. Five fuels emphasized hydrocarbon types: (mono, di, and tricyclic), naphthenes (decalin) and partially hydrogenated aromatics (tetralin); the sixth fuel emphasized final boiling point.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 147-152
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  • 167
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    Fuel property effects in stirred combustors (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Soot formation in strongly backmixed combustion was investigated using the jet-stirred combustor (JSC). This device provided a combustion volume in which temperature and combustion were uniform. It simulated the recirculating characteristics of the gas turbine primary zone; it was in this zone where mixture conditions were sufficiently rich to produce soot. Results indicate that the JSC allows study of soot formation in an aerodynamic situation revelant to gas turbines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 139-146
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  • 168
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    Soot formation and burnout in flames (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The amount of soot formed when burning a benzene/hexane mixture in a turbulent combustor was examined. Soot concentration profiles in the same combustor for kerosene fuel are given. The chemistry of the formation of soot precursors, the nucleation, growth and subsequent burnout of soot particles, and the effect of mixing on the previous steps were considered.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 131-137
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  • 169
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    Antimisting kerosene (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The antimisting additive ((FM-9) was tested in terms of its propulsion systems performance. The effect of the additive on engine operation was evaluated, operating problems were identified, the adaptability of engines to antimisting kerosene was assessed, and the potential viability of this fuel for use in present and future fan jet engines was determined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels Jul. 1980; p 125-130
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  • 170
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    Atomization of broad specification aircraft fuels (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The atomization properties of liquid fuels for the potential use in aircraft gas turbine engines are discussed. The significance of these properties are addressed with respect to the ignition and subsequent combustion behavior of the fuel spray/air mixture. It is shown that the fuel properties which affect the atomization behavior (viscosity, surface tension, and density) are less favorable for the broad specification fuels as compared to with those for conventional fuels.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels Jul. 1980; p 117-124
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  • 171
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    Fuels research: Combustion effects overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effects of broadened property fuels on gas turbine combustors were assessed. Those physical and chemical properties of fuels that affect aviation gas turbine combustion were isolated and identified. Combustion sensitivity to variations in particular fuel properties were determined. Advanced combustion concepts and subcomponents that could lessen the effect of using broadened property fuels were also identified.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 115-116
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  • 172
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    NASA broadened-specification fuels combustion technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The broadened-Specification Fuels Combustion Technology program's purpose is to evolve and demonstrate the technology required to enable current and next generation high-thrust, high-bypass-ratio turbofan engines to use fuels with broadened properties and to verify the evolved technology in full scale engine tests. The three phases of the program are combustor concept screening, combustor optimization testing, and engine verification testing. Constraints for designing combustion systems are outlined and problems to be expected in the use of broadened properties fuels are listed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels p95-98 (SEE N80-29300 20-07)
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  • 173
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    Fuel character effects on the J79 and F101 engine combustion systems (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effects of select fuel property variations on two major engine classifications are summarized. Thirteen refined and blended fuels were used which exhibited significant variations in hydrogen content, aromatic type, initial boiling point, final boiling point, and viscosity. Trends were very similar but the degree of fuel sensitivity was not constant. For both systems the dominant fuel property during high pressure operation was found to be fuel hydrogen content. For operation at low pressure test points the fuel volatility and viscosity became the dominant fuel properties for both systems. Aromatic type and final boiling point did not significantly affect combustion data. Correlations of other fuel properties with these and other performance parameters are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 83-93
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  • 174
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    Military jet fuel from shale oil (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Investigations leading to a specification for aviation turbine fuel produced from whole crude shale oil are described. Refining methods involving hydrocracking, hydrotreating, and extraction processes are briefly examined and their production capabilities are assessed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 49-57
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  • 175
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    Aviation fuels outlook (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Options for satisfying the future demand for commercial jet fuels are analyzed. It is concluded that the most effective means to this end are to attract more refiners to the jet fuel market and encourage development of processes to convert oil shale and coal to transportation fuels. Furthermore, changing the U.S. refineries fuel specification would not significantly alter jet fuel availability.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 15-24
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  • 176
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    AiResearch QCGAT engine, airplane, and nacelle design features (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The quiet, clean, general aviation turbofan engine and nacelle system was designed and tested. The engine utilized the core of the AiResearch model TFE731-3 engine and incorporated several unique noise- and emissions-reduction features. Components that were successfully adapted to this core include the fan, gearbox, combustor, low-pressure turbine, and associated structure. A highly versatile workhorse nacelle incorporating interchangeable acoustic and hardwall duct liners, showed that large-engine attenuation technology could be applied to small propulsion engines. The application of the mixer compound nozzle demonstrated both performance and noise advantages on the engine. Major performance, emissions, and noise goals were demonstrated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 11-43
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  • 177
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    High-speed-propeller wind-tunnel aeroacoustic results (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Some aerodynamic concepts are presented together with an explanation of how these concepts are applied to advanced propeller design. The unique features of this propulsion system are addressed with emphasis on the design concepts being considered for the high speed turboprop. More particular emphasis is given to the blade sweep, long blade chords, and the large number of blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 361-374
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  • 178
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    Determination of jet fuel thermal deposit rate using a modified JFTOT (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Three fuels having different breakpoint temperatures were studied in the modified jet fuel thermal oxidation tester. The lower stability fuel with a breakpoint of 240 C was first stressed at a constant temperature. After repeating this procedure at several different temperatures, an Arrehenius plot was drawn from the data. The correlation coefficient and the energy of activation were calculated to be 0.97 and 8 kcal/mole respectively. Two other fuels having breakpoint temperatures of 271 C and 285 C were also studied in a similar manner. A straight line was drawn through the data at a slope equivalent to the slope of the lower stability fuel. The deposit formation rates for the three fuels were determined at 260 C, and a relative deposit formation rate at this temperature was calculated and plotted as a function of the individual fuel's breakpoint temperatures.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 181-184
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  • 179
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    Experimental combustor study program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Advanced combustor concepts are evaluated as a means of accommodating possible future broad specification fuels. The three advanced double annular combustor concepts consisted of (1) a concept employing high pressure drop fuel nozzles for improved atomization, (2) a concept with premixing tubes in the main stage, and (3) a concept with the pilot stage on the inside and the main stage on the sideout, which is the reverse of the other two concepts. All of the advanced concepts show promise for reduced sensitivity to fuel hydrogen content. Some hardware problems were encountered, but these problems could be quickly resolved if refinement tests were conducted. The design with the premixing main stage was selected for a parametric test because of its low NOx emissions level, carbon free dome, and very low dome temperatures which were essentially independent of fuel type. The other advanced designs also had low done temperatures. The premixing dome design liner temperatures exhibited less sensitivity to fuel type than did the base-line combustor, although more sensitivity than observed for concept 1. The inner liner hot spot and the observed smoke results for the premixing design suggest that the fuel-air mixture was not as uniform as desired.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 75-82
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  • 180
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    Fuels characterization studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Current analytical techniques used in the characterization of broadened properties fuels are briefly described. Included are liquid chromatography, gas chromatography, and nuclear magnetic resonance spectroscopy. High performance liquid chromatographic ground-type methods development is being approached from several directions, including aromatic fraction standards development and the elimination of standards through removal or partial removal of the alkene and aromatic fractions or through the use of whole fuel refractive index values. More sensitive methods for alkene determinations using an ultraviolet-visible detector are also being pursued. Some of the more successful gas chromatographic physical property determinations for petroleum derived fuels are the distillation curve (simulated distillation), heat of combustion, hydrogen content, API gravity, viscosity, flash point, and (to a lesser extent) freezing point.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 59-65
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  • 181
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    Future aviation fuels overview (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The outlook for aviation fuels through the turn of the century is briefly discussed and the general objectives of the NASA Lewis Alternative Aviation Fuels Research Project are outlined. The NASA program involves the evaluation of potential characteristics of future jet aircraft fuels, the determination of the effects of those fuels on engine and fuel system components, and the development of a component technology to use those fuels.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 1-4
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  • 182
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    Advanced turboprop potential for high speed (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A turboprop propulsion system for general aviation aircraft, allowing high speed flight (to 0.8 Mach) is discussed. Design methodologies for aerodynamic and acoustic considerations and the performance and cost advantages of a prop-fan aircraft are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 345-359
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  • 183
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    QCGAT aircraft/engine design for reduced noise and emissions (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The high bypass ratio QCGAT engine played an important role in shaping the aircraft design. The aircraft which evolved is a sleek, advanced design, six-place aircraft with 3538 kg (7,800 lb) maximum gross weight. It offers a 2778 kilometer (1500 nautical mile) range with cruise speed of 0.5 Mach number and will take-off and land on the vast majority of general aviation airfields. Advanced features include broad application of composite materials and a supercritical wing design with winglets. Full-span fowler flaps were introduced to improve landing capability. Engines are fuselage-mounted with inlets over the wing to provide shielding of fan noise by the wing surfaces. The design objectives, noise, and emission considerations, engine cycle and engine description are discussed as well as specific design features.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 101-133
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  • 184
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    AiResearch QCGAT engine performance and emissions tests (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results of aerodynamic performance and emission tests, conducted on a specially designed QCGAT engine in the 17,793-N (4,000 lb) thrust class, are presented. Performance of the AiResearch QCGAT engine was excellent throughout all testing. No serious mechanical malfunctions were encountered, and no significant test time was lost due to engine-related problems. Emissions were drastically reduced over similar engines, and the engine exhibited good smoke performance.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 45-64
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  • 185
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    A Review of propeller theory (1948)
    In:  CASI
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    Publication Date: 2016-06-07
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA: Univ. Conf. on Aerodyn.; p 71-105
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  • 186
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    NASA Research in Aeropropulsion (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The role of the Lewis Research Center in aeronautical propulsion is described. The state of the art in engine systems and components are discussed and some of the problems that confront the civil and military aeronautic sectors are addressed. Some of the programs that are under way are summarized with emphasis on the future needs and opportunities in aeronautics.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Impact for the 80's: Proc. of a Conf. on Selected Technol. for Business and Ind.; p 11-26
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  • 187
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    Propulsion control and control theory: A new research focus (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Technological developments necessary for the implementation of advanced digital control concepts for aircraft propulsion are identified and discussed. Developments associated with the replacement analog controllers with digital control systems, sensors and actuators, and control modes and software are reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion Controls, 1979; p 89-95
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  • 188
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    Should we attempt global (inlet engine airframe) control design? (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The feasibility of multivariable design of the entire airplane control system is briefly addressed. An intermediate step in that direction is to design a control for an inlet engine augmentor system by using multivariable techniques. The supersonic cruise large scale inlet research program is described which will provide an opportunity to develop, integrate, and wind tunnel test a control for a mixed compression inlet and variable cycle engine. The integrated propulsion airframe control program is also discussed which will introduce the problem of implementing MVC within a distributed processing avionics architecture, requiring real time decomposition of the global design into independent modules in response to hardware communication failures.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 71-82
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  • 189
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    Design of a multivariable integrated control for a supersonic propulsion system (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: An inlet/engine/nozzle integrated control mode for the propulsion system of an advanced supersonic commercial aircraft was studied. Results show that integration of these control functions can result in both operational and performance benefits for the propulsion system. For example, this integrated control mode may make it possible to minimize the use of inlet bypass doors for shock position control. This may be of benefit to the aircraft as a result of minimizing: (1) bypass bleed drag effects; (2) perturbations to the aircraft resulting from the side thrust effect of the bypass bleeds; and (3) potential unstarts of the inlet. A conceptual integrated control mode was developed which makes use of many cross coupling paths between inlet and engine control variables and inlet and engine sensed variables. A multivariable control design technique based upon linear quadratic regulator theory was applied to designing the feedback gains for this control to allow a simulation evaluation of the benefits of the integrated control mode.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 35-47
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  • 190
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    Sensor/actuator failure detection for turbofan engines (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A procedure for sensor/actuator failure detection using a generalized likelihood ratio (GLR) test is described. The GLR concept can provide a reliable evaluation of failure occurence when associated with a feedback control design which does not require sensor outputs to provide data estimates. A GLR detector was developed and tested.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 139-143
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  • 191
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    Multivariable synthesis with transfer functions (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A transfer function design theory for multivariable control synthesis is highlighted. The use of unique transfer function matrices and two simple, basic relationships - a synthesis equation and a design equation - are presented and illustrated. This multivariable transfer function approach provides the designer with a capability to specify directly desired dynamic relationships between command variables and controlled or response variables. At the same time, insight and influence over response, simplifications, and internal stability is afforded by the method. A general, comprehensive multivariable synthesis capability is indicated including nonminmum phase and unstable plants. Gas turbine engine examples are used to illustrate the ideas and method.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 111-127
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  • 192
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    Road map to adaptive optimal control (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A building block control structure leading toward adaptive, optimal control for jet engines is developed. This approach simplifies the addition of new features and allows for easier checkout of the control by providing a baseline system for comparison. Also, it is possible to eliminate certain features that do not have payoff by being selective in the addition of new building blocks to be added to the baseline system. The minimum risk approach specifically addresses the need for active identification of the plant to be controlled in real time and real time optimization of the control for the identified plant.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 83-87
    Format: application/pdf
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  • 193
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    Future Air Force aircraft propulsion control systems: The extended summary paper (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Hydromechanical control technology simply cannot compete against the performance benefits offered by electronics. Future military aircraft propulsion control systems will be full authority, digital electronic, microprocessor base systems. Anticipating the day when microprocessor technology will permit the integration and management of aircraft flight control, fire control and propulsion control systems, the Air Force Aero Propulsion Laboratory is developing control logic algorithms for a real time, adaptive control and diagnostic information system.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 63-67
    Format: application/pdf
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  • 194
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    F100 multivariable control synthesis program: A review of full scale engine altitude tests (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The benefits of linear quadratic regulator synthesis methods in designing a multivariable engine control capable of operating an engine throughout its flight envelope were demonstrated. The entire multivariable control synthesis program is reviewed with particular emphasis on engine tests conducted in the NASA Lewis propulsion systems laboratory altitude facility. The multivariable control has basically a proportional plus integral, model following structure with gains scheduled as functions of flight condition. The multivariable control logic design is described, along with control computer implementation aspects. Altitude tests demonstrated that the multivariable control logic could control an engine over a wide range of test conditions. Representative transient responses are presented to demonstrate engine behavior and the functioning of the control logic.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion Controls, 1979; p 20-34
    Format: application/pdf
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  • 195
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    Multivariable identification using centralized fixed modes (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: A procedure to determine a state space model of a multivariable system (lambda inputs, m outputs) is presented. The model is suitable for control studies and uses single input, single output (SISO) system data in the identification procedure. The procedure can be defined in three distinct steps. First, the system's lambda x m SISO transfer functions are identified by using any standard or known identification technique for SISO systems. One objective of this step is to identify SISO transfer functions with as few distinct modes as possible between any two functions. Second, the time domain realization of each SISO transfer function is obtained in a straightforward manner and combined into a total multivariable realization. This total realization, in all probability, has more state variables than are required to define system response. In the third step, these excess or redundant states are removed by using minimal realization theory. The remaining states are related to system centralized fixed modes. Eigenvalue-eigenvector techniques were recently reported that yield a computationally feasible solution to the problem posed in step three. The procedure is applied to QCSEE data to demonstrate its feasibility.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion Controls, 1979; p 3-10
    Format: text
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  • 196
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    All-purpose bidirectional four-quadrant controller (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The basic purpose of this paper is to provide some information regarding bidirectional four quadrant resonant power conversion and describe possible applications to aircraft electrical systems. As this technology has been developed sufficiently to demonstrate its feasibility, this is an appropriate time to evaluate the benefits of its application to aircraft electrical systems.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Elect. Secondary Power; p 189-196
    Format: application/pdf
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  • 197
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    Application of advanced materials to rotating machines (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In discussing the application of advanced materials to rotating machinery, the following topics are covered: the torque speed characteristics of ac and dc machines, motor and transformer losses, the factors affecting core loss in motors, advanced magnetic materials and conductors, and design tradeoffs for samarium cobalt motors.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Elect. Secondary Power; p 93-101
    Format: application/pdf
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  • 198
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    Installation of electric generators on turbine engines (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The installation of generators on turbine aircraft is discussed. Emphasis is placed on the use of the samarium cobalt generator. Potential advantages of an electric secondary power system at the engine level are listed. The integrated generator and the externally mounted generator are discussed. It is concluded that the integrated generator is best used in turbojet and low bypass ratio engines where there is no easy way of placing generators externally without influencing frontal areas.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Aircraft Elect. Secondary Power; p 73-78
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  • 199
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    Permanent-Magnet Motors and Generators for Aircraft (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Electric motors and generators that use permarotating machinery, but aspects of control and power conditioning are also considered. The discussion is structured around three basic areas: rotating machine design considerations presents various configuration and material options, generator applications provides insight into utilization areas and shows actual hardware and test results, and motor applications provides the same type of information for drive systems.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Aircraft Elect. Secondary Power; p 79-91
    Format: application/pdf
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  • 200
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    Primary electric power generation systems for advanced-technology engines (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The advantages of the all electric airplane are discussed. In the all electric airplane the generator is the sole source of electric power; it powers the primary and secondary flight controls, the environmentals, and the landing gear. Five candidates for all electric power systems are discussed and compared. Cost benefits of the all electric airplane are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Aircraft Elect. Secondary Power; p 51-72
    Format: application/pdf
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