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  • Inorganic Chemistry  (765)
  • Analytical Chemistry and Spectroscopy  (734)
  • Cell & Developmental Biology  (298)
  • AIRCRAFT PROPULSION AND POWER
  • 1975-1979  (2,014)
  • 1915-1919
  • 1978  (2,014)
Collection
Keywords
Publisher
Years
  • 1975-1979  (2,014)
  • 1915-1919
Year
  • 1
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    Optimal control of a supersonic inlet to minimize frequency of inlet unstart (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: A preliminary investigation into the use of modern control theory for the design of controls for a supersonic inlet is described. In particular, the task of controlling a mixed-compression supersonic inlet is formulated as a linear optimal stochastic control and estimation problem. An inlet can exhibit an undesirable instability due to excessive inlet normal shock motion. For the optimal control formulation of the inlet problem, a non quadratic performance index, which is equal to the expected frequency of inlet unstarts, is used. This physically meaningful performance index is minimized for a range of inlet disturbance and measurement noise covariances.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 323-335
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  • 2
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    Normal shock and restart controls for a supersonic airbreathing propulsion system (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-28
    Description: Results of experimental investigations to control a supersonic mixed-compression inlet coupled to a turbojet engine are presented. Special instrumentation and servoactuators were developed to have sufficiently fast dynamic response so that basic propulsion system dynamics were the main limitation to controllability. In some cases servoactuator input signals were electronically limited to simulate moderate performance flight hardware.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 299-321
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  • 3
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    Gas turbine engine emissions - Problems, progress and future (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The current status of the problem of gas turbine engine emissions is reviewed. Presently promulgated EPA standards and their implications for aircraft gas turbines are discussed. The progress and status of emissions reduction technology programs and other efforts which have emphasized advanced combustor technology are reviewed in detail. Also examined are those efforts underway to determine the emissions floor and incorporate those techniques into practical combustors of the future.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Progress in Energy and Combustion Science; 4; 2, 19; 1978
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  • 4
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    Multitube turbojet noise-suppression studies using cross-correlation techniques (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The noise-generating region of a suppressed turbojet exhaust is studied by cross-correlating static pressure fluctuations within the exhaust with far-field sound for Mach numbers up to 0.99, using a 31-tube nozzle having an area ratio of 3.1. Measurements made with an unsuppressed turbojet exhaust having an equivalent area ratio and operating under effectively equal thrust loads serve as the experimental control. Static pressure-level measurements, made with a calibrated high-temperature acoustically damped probe tube, show that noise suppression by multitube nozzles results from reduced turbulence levels. The maximum fluctuating static-pressure level in the unsuppressed turbojet exhaust is typically 5-6 dB higher than static-pressure levels in the suppressed exhaust under conditions of effectively equal static thrust. This suggests that the turbulence intensity in the multitube suppressor flow is reduced in excess of 20% compared with the unsuppressed jet exhaust.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Acoustical Society of America; vol. 63
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  • 5
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    Propulsion (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: NASA aims at developing propulsion technology to reduce the fuel consumption of present engines by 5%, that of new engines of the late 1980s by at least 12%, and that of an advanced early 1990s turboprop by an additional 15%. This paper reviews three separate NASA programs which take up these aims. They are, respectively, Engine Component Improvement, Energy Efficient Engine, and Advanced Turboprops.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 16; July-Aug
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  • 6
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    Engine requirements for future general aviation aircraft (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The market place is examined for general aviation aircraft into the 1980's. The visible constraints that engine manufacturers must face regardless of the type of cycle are indicated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center The Rotary Combust. Engine; p 175-186
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  • 7
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    Review of the Rhein-Flugzeugbau Wankel powered aircraft program (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The development of light aircraft with special emphasis on modern propulsion systems and production is discussed in terms of the application of rotary engines to aircraft. Emphasis is placed on the integrated ducted-fan propulsion system using rotary engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center The Rotary Combust. Engine; p 109-122
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  • 8
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    Update of development on the new Audi NSU rotary engine generation (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Rotary engines with a chamber volume of 750 cc as a two rotor automotive powerplant, called KKM 871 are described. This engine is compared to a 3 liter or 183 cubic inch, six-cylinder reciprocating engine. Emphasis is placed on exhaust emission control and fuel economy.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center The Rotary Combust. Engine 85-107 (SEE N79-15961 07-07)
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  • 9
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    Rotary engine developments at Curtiss-Wright over the past 20 years and review of general aviation engine potential (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The development of the rotary engine as a viable power plant capable of wide application is reviewed. Research results on the stratified charge engine with direct chamber injection are included. Emission control, reduced fuel consumption, and low noise level are among the factors discussed in terms of using the rotary engine in general aviation aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center The Rotary Combust. Engine; p 123-174
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  • 10
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    Development status of rotary engine at Toyo Kogyo (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Progress in the development of rotary engines which use a thermal reactor as the primary part of the exhaust emission control system is reviewed. Possibilities of further improvements in fuel economy of future rotary engines are indicated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center The Rotary Combust. Engine; p 37-84
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  • 11
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    General aviation energy-conservation research programs (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A review is presented of nonturbine general aviation engine programs underway at the NASA-Lewis Research Center. The program encompasses conventional, lightweight diesel, and rotary engines. Its three major thrusts are: (1) reduced SFC's; (2) improved fuels tolerance; and (3) reducing emissions. Current and planned future programs in such areas as lean operation, improved fuel management, advanced cooling techniques, and advanced engine concepts, are described. These are expected to lay the technology base, by the mid to latter 1980's, for engines whose total fuel costs are as much as 30% lower than today's conventional engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: The Rotary Combust. Engine; p 13-35
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  • 12
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    Advanced materials research for long-haul aircraft turbine engines (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The status of research efforts to apply low to intermediate temperature composite materials and advanced high temperature materials to engine components is reviewed. Emerging materials technologies and their potential benefits to aircraft gas turbines were emphasized. The problems were identified, and the general state of the technology for near term use was assessed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 187-204
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  • 13
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    Gas turbine engine emission reduction technology program (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Progress in the development of combustor technology to meet the standards for the allowable pollutant emission levels of aircraft gas turbine engines is reported. The high-bypass-ratio turbofan engines which power the large commercial aircraft were emphasized along with efforts to reduce emission for near term applications. Recommendations for continuing research to reduce emissions to meet far term needs are given.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 205-216
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  • 14
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    Status of advanced turboprop technology (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Research is reviewed in the following areas: turboprop powered transport aircraft; wind tunnel aerodynamic and acoustics tests of model propellers; turboprop maintenance; and wind tunnel tests on airframe-turboprop interactions. Continued development of the technology for advanced turboprop transport was emphasized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 139-166
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  • 15
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    Propulsion systems noise technology (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Turbofan engine noise research relevant to conventional aircraft is discussed. In the area of fan noise, static to flight noise differences were discussed and data were presented for two different ways of simulating flight behavior. Experimental results from a swept rotor fan design are presented which show that this concept has potential for reducing the multiple-pure-tone or buzz-saw noise related to the shock waves on a fan operating at supersonic tip speeds. Acoustic suppressor research objectives centered around the effect of the wave system generated by the fan stage that is the input to the treatment. A simplifying and unifying parameter, mode cutoff ratio was described. Results are presented which show that suppressor performance can be improved if the input wave is more precisely described. In jet noise, calculated results showing the potential noise reduction from the use of internal mixer nozzles rather than separate flow nozzles are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 167-185
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  • 16
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    Energy efficient engine preliminary design and integration studies (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The characteristics and systems benefits of an energy efficient engine (E3) suitable for use on advanced subsonic transport aircraft were determined. Relative to a current CF6-50C engine, the following benefits were estimated: 14.4% reduction in installed cruise specific fuel consumption, and a reduction in direct operating cost of more than 5%. The advanced technology E3 system would also permit: compliance with FAR 36 (1977) noise limits, and compliance with 1981 EPA emission standards.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 111-138
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  • 17
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    Energy efficient engine: Preliminary design and integration studies (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A mixed exhaust, direct drive fan turbofan configuration was selected from four candidates. This choice was based on its ability to exceed study goals of 12% lower thrust specific fuel consumption and 5% lower direct operating cost by the 1990's with commercially acceptable technical risk and relative mechanical simplicity. The evaluation leading to configuration selection is discussed. Necessary technology advancements are identified and related to the goals.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 89-110
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  • 18
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    Engine component improvement: JT8D and JT9D performance improvements (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A feasibility analysis screening method for predicting the airline acceptance of a proposed engine performance improvement modification was developed. Technical information derived from available test data and analytical models is used along with conceptual/preliminary designs to establish the predicted performance improvement, weight and installation characteristics, the cost for new production and retrofit, maintenance cost and qualitative characteristics of the performance improvement concepts being evaluated. These results are used to arrive at the payback period, which is the time required for an airline to recover the investment cost of concept implementation, and to predict the amount of fuel saved by a performance improvement concept. The assumptions used to calculate the payback period and fuel saved are discussed. A summary of the results when the screening method is applied is presented for several representative JT8D and JT9D performance improvement concepts. An example of the input information used to develop the summary results is shown.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 79-80
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  • 19
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    CF6 performance improvement (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Potential CF6 engine performance improvements directed at reduced fuel consumption were identified and screened relative to airline acceptability and are reviewed. The screening process developed to provide evaluations of fuel savings and economic factors including return on investment and direct operating cost is described. In addition, assessments of development risk and production potential are made. Several promising concepts selected for full-scale development based on a ranking involving these factors are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 59-78
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  • 20
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    ACEE Propulsion Overview (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Technology for fuel-efficient subsonic CTOL transport aircraft is discussed. The engine component improvement project, the energy efficient engine project, and the advanced turboprop project are included. The overall goals and objectives of each project are reviewed and the approach and schedule for accomplishing these project goals and objectives are given.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 9-23
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  • 21
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    Gas path sealing in turbine engines (1978)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Gas path seals are discussed with emphasis on sealing clearance effects on engine component efficiency, compressor pressure ratio, and stall margin. Various case-rotor relative displacements, which affect gas path seal clearances, are identified. Forces produced by nonuniform sealing clearances and their effect on rotor stability are examined qualitatively, and recent work on turbine-blade-tip sealing for high temperatures is described. The need for active clearance control and for engine structural analysis is discussed. The functions of the internal-flow system and its seals are reviewed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Seal Technol. in Gas Turbine Eng.; 41 p
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  • 22
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    Progress in advanced high temperature turbine materials, coatings, and technology (1978)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Advanced materials, coatings, and cooling technology is assessed in terms of improved aircraft turbine engine performance. High cycle operating temperatures, lighter structural components, and adequate resistance to the various environmental factors associated with aircraft gas turbine engines are among the factors considered. Emphasis is placed on progress in development of high temperature materials for coating protection against oxidation, hot corrosion and erosion, and in turbine cooling technology. Specific topics discussed include metal matrix composites, superalloys, directionally solidified eutectics, and ceramics.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD High Temp. Probl. in Gas Turbine Eng.; 31 p
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  • 23
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    Design of an exhaust mixer nozzle for the Avco-Lycoming Quiet Clean General Aviation Turbofan (QCGAT) (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes the design configuration and method used to design the forced engine exhaust to bypass air mixing system for Lycoming's QCGAT engine. This mixer is an integral part of the total engine and nacelle system and was configured to reduce the propulsion system noise and fuel consumption levels.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159426 , LYC-78-36
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  • 24
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    QCGAT mixer compound exhaust system design and static big model test report (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mixer exhaust system was designed to meet the proposed performance and exhaust jet noise goals for the AiResearch QCGAT engine. Some 0.35 scale models of the various nozzles were fabricated and aerodynamically and acoustically tested. Preliminary optimization, engine cycle matching, model test data and analysis are presented. A final mixer exhaust system is selected for optimum performance for the overall flight regime.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135386 , AIRESEARCH-21-2861
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  • 25
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    Low-speed aerodynamic performance of 50.8-centimeter-diameter noise-suppressing inlets for the Quiet, Clean, Short-haul Experimental Engine (QCSEE) (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two basic inlet concepts, a high throat Mach number (0.79) design and a low throat Mach number (0.60) design, were tested with four diffuser acoustical treatment designs that had face sheet porosity ranging from 0 to 24 percent for the high Mach number inlet and 0 to 28 percent for the low Mach number inlet. The tests were conducted in a low speed wind tunnel at free stream velocities of 0, 41, and 62 m/sec and angles of attack to 50 deg. Inlet throat Mach number was varied about the design value. Increasing the inlet diffuser face sheet porosity resulted in an increase in total pressure loss in the boundary layer for both the high and low Mach number inlet designs, however, the overall effect on inlet total pressure recovery of 0.991 at the design throat Mach number, a free stream velocity of 41 m/sec, and an angle of attack of 50 deg; Inlet flow separation at an angle of attack of 50 deg was encountered with only one inlet configuration the high Mach number design with the highest diffuser face sheet porosity (24 percent).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1178 , E-9542
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  • 26
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    Quiet Clean Short-Haul Experimental Engine (QCSEE) ball spline pitch-change mechanism whirligig test report (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The component testing of a ball spline variable pitch mechanism is described including a whirligig test. The variable pitch actuator successfully completed all planned whirligig tests including a fifty cycle endurance test at actuation rates up to 125 deg per second at up to 102 percent fan speed (3400 rpm).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135354 , R77AEG394
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  • 27
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    Program for impact testing of spar-shell fan blades, test report (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Six filament-wound, composite spar-shell fan blades were impact tested in a whirligig relative to foreign object damage resulting from ingestion of birds into the fan blades of a QCSEE-type engine. Four of the blades were tested by injecting a simulated two pound bird into the path of the rotating blade and two were tested by injecting a starling into the path of the blade.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135393 , R78AEG444
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  • 28
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    Quiet Clean Short-haul Experimental Engine (QCSEE) over-the-wing engine and control simulation results (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A hybrid-computer simulation of the over the wing turbofan engine was constructed to develop the dynamic design of the control. This engine and control system includes a full authority digital electronic control using compressor stator reset to achieve fast thrust response and a modified Kalman filter to correct for sensor failures. Fast thrust response for powered-lift operations and accurate, fast responding, steady state control of the engine is provided. Simulation results for throttle bursts from 62 to 100 percent takeoff thrust predict that the engine will accelerate from 62 to 95 percent takeoff thrust in one second.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135049 , R76AEG218
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  • 29
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    Quiet Clean Short-haul Experimental Engine (QCSEE) under-the-wing engine digital control system design report (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digital electronic control was combined with conventional hydromechanical components to operate the four controlled variables on the under-the-wing engine: fuel flow, fan blade pitch, fan exhaust area, and core compressor stator angles. The engine and control combination offers improvements in noise, pollution, thrust response, operational monitoring, and pilot workload relative to current engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134920 , R75AEG483
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  • 30
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    Quiet Clean Short-Haul Experimental Engine (QCSEE) Over-The Wing (OTW) propulsion system test report. Volume 3: Mechanical performance (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The mechanical performance of the over-the-wing engine is described with emphasis on the advanced technology components. The overall dynamic response of the engine was excellent.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135325 , R77AEG475-VOL-3
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  • 31
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    Quiet Clean Short-Haul Experimental Engine (QCSEE) Over-The-Wing (OTW) propulsion system test report. Volume 1: Summary report (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Sea level, static, ground testing of the over-the-wing engine and boilerplate nacelle components was performed. The equipment tested and the test facility are described. Summaries of the instrumentations, the chronological history of the tests, and the test results are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135323 , R77AEG473-VOL-1
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  • 32
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    Quiet Clean Short-haul Experimental Engine (QCSEE) Under-The-Wing (UTW) composite nacelle (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The detail design of the under the wing experimental composite nacelle components is summarized. Analysis of an inlet, fan bypass duct doors, core cowl doors, and variable fan nozzle are given. The required technology to meet propulsion system performance, weight, and operational characteristics is discussed. The materials, design, and fabrication technology for quiet propulsion systems which will yield installed thrust to weight ratios greater than 3.5 to 1 are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135352 , R77AEG588
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  • 33
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    Quiet Clean Short-haul Experimental Engine (QCSEE) composite fan frame design report (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An advanced composite frame which is flight-weight and integrates the functions of several structures was developed for the over the wing (OTW) engine and for the under the wing (UTW) engine. The composite material system selected as the basic material for the frame is Type AS graphite fiber in a Hercules 3501 epoxy resin matrix. The frame was analyzed using a finite element digital computer program. This program was used in an iterative fashion to arrive at practical thicknesses and ply orientations to achieve a final design that met all strength and stiffness requirements for critical conditions. Using this information, the detail design of each of the individual parts of the frame was completed and released. On the basis of these designs, the required tooling was designed to fabricate the various component parts of the frame. To verify the structural integrity of the critical joint areas, a full-scale test was conducted on the frame before engine testing. The testing of the frame established critical spring constants and subjected the frame to three critical load cases. The successful static load test was followed by 153 and 58 hours respectively of successful running on the UTW and OTW engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135278 , R77AEG439
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  • 34
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    Quiet Clean Short-haul Experimental Engine (QCSEE). Ball spline pitch change mechanism design report (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Detailed design parameters are presented for a variable-pitch change mechanism. The mechanism is a mechanical system containing a ball screw/spline driving two counteracting master bevel gears meshing pinion gears attached to each of 18 fan blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134873 , R77AEG327
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  • 35
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    Study of turboprop systems reliability and maintenance costs (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall reliability and maintenance costs (R&MC's) of past and current turboprop systems were examined. Maintenance cost drivers were found to be scheduled overhaul (40%), lack of modularity particularly in the propeller and reduction gearbox, and lack of inherent durability (reliability) of some parts. Comparisons were made between the 501-D13/54H60 turboprop system and the widely used JT8D turbofan. It was found that the total maintenance cost per flight hour of the turboprop was 75% higher than that of the JT8D turbofan. Part of this difference was due to propeller and gearbox costs being higher than those of the fan and reverser, but most of the difference was in the engine core where the older technology turboprop core maintenance costs were nearly 70 percent higher than for the turbofan. The estimated maintenance cost of both the advanced turboprop and advanced turbofan were less than the JT8D. The conclusion was that an advanced turboprop and an advanced turbofan, using similar cores, will have very competitive maintenance costs per flight hour.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135192 , EDR-9132
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  • 36
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    Quiet Clean Short-Haul Experimental Engine (QCSEE) Over-The-Wing (OTW) propulsion system test report. Volume 2: Aerodynamics and performance (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design and testing of the over the wing engine, a high bypass, geared turbofan engine, are discussed. The propulsion system performance is examined for uninstalled performance and installed performance. The fan aerodynamic performance and the D nozzle and reverser thrust performance are evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135324 , R77AEG474-VOL-2
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  • 37
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    Quiet Clean Short-Haul Experimental Engine (QCSEE) Under-The-Wing (UTW) graphite/PMR cowl development (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The PMR process development, tooling concepts, testing conducted to generate materials properties data, and the fabrication of a subscale model of the inner cowl are presented. It was concluded that the materials, processes, and tooling concepts were satisfactory for making an inner cowl with adequate structural integrity.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135279 , R78AEG206
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  • 38
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    Quiet, Clean, Short-Haul Experimental Engine (QCSEE) Over-The-Wing (OTW) engine acoustic design (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The acoustic considerations involved in the low source noise basic engine design and the design procedures followed in the development of the over-the-wing (OTW) nacelle acoustic treatment design are presented. Laboratory experiments, component tests, and scale model and engine tests supporting the OTW engine acoustic design are referenced. Acoustic design features include a near-sonic inlet, low fan and core pressure ratios, low fan tip speed, high and low frequency stacked core treatment, multiple thickness treatment, and fan frame and stator vane treatment.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135268 , R76AEG228
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  • 39
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    Quiet, Clean, Short-Haul, Experimental Engine (QCSEE) Under-The-Wing (UTW) engine acoustic design (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The acoustic considerations involved in the low source noise basic engine design and the design procedures followed in the development of the under-the-wing (UTW) engine boilerplate and composite nacelle acoustic treatment designs are presented. Laboratory experiments, component tests, and scale model and engine tests supporting the UTW engine acoustic design are referenced. Acoustic design features include a near-sonic inlet, low fan and core pressure ratios, low fan tip speed, high and low frequency stacked core treatment, multiple thickness treatment, and fan frame and stator vane treatment.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135267 , R76AEG195
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  • 40
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    Quiet Clean Short-Haul Experimental Engine (QCSEE) acoustic and aerodynamic tests on a scale model over-the-wing thrust reverser and forward thrust nozzle (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An acoustic and aerodynamic test program was conducted on a 1/6.25 scale model of the Quiet, Clean, Short-Haul Experimental Engine (QCSEE) forward thrust over-the-wing (OTW) nozzle and OTW thrust reverser. In reverse thrust, the effect of reverser geometry was studied by parametric variations in blocker spacing, blocker height, lip angle, and lip length. Forward thrust nozzle tests determined the jet noise levels of the cruise and takeoff nozzles, the effect of opening side doors to achieve takeoff thrust, and scrubbing noise of the cruise and takeoff jet on a simulated wing surface. Velocity profiles are presented for both forward and reverse thrust nozzles. An estimate of the reverse thrust was made utilizing the measured centerline turning angle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135254 , R75AEG504
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  • 41
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    Investigation of blade flutter of axial compressors by the discrete-phase method (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AD-A066464 , FTD-ID(RS)T-0860-78
    Format: text
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  • 42
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    Redundant disc (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A rotatable disc is described that consists of parallel plates tightly joined together for rotation about a hub. Each plate is provided with several angularly projecting spaced lands. The lands of each plate are interposed in alternating relationship between the lands of the next adjacent plate. In this manner, circumferential displacement of adjacent sectors in any one plate is prevented in the event that a crack develops. Each plate is redundantly sized so that, in event of structural failure of one plate, the remaining plates support a proportionate share of the load of the failed plate. The plates are prevented from separating laterally through the inclusion of generally radially extending splines which are inserted to interlock cooperating, circumferentially adjacent lands.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 43
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    Blade row dynamic digital compression program. Volume 2: J85 circumferential distortion redistribution model, effect of Stator characteristics, and stage characteristics sensitivity study (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of dynamic digital blade row compressor model studies of a J85-13 engine are reported. The initial portion of the study was concerned with the calculation of the circumferential redistribution effects in the blade-free volumes forward and aft of the compression component. Although blade-free redistribution effects were estimated, no significant improvement over the parallel-compressor type solution in the prediction of total-pressure inlet distortion stability limit was obtained for the J85-13 engine. Further analysis was directed to identifying the rotor dynamic response to spatial circumferential distortions. Inclusion of the rotor dynamic response led to a considerable gain in the ability of the model to match the test data. The impact of variable stator loss on the prediction of the stability limit was evaluated. An assessment of measurement error on the derivation of the stage characteristics and predicted stability limit of the compressor was also performed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134953 , R76AEG484-VOL-2
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  • 44
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    Pollution Reduction Technology Program for Small Jet Aircraft Engines, Phase 2 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A series of iterative combustor pressure rig tests were conducted on two combustor concepts applied to the AiResearch TFE731-2 turbofan engine combustion system for the purpose of optimizing combustor performance and operating characteristics consistant with low emissions. The two concepts were an axial air-assisted airblast fuel injection configuration with variable-geometry air swirlers and a staged premix/prevaporization configuration. The iterative rig testing and modification sequence on both concepts was intended to provide operational compatibility with the engine and determine one concept for further evaluation in a TFE731-2 engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159415 , AIRESEARCH-21-2817
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  • 45
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    Large scale static tests of a tilt-nacelle V/STOL propulsion/attitude control system (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The concept of a combined V/STOL propulsion and aircraft attitude control system was subjected to large scale engine tests. The tilt nacelle/attitude control vane package consisted of the T55 powered Hamilton Standard Q-Fan demonstrator. Vane forces, moments, thermal and acoustic characteristics as well as the effects on propulsion system performance were measured under conditions simulating hover in and out of ground effect.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-152181 , PDR-698-8
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  • 46
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    Aircraft gas turbine low-power emissions reduction technology program (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Advanced aircraft turbine engine combustor technology was used to reduce low-power emissions of carbon monoxide and unburned hydrocarbons to levels significantly lower than those which were achieved with current technology. Three combustor design concepts, which were designated as the hot-wall liner concept, the recuperative-cooled liner concept, and the catalyst converter concept, were evaluated in a series of CF6-50 engine size 40 degree-sector combustor rig tests. Twenty-one configurations were tested at operating conditions spanning the design condition which was an inlet temperature and pressure of 422 K and 304 kPa, a reference velocity of 23 m/s and a fuel-air-ration of 10.5 g/kg. At the design condition typical of aircraft turbine engine ground idle operation, the best configurations of all three concepts met the stringent emission goals which were 10, 1, and 4 g/kg for CO, HC, and Nox, respectively.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135434 , DOC-R78AEG408
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  • 47
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    Analysis of metal temperature and coolant flow with a thermal-barrier coating on a full-coverage-film-cooled turbine vane (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The potential benefits of combining full-coverage film cooling with a thermal-barrier coating were investigated analytically for sections on the suction and pressure sides a high-temperature, high-pressure turbine vane. Metal and ceramic coating temperatures were calculated as a function of coating thickness and coolant flow. With a thermal-barrier coating, the coolant flows required for the chosen sections were half those of an uncoated design, and the metal outer temperatures were simultaneously reduced by over 111 K (200 F). For comparison, transpiration cooling was also investigated. Full-coverage film cooling of a coated vane required more coolant flow than did transpiration cooling.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1310 , AVRADCOM-TR-78-20
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  • 48
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    Advanced optical blade tip clearance measurement system (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An advanced electro-optical system was developed to measure single blade tip clearances and average blade tip clearances between a rotor and its gas path seal in an operating gas turbine engine. This system is applicable to fan, compressor, and turbine blade tip clearance measurement requirements, and the system probe is particularly suitable for operation in the extreme turbine environment. A study of optical properties of blade tips was conducted to establish measurement system application limitations. A series of laboratory tests was conducted to determine the measurement system's operational performance characteristics and to demonstrate system capability under simulated operating gas turbine environmental conditions. Operational and environmental performance test data are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159402 , FR-10200A
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  • 49
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    F-15 inlet engine test techniques and distortion methodologies studies. Volume 9: Stability audits (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Stability audit plots were used to determine if peak distortion data taken from a subscale inlet model can be used to predict peak distortion levels for a full scale flight test vehicle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-144874
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  • 50
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    F-15 inlet/engine test techniques and distortion methodologies studies. Volume 5: Effect of filter cutoff frequency on turbulence plots (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of filter cutoff frequency on turbulence plots were used to determine if peak distortion data taken from a subscale inlet model can be used to predict peak distortion levels for a full scale flight test vehicle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-144870
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  • 51
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    Acoustic tests of duct-burning turbofan jet noise simulation: Comprehensive data report. Volume 2: Model design and aerodynamic test results (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The selection procedure is described which was used to arrive at the configurations tested, and the performance characteristics of the test nozzles are given.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135239-VOL-2
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  • 52
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    Experimental study of the effect of cycle pressure on lean combustion emissions (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experiments were conducted in which a stream of premixed propane and air was burned under conditions representative of gas turbine operation. Emissions of NOx, CO, and unburned hydrocarbons (UHC) were measured over a range of combustor inlet temperature, pressure, and residence time at equivalence ratios from 0.7 down to the lean stability limit. At an inlet temperature of 600 K, observed NOx levels dropped markedly with decreasing pressure for pressures below 20 atm. The NOx levels are proportional to combustor residence time and formation rates were principally a function of adiabatic flame temperature. For adiabatic flame temperatures of 2050 K and higher, CO reached chemical equilibrium within 2 msec. Unburned hydrocarbon species dropped to a negligible level within 2 msec regardless of inlet temperature, pressure, or equivalence ratio. For a combustor residence time of 2.5 msec, combustion inefficiency became less than 0.01% at an adiabatic flame temperature of 2050 K. The maximum combustion inefficiency observed was on the order of 1% and corresponded to conditions near the lean stability limit. Using a perforated plate flameholder, this limit is well represented by the condition of 1800 K adiabatic flame temperature.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-3032 , GASL-TR-248
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  • 53
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    Acoustic tests of duct-burning turbofan jet noise simulation: Comprehensive data report. Volume 1, section 2: Full size data (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Acoustic data are presented scaled to a full size engine by a factor of 8 on a 96.9 m (320 ft) arc and a 731.5 m (2400 ft) sideline.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135239-VOL-1-SECT-2
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  • 54
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    FORTRAN program for calculating coolant flow and metal temperatures of a full-coverage-film-cooled vane or blade (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program that calculates the coolant flow and the metal temperatures of a full-coverage-film-cooled vane or blade was developed. The analysis was based on compressible, one-dimensional fluid flow and on one-dimensional heat transfer and treats the vane or blade shell as a porous wall. The calculated temperatures are average values for the shell outer-surface area associated with each film-cooling hole row. A thermal-barrier coating may be specified on the shell outer surface, and centrifugal effects can be included for blade calculations. The program is written in FORTRAN 4 and is operational on a UNIVAC 1100/42 computer. The method of analysis, the program input, the program output, and two sample problems are provided.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1259 , E-9491 , AVRADCOM-TR-78-19(PL)
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  • 55
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    Acoustic tests of duct-burning turbofan jet noise simulation: Comprehensive data report. Volume 1, section 3: Data plots (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Acoustic data plots are presented which were obtained in the tests on scale nozzles for use on duct-burning turbofan engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135239-VOL-1-SECT-3
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  • 56
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    Acoustic tests of duct-burning turbofan jet noise simulation: Comprehensive data report. Volume 1, section 1: Model scale data (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Model scale data on a 12.2 m (40 ft) arc are presented which were obtained in the hot, static acoustic tests on eleven nozzle designs suitable for use on duct-burning turbofan engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135239-VOL-1-SECT-1
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  • 57
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    Performance of a short annular dump diffuser using suction-stabilized vortices at inlet Mach numbers to 0.41 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A short, annular dump diffuser was designed to use suction to establish stabilized vortices on both walls for improved flow expansion in the region of an abrupt area change. The diffuser was tested at near ambient inlet pressure and temperature. The overall diffuser area ratio was 4.0. The inlet height was 2.54 cm and the exit pitot-static rakes were located at a distance from the vortex fence equal to two or six times the inlet height. Performance data were taken at near ambient temperature and pressure for nominal inlet Mach numbers of 0.18 to 0.41 with suction rates of 0 to 18 percent of the total inlet airflow. The exit velocity profile could be shifted toward either wall by adjusting the inner- or outer-wall suction rate. Symmetrical exit velocity profiles were unstable, with a tendency to shift back to hub- or tip-weighted profile. Diffuser effectiveness was increased from about 47 percent without suction to over 85 percent at a total suction rate of about 14 percent. The diffuser total pressure losses at inlet Mach numbers of 0.18 and 0.41 decreased from 1.1 and 5.6 percent without suction to 0.48 and 5.2 percent at total suction rates of 14.4 and 5.6 percent, respectively.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1194 , E-9332
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  • 58
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    Experimental determination of transient strain in a thermally-cycled simulated turbine blade utilizing a non-contact technique (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A type of noncontacting electro-optical extensometer was used to measure the displacement between parallel targets mounted on the leading edge of a simulated turbine blade throughout a complete heating and cooling cycle. The blade was cyclically heated and cooled by moving it into and out of a Mach 1 hot gas stream. The principle of operation and measurement procedure of the electro-optics extensometer are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-73886 , E-9500
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  • 59
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    Effects of film injection on performance of a cooled turbine (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted in a 20 inch diameter single stage air cooled turbine designed to evaluate the effects of film cooling air on turbine aerodynamic performance. A comparison was made of the experimental results and an analytical method of evaluating film injection effects on turbine performance. The results are used to determine the effects of film cooling on overall engine performance for selected cycle conditions. The engine performance studies are used to show the cycle benefits of increased gas temperature at various coolant flow rates.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD High Temp. Probl. in Gas Turbine Eng.; 11 p
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  • 60
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    Nitric oxide formation in gas turbine engines: A theoretical and experimental study (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A modified Zeldovich kinetic scheme was used to predict nitric oxide formation in the burned gases. Nonuniformities in fuel-air ratio in the primary zone were accounted for by a distribution of fuel-air ratios. This was followed by one or more dilution zones in which a Monte Carlo calculation was employed to follow the mixing and dilution processes. Predictions of NOX emissions were compared with various available experimental data, and satisfactory agreement was achieved. In particular, the model is applied to the NASA swirl-can modular combustor. The operating characteristics of this combustor which can be inferred from the modeling predictions are described. Parametric studies are presented which examine the influence of the modeling parameters on the NOX emission level. A series of flow visualization experiments demonstrates the fuel droplet breakup and turbulent recirculation processes. A tracer experiment quantitatively follows the jets from the swirler as they move downstream and entrain surrounding gases. Techniques were developed for calculating both fuel-air ratio and degree of nonuniformity from measurements of CO2, CO, O2, and hydrocarbons. A burning experiment made use of these techniques to map out the flow field in terms of local equivalence ratio and mixture nonuniformity.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-2977
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  • 61
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    Theoretical flow characteristics of inlets for tilting-nacelle VTOL aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a theoretical investigation of geometric variables for lift-cruise-fan, tilting nacelle inlets operating at high incidence angles are presented. These geometric variables are investigated for their effects on surface static to free stream pressure ratio, and the separation parameters of maximum to diffuser exit surface velocity ratio and maximum surface Mach number for low speed operating conditions. The geometric parameters varied were the internal lip contraction ratio, external forebody to diffuser exit diameter ratio external forebody length to diameter ratio and internal lip major to minor axis ratio.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1205 , E-9387
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  • 62
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    Flow visualization of film cooling with spanwise injection from a small array of holes and compound-angle injection from a large array (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Film injection from discrete holes in a smooth, flat plate was studied for two configurations: (1) spanwise injection through a four hole staggered array; and (2) compound angle injection through a 49 hole staggered array. The ratio of boundary layer thicknesses to hole diameter and the Reynolds number were typical of gas turbine film cooling applications. Streaklines showing the motion of the injected air were obtained by photographing small, neutrally buoyant, helium-filled soap bubbles that followed the flow field.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1195 , E-9340
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  • 63
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    Airflow and thrust calibration of an F100 engine, S/N P680059, at selected flight conditions (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An airflow and thrust calibration of an F100 engine, S/N P680059, was conducted to study airframe propulsion system integration losses in turbofan-powered high-performance aircraft. The tests were conducted with and without thrust augmentation for a variety of simulated flight conditions with emphasis on the transonic regime. The resulting corrected airflow data generalized into one curve with corrected fan speed while corrected gross thrust increased as simulated flight conditions increased. Overall agreement between measured data and computed results was 1 percent for corrected airflow and -1 1/2 percent for gross thrust. The results of an uncertainty analysis are presented for both parameters at each simulated flight condition.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1069 , E-9257
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  • 64
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    Comparison of the noise characteristics of two low pressure ratio fans with a high throat Mach number inlet (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Acoustics data obtained in experiments with two low pressure ratio 50.8 cm (20 in.) diameter model fans differing in design tip speed were compared. Determination of the average throat Mach number used to compare high Mach inlet noise reduction characteristics was based on a correlation of inlet wall static pressure measurements with a flow field calculation. The largest noise reductions were generally obtained with the higher tip speed fan. At a throat Mach number of 0.79, the difference in noise reduction was about 3.5 db with static test conditions. Although the noise reduction increased for the lower tip speed fan with a simulated flight velocity of 41 m/sec (80 knots), it was still about 2 db less than that of the high tip speed fan which was only tested at the static condition. However, variations in acoustic performance could not be absolutely attributed to the different fan designs because of differences in inlet lip contours which resulted in small variations of peak wall Mach number and axial extend of supersonic and near-sonic flow.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-73880 , E-9489
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  • 65
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    Rectangular capture area to circular combustor scramjet engine (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A new concept for a scramjet engine design was presented. The inlet transformed a rectangular shaped capture stream into a cross section which was almost circular in shape at the inlet throat or combustor entrance. The inlet inner surface was designed by the method of streamline tracing. The high pressure and temperature regions of the combustor were almost circular in shape and thus the benefits of hoop stresses in relation to structural weight could be utilized to reduce combustor and engine weights. The engine had a center body consisting of a 20 deg included angle cone, followed by a constant diameter cylinder. Fuel injection struts were arranged in a radial array and were swept 54 deg from the center body to the inlet inner surface and had values of length to maximum average thickness between 5.6and 6.6 which were felt to be structurally reasonable. Combustor wetted areas were shown to be less than those of the present fully rectangular engine concept.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78657
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  • 66
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    Low speed test of a high-bypass-ratio propulsion system with an asymmetric inlet designed for a tilt-nacelle V/STOL airplane (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A large scale model of a lift/cruise fan inlet designed for a tilt nacelle V/STOL airplane was tested with a high bypass ratio turbofan. Testing was conducted at low freestream velocities with inlet angles of attack ranging from 0 deg to 120 deg. The operating limits for the nacelle were found to be related to inlet boundary layer separation. Small separations originating in the inlet diffuser cause little or no performance degradation. However, at sufficiently severe freestream conditions the separation changes abruptly to a lip separation. This change is associated with a significant reduction in nacelle net thrust as well as a sharp increase in fan blade vibratory stresses. Consequently, the onset of lip separation is regarded as the nacelle operating limit. The test verified that the asymmetric inlet design will provide high performance and stable operation at the design forward speed and angle of attack conditions. At some of these, however, operation near the lower end of the design inlet airflow range is not feasible due to the occurrence of lip separation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-152072 , D-180-22888-1
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  • 67
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    Internal performance predictions for Langley scramjet engine module (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A one dimensional theoretical method for the prediction of the internal performance of a scramjet engine is presented. The effects of changes in vehicle forebody flow parameters and characteristics on predicted thrust for the scramjet engine were evaluated using this method, and results are presented. A theoretical evaluation of the effects of changes in the scramjet engine's internal parameters is also presented. Theoretical internal performance predictions, in terms thrust coefficient and specific impulse, are provided for the scramjet engine for free stream Mach numbers of 5, 6, and 7 free stream dynamic pressure of 23,940 N/sq m forebody surface angles of 4.6 deg to 14.6 deg, and fuel equivalence ratio of 1.0.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-74038
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  • 68
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    Gas turbine engine with convertible accessories (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Drive means for connecting a gas turbine engine to its accessories are so constructed as to allow the accessories to be selectively positioned to any one of several predetermined circumferential positions about the perimeter of the engine. This feature permits convenient mounting of the same engine upon vehicles demanding radically different engine mounting arrangements.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 69
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    Variable thrust nozzle for quiet turbofan engine and method of operating same (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An improved method of operating a gas turbine engine is presented wherein engine-generated noise is maintained at a reduced level during reduced thrust operation. Fan speed was maintained at a constant level while fan nozzle area was increased. This maintained high inlet Mach numbers for reduced forward noise propagation and also permited reduced nozzle exhaust velocity for reduced shear noise. In another embodiment, airflow was increased by means of a fan blade pitch change or speed increase while the fan nozzle area was increased, yielding both a net reduction in engine thrust and noise.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 70
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    An analytical study of thermal barrier coated first stage blades in a JT9D engine (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Steady state and transient heat transfer and structural calculations were completed to determine the coating and base alloy temperatures and strains. Results indicate potential for increased turbine life using thin durable thermal barrier coatings on turbine airfoils due to a significant reduction in blade average and maximum temperatures, and alloy strain range. An intepretation of the analytical results is compared to the experimental engine test data.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135360 , PWA-5590
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  • 71
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    Cold-air performance of free-power turbine designed for 112-kilowatt automotive gas-turbine engine. 1: Design Stator-vane-chord setting angle of 35 deg (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A cold air experimental investigation of a free power turbine designed for a 112-kW automotive gas-turbine was made over a range of speeds from 0 to 130 percent of design equivalent speeds and over a range of pressure ratio from 1.11 to 2.45. Results are presented in terms of equivalent power, torque, mass flow, and efficiency for the design power point setting of the variable stator.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1007 , CONS/1011-12 , E-8964
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  • 72
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    Filament-winding fabrication of QCSEE configuration fan blades (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design and fabrication of twelve NASA-QCSEE type composite fan blades utilizing wet filament winding fabrication techniques is described. All composite fibers were continuous and attached to the root end. All components were formed, bonded, and co-cured in one molding process. Advanced fiber materials used in the blade fabrication were Thornel-300, Carbolon Z-2-1, and Carbolon Z-3 graphite in an epoxy resin matrix.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135332
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  • 73
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    F-15 inlet/engine test techniques and distortion methodologies studies. Volume 3: Power spectral density plots (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Power spectral density plots were used to determine if peak distortion data taken from a subscale inlet model can be used to predict peak distortion levels for a full scale flight test vehicle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-144868
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  • 74
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    Computer Program for the Design and Off-Design Performance of Turbojet and Turbofan Engine Cycles (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The rapid computer program is designed to be run in a stand-alone mode or operated within a larger program. The computation is based on a simplified one-dimensional gas turbine cycle. Each component in the engine is modeled thermo-dynamically. The component efficiencies used in the thermodynamic modeling are scaled for the off-design conditions from input design point values using empirical trends which are included in the computer code. The engine cycle program is capable of producing reasonable engine performance prediction with a minimum of computer execute time. The current computer execute time on the IBM 360/67 for one Mach number, one altitude, and one power setting is about 0.1 seconds. about 0.1 seconds. The principal assumption used in the calculation is that the compressor is operated along a line of maximum adiabatic efficiency on the compressor map. The fluid properties are computed for the combustion mixture, but dissociation is not included. The procedure included in the program is only for the combustion of JP-4, methane, or hydrogen.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78653
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  • 75
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    Long-term CF6 engine performance deterioration: Evaluation of engine S/N 451-479 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The performance testing and analytical teardown of CF6-6D engine is summarized. This engine had completed its initial installation on DC-10 aircraft. The investigative test program was conducted inbound prior to normal overhaul/refurbishment. The performance testing included an inbound test, a test following cleaning of the low pressure turbine airfoils, and a final test after leading edge rework and cleaning the stage one fan blades. The analytical teardown consisted of detailed disassembly inspection measurements and airfoil surface finish checks of the as received deteriorated hardware. Included in this report is a detailed analysis of the test cell performance data, a complete analytical teardown report with a detailed description of all observed hardware distress, and an analytical assessment of the performance loss (deterioration) relating measured hardware conditions to losses in both SFC (specific fuel consumption) and EGT (exhaust gas temperature).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135381
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  • 76
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    DYGABCD: A program for calculating linear A, B, C, and D matrices from a nonlinear dynamic engine simulation (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digital computer program, DYGABCD, was developed that generates linearized, dynamic models of simulated turbofan and turbojet engines. DYGABCD is based on an earlier computer program, DYNGEN, that is capable of calculating simulated nonlinear steady-state and transient performance of one- and two-spool turbojet engines or two- and three-spool turbofan engines. Most control design techniques require linear system descriptions. For multiple-input/multiple-output systems such as turbine engines, state space matrix descriptions of the system are often desirable. DYGABCD computes the state space matrices commonly referred to as the A, B, C, and D matrices required for a linear system description. The report discusses the analytical approach and provides a users manual, FORTRAN listings, and a sample case.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1295 , E-9464
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  • 77
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    F-15 inlet/engine test techniques and distortion methodologies studies. Volume 7: Cross correlation functions. (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Cross correlation function plots were used to determine if peak distortion data taken from a subscale inlet model can be used to predict peak distortion levels for a full scale flight test vehicle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-144872
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  • 78
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    Short-term performance deterioration in JT9D-7A(SP) engine 695743 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The level of performance deterioration that occurred during early service was studied and also the contribution of each engine module to the overall level of engine performance deterioration. To assist in the distribution of the performance losses to the module level, testing with expanded experimental instrumentation was accomplished to permit direct measurement of module performance. An analytical teardown of the engine was accomplished to permit assignment of module performance losses to individual mechanical damage mechanisms including blade and seal wear, roughness, and thermal distortion of turbine parts. The results of the testing show that the engine deteriorated 1.5 percent in thrust specific fuel consumption from its performance when new. Initial testing, which included water washing, showed that 0.2 percent in performance deterioration was due to surface contamination (dirt) and 0.1 percent was due to drift of the engine vane control system, leaving 1.2 percent in basic TSFC deterioration. This 1.2 percent TSFC loss was distributed among the engine modules with 0.6 percent caused by clearance changes, 0.4 percent loss due to thermal distortion, and 0.2 percent loss due to increased roughness of the fan and low-pressure compressor airfoils.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135431 , PWA-5512-17
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  • 79
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    F-15 inlet/engine test techniques and distortion methodologies studies. Volume 2: Time variant data quality analysis plots (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Time variant data quality analysis plots were used to determine if peak distortion data taken from a subscale inlet model can be used to predict peak distortion levels for a full scale flight test vehicle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-144867
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  • 80
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    Design of impact-resistant boron/aluminum large fan blade (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The technical program was comprised of two technical tasks. Task 1 encompassed the preliminary boron/aluminum fan blade design effort. Two preliminary designs were evolved. An initial design consisted of 32 blades per stage and was based on material properties extracted from manufactured blades. A final design of 36 blades per stage was based on rule-of-mixture material properties. In Task 2, the selected preliminary blade design was refined via more sophisticated analytical tools. Detailed finite element stress analysis and aero performance analysis were carried out to determine blade material frequencies and directional stresses.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135417
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  • 81
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    Propulsion/flight control integration technology (PROFIT) design analysis status (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The propulsion flight control integration technology (PROFIT) program was designed to develop a flying testbed dedicated to controls research. The preliminary design, analysis, and feasibility studies conducted in support of the PROFIT program are reported. The PROFIT system was built around existing IPCS hardware. In order to achieve the desired system flexibility and capability, additional interfaces between the IPCS hardware and F-15 systems were required. The requirements for additions and modifications to the existing hardware were defined. Those interfaces involving the more significant changes were studied. The DCU memory expansion to 32K with flight qualified hardware was completed on a brassboard basis. The uplink interface breadboard and a brassboard of the central computer interface were also tested. Two preliminary designs and corresponding program plans are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-144875
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  • 82
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    Long-term CF6 engine performance deterioration: Evaluation of engine S/N 451-380 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The performance testing and analytical teardown of CF6-6D engine serial number 451-380 which was recently removed from a DC-10 aircraft is summarized. The investigative test program was conducted inbound prior to normal overhaul/refurbishment. The performance testing included an inbound test, a test following cleaning of the low pressure turbine airfoils, and a final test after leading edge rework and cleaning the stage one fan blades. The analytical teardown consisted of detailed disassembly inspection measurements and airfoil surface finish checks of the as-received deteriorated hardware. Aspects discussed include the analysis of the test cell performance data, a complete analytical teardown report with a detailed description of all observed hardware distress, and an analytical assessment of the performance loss (deterioration) relating measured hardware conditions to losses in both specific fuel comsumption and exhaust gas temperature.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159390
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  • 83
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    Effect of Air Temperature and Relative Humidity at Various Fuel-Air Ratios on Exhaust Emissions on a Per-Mode Basis of an AVCO Lycoming 0-320 Diad Light Aircraft Engine: Volume 1: Results and Plotted Data (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A carbureted four cylinder air cooled 0-320 DIAD Lycoming aircraft engine was tested to establish the effects of air temperature and humidity at various fuel-air ratios on the exhaust emissions on a per-mode basis. The test conditions include carburetor lean out at air temperatures of 50, 59, 80, and 100 F at relative humidities of 0, 30, 60, and 80 percent. Temperature humidity effects at the higher values of air temperature and relative humidity tested indicated that the HC and CO emissions increased significantly, while the NOx emissions decreased. Even at a fixed fuel air ratio, the HC emissions increase and the NOx emissions decrease at the higher values of air temperature and humidity.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-73507-VOL-1 , E-8916-2
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  • 84
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    Reverse-flow combustor for small gas turbines with pressure-atomizing fuel injectors (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A reverse flow combustor suitable for a small gas turbine (2 to 3 kg/s mass flow) was used to evalute the effect of pressure atomizing fuel injectors on combustor performance. In these tests an experimental combustor was designed to operate with 18 simplex pressure atomizing fuel injectors at sea level takeoff conditions. To improve performance at low power conditions, fuel was redistributed so that only every other injector was operational. Combustor performance, emissions, and liner temperature were compared over a range of pressure and inlet air temperatures corresponding to simulated idle, cruise, and takeoff conditions typical of a 16 to 1 pressure ratio turbine engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1260 , AVRADCOM-TR-78-22(PL) , E-9458
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  • 85
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    Fabrication and test of digital output interface devices for gas turbine electronic controls (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A program was conducted to develop an innovative digital output interface device, a digital effector with optical feedback of the fuel metering valve position, for future electronic controls for gas turbine engines. A digital effector (on-off solenoids driven directly by on-off signals from a digital electronic controller) with optical position feedback was fabricated, coupled with the fuel metering valve, and tested under simulated engine operating conditions. The testing indicated that a digital effector with optical position feedback is a suitable candidate, with proper development for future digital electronic gas turbine controls. The testing also identified several problem areas which would have to be overcome in a final production configuration.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135427 , PWA-5544-13
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  • 86
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    Prop-fan data support study (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Updated parametric prop-fan data packages are presented and the rationale used in developing the new prop-fan data is detailed. These data represent Hamilton Standard's projections of prop-fan characteristics for aircraft that are expected to be in-service in the 1985 to 1990 time frame. The basic prop-fan configuration was designed for efficient cruise operation at 0.8 Mach number and 10,668M altitude. The design blade tip speed is 244 mps and the design power loading is 301 KW/M squared.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-152141
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  • 87
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    Two dimensional wedge/translating shroud nozzle (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A jet propulsion exhaust nozzle is reported for multi-engine installations which produces high internal/external, thrust-minus-drag, performance for transonic cruise or transonic acceleration as well as improved performance at subsonic and supersonic speeds. A two dimensional wedge/translating shroud provides the variable nozzle exit geometry needed to achieve high engine performance over a wide range of throttle power settings.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 88
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    JT9D jet engine performance deterioration (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analytical techniques utilized to examine the effects of flight loads and engine operating conditions on performance deterioration are presented. The role of gyroscopic, gravitational, and aerodynamic loads are shown along with the effect of variations in engine build clearances. These analytical results are compared to engine test data along with the correlation between analytically predicted and measured clearances and rub patterns. Conclusions are drawn and important issues are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 45-58
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  • 89
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    CF6 jet engine performance deterioration results (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of the performance baseline from the flight planning manual as a reference to measure changes in cruise fuel flow rates was discussed. For the CF6-6D engine, the introduction of design changes for performance and durability reasons was seen to introduce an average increment relative to this baseline of 3.2% WFM increase at Nl, 2.5% Fn increase at Nl, 0.8% specific fuel consumption (SFC) increase at Fn, and 7 C EGT increase at Nl, while maintaining sufficient SFC margin of the delivered airplane. The effect of revenue service deterioration and performance restoration relative to the reference was shown to be an adder on top of these design effects. A schematic of typical CF6-6D performance through revenue service and airline maintenance is presented in terms of percent cruise SFC relative to an airline datum point (average level upon entering revenue service). The typical changes in SFC margin are shown for airline revenue service through for installations and refurbishments.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 25-44
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  • 90
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    Flight effects on noise by the JT8D engine with inverted primary/fan flow as measured in the NASA-Ames 40 by 80 foot wind tunnel (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A JT8D-17R engine with inverted primary and fan flows was tested under static conditions as well as in the NASA Ames 40 by 80 Foot Wind Tunnel to determine static and flight noise characteristics, and flow profile of a large scale engine. Test and analysis techniques developed by a previous model and JT8D engine test program were used to determine the in-flight noise. The engine with inverted flow was tested with a conical nozzle and with a plug nozzle, 20 lobe nozzle, and an acoustic shield. Wind tunnel results show that forward velocity causes significant reduction in peak PNL suppression relative to uninverted flow. The loss of EPNL suppression is relatively modest. The in-flight peak PNL suppression of the inverter with conical nozzle was 2.5 PNdb relative to a static value of 5.5 PNdb. The corresponding EPNL suppression was 4.0 EPNdb for flight and 5.0 EPNdb for static operation. The highest in-flight EPNL suppression was 7.5 EPNdb obtained by the inverter with 20 lobe nozzle and acoustic shield. When compared with the JT8D engine with internal mixer, the inverted flow configuration provides more EPNL suppression under both static and flight conditions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-2996
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  • 91
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    Experimental study of the effects of flameholder geometry on emissions and performance of lean premixed combustors (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Emissions of NOx, CO, and unburned hydrocarbons (UHC) are reported for a lean premixed propane-air system at inlet conditions of 800K and 1MPa using twelve flameholder designs. The flameholders tested represent six design concepts with two values of blockage for each concept. Data were obtained at reference velocities of 35 m/s, 25 m/s and 20 m/s at combustor stations 10 cm and 30 cm downstream of the flameholders. Flameholder pressure drop was found to be a principal determinant of emissions performance. Designs producing larger pressure drops also produced less NOx, CO, and UHC emissions. The lean stability limit equivalence ratio was found to be approximately 0.35 for all designs. Flashback velocities (axial components in the flameholder passages) varied between 30 m/s and 40 m/s. A perforated plate flameholder was operated with a velocity as low as 23 m/s through the perforations at equivalence ratio 0.7 without producing flashback.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135424 , GASL-TR-249
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  • 92
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    Low cost fabrication development for oxide dispersion strengthened alloy vanes (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Viable processes were developed for secondary working of oxide dispersion strengthened (ODS) alloys to near-net shapes (NNS) for aircraft turbine vanes. These processes were shown capable of producing required microstructure and properties for vane applications. Material cost savings of 40 to 50% are projected for the NNS process over the current procedures which involve machining from rectangular bar. Additional machining cost savings are projected. Of three secondary working processes evaluated, directional forging and plate bending were determined to be viable NNS processes for ODS vanes. Directional forging was deemed most applicable to high pressure turbine (HPT) vanes with their large thickness variations while plate bending was determined to be most cost effective for low pressure turbine (LPT) vanes because of their limited thickness variations. Since the F101 LPT vane was selected for study in this program, development of plate bending was carried through to establishment of a preliminary process. Preparation of ODS alloy plate for bending was found to be a straight forward process using currently available bar stock, providing that the capability for reheating between roll passes is available. Advanced ODS-NiCrAl and ODS-FeCrAl alloys were utilized on this program. Workability of all alloys was adequate for directional forging and plate bending, but only the ODS-FeCrAl had adequate workability for shaped preform extrustion.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135373 , R78AEG418
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  • 93
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    Counter pumping debris excluder and separator (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A dirt separator and excluder for removing entrained debris from gas turbine shaft seals is described. A helical groove pattern is constructed on the rotating shaft with the pumping pattern such that it tends to pump seal pressurizing gas toward the gas turbine seal. A second helical groove pattern is provided on the stationary housing or counter rotating member coaxial with the shaft, and this pattern is designed to provide pumping in the direction opposite from that of the groove pattern on the shaft. Gas with entrained debris entering this grooved area will be subjected to high centrifugal forces due to the swirl motion induced by the groove pattern and the rotation of the shaft. This debris is centrifuged outwardly into the outer groove pattern on the housing or counter rotating member. Because the outer groove pattern has a pumping direction opposite from that of the seal, dirt is pumped away from the seal and can be collected in a suitable debris trap remote from the seal location.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 94
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    Gas turbine engine with recirculating bleed (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Carbon monoxide and unburned hydrocarbon emissions in a gas turbine engine are reduced by bleeding hot air from the engine cycle and introducing it back into the engine upstream of the bleed location and upstream of the combustor inlet. As this hot inlet air is recycled, the combustor inlet temperature rises rapidly at a constant engine thrust level. In most combustors, this will reduce carbon monoxide and unburned hydrocarbon emissions significantly. The preferred locations for hot air extraction are at the compressor discharge or from within the turbine, whereas the preferred reentry location is at the compressor inlet.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 95
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    Altitude calibration of an F100, S/N P680063, turbofan engine (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An airflow and thrust calibration of an F100 engine was conducted in coordination with a flight test program to study airframe-propulsion system integration characteristics of turbofan-powered high-performance aircraft. The tests were conducted with and without augmentation for a variety of simulated flight conditions with emphasis on the transonic regime. Test results for all conditions are presented in terms of corrected airflow and corrected gross thrust as functions of corrected fan speed for nonaugmented power and an augmented thrust ratio as a function of fuel-air ratio for augmented power. Comparisons of measured and predicted data are presented along with the results of an uncertainty analysis for both corrected airflow and gross thrust.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1228 , E-9355
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 96
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    Interaction between step fuel injectors on opposite walls in a supersonic combustor model (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are presented from an experimental investigation of perpendicular, hydrogen fuel injection and combustion from opposing walls in a scramjet combustor model using a longitudinally staged laterally inline step-injection configuration. The model represents a portion of the flow in the Langley integrated modular scramjet engine combustor operating at a flight Mach number of 7. When operating at a ratio of jet pressure to free-stream dynamic pressure of 3, the injectors produce a bulk equivalence ratio of unity. This investigation represents part of a continuing study of the modular engine fuel injectors and is specifically designed to eliminate the adverse lateral pressure gradient observed at the injector location in a previous test. Flow survey contours at three axial locations, ranging from one-third of the engine combustor length to the total engine combustor length, are used to determine mixing efficiency and fuel distribution. Wall static pressures are analyzed by using one-dimensional theory to determine the combustion efficiency. Results show a significant improvement over previous injector designs tested in this duct geometry.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1174 , L-11811
    Format: application/pdf
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  • 97
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    Combustion of hydrogen in a two-dimensional duct with step fuel injectors (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation of the combustion of hydrogen perpendicularly injected from step fuel injectors into a Mach 2.72, 2100 K vitiated test gas was conducted. The model simulated the flow between the center and side struts of an integrated scramjet module at Mach 7 flight and an altitude of 29 km. Parametric variation included equivalence ratio, fuel dynamic pressure ratio, and area distribution of the model. The overall area ratio of the model was held constant at 2.87. The data analysis indicated that no measurable improvement in mixing or combustion efficiency was obtained by varying the fuel dynamic pressure ratio from 0.79 to 2.45. Computations indicated approximately 80 percent of the fuel was mixed so that it could react; however, only approximately 50 percent of the mixed fuel actually reacted in two test configurations, and 74 percent in later tests where less area expansion of the flow occurred.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1159 , L-11981
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 98
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    Supersonic through-flow fan engines for supersonic cruise aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Engine performance, weight and mission studies were carried out for supersonic through flow fan engine concepts. The mission used was a Mach 2.32 cruise mission. The advantages of supersonic through flow fan engines were evaluated in terms of mission range comparisons between the supersonic through flow fan engines and a more conventional turbofan engine. The specific fuel consumption of the supersonic through flow fan engines was 12 percent lower than the more conventional turbofan. The aircraft mission range was increased by 20 percent with the supersonic fan engines compared to the conventional turbofan.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78889 , E-9626
    Format: application/pdf
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  • 99
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    In-place recalibration technique applied to a capacitance-type system for measuring rotor blade tip clearance (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The rotor blade tip clearance measurement system consists of a capacitance sensing probe with self contained tuning elements, a connecting coaxial cable, and remotely located electronics. Tests show that the accuracy of the system suffers from a strong dependence on probe tip temperature and humidity. A novel inplace recalibration technique was presented which partly overcomes this problem through a simple modification of the electronics that permits a scale factor correction. This technique, when applied to a commercial system significantly reduced errors under varying conditions of humidity and temperature. Equations were also found that characterize the important cable and probe design quantities.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1110 , E-9395
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 100
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    Lean Combustion Limits of a Confined Premixed-Prevaporized Propane Jet (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Lean blowout limits were reported for a premixed prevaporized propane jet issuing into a cylindrical combustor. A single hole in a flat plate was used as a flameholder. Flameholders with various hole diameters were used. Jet velocities were varied from 3 to 290 meters per second. The combustor cross sectional area was changed by using different quartz liners of 12.7 and 22.2 millimeters diameters. As a result the combustor Reynolds number varied from 1000 to 9000. Stability was achieved at laminar as well as turbulent conditions. Three zones of flame stability were observed. The blowout equivalence ratio varied with step size and the combustor and jet Reynolds numbers. The combustor inlet mixture temperature was 395 K, and the combustor pressure was 1 atmosphere.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78868 , E-9453
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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