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  • AIRCRAFT PROPULSION AND POWER  (1,211)
  • 1975-1979  (1,211)
  • 1
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    Aircraft Energy Efficiency (ACEE) status report (1979)
    In:  CASI
    Details
    Publication Date: 2009-11-17
    Description: Fuel efficiency in aeronautics, for fuel conservation in general as well as for its effect on commercial aircraft operating economics is considered. Projects of the Aircraft Energy Efficiency Program related to propulsion are emphasized. These include: (1) engine component improvement, directed at performance improvement and engine diagnostics for prolonged service life; (2) energy efficient engine, directed at proving the technology base for the next generation of turbofan engines; and (3) advanced turboprop, directed at advancing the technology of turboprop powered aircraft to a point suitable for commercial airline service. Progress in these technology areas is reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 1-58
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  • 2
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    High-performance-vehicle technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Propulsion needs of high performance military aircraft are discussed. Inlet performance, nozzle performance and cooling, and afterburner performance are covered. It is concluded that nonaxisymmetric nozzles provide cleaner external lines and enhanced maneuverability, but the internal flows are more complex. Swirl afterburners show promise for enhanced performance in the high altitude, low Mach number region.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 445-462
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  • 3
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    Vertical Takeoff and Landing (VTOL) propulsion technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Propulsion problems and advanced technology requirements of VTOL aircraft are discussed. Specific topics covered include inlets with high angle of attack capability, rapid thrust modulation fans, and propulsion-system/aircraft-control integration.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 409-444
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  • 4
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    Hypersonic propulsion (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Research on hydrogen fueled scramjet engines for hypersonic flight is reviewed. Component developments, computational methods, and preliminary ground tests of subscale scramjet engine modules at Mach 4 and 7 are emphasized. Airframe integration, structures, and flow diagnostics are also discussed. It is shown that mixed-mode perpendicular and parallel fuel injection controls heat release over a wide Mach range and the fixed geometry inlet gives good performance over a wide range of Mach numbers.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 387-408
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  • 5
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    Control technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: An overview of engine control technology is presented with emphasis on gas turbine engine controls. The role of the government, and NASA in particular, in advancing this technology is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 329-344
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  • 6
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    Supersonic propulsion technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Propulsion concepts for commercial supersonic transports are discussed. It is concluded that variable cycle engines, together with advanced supersonic inlets and low noise coannular nozzles, provide good operating performance for both supersonic and subsonic flight. In addition, they are reasonably quiet during takeoff and landing and have acceptable exhaust emissions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 345-386
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  • 7
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    Mechanical components (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Research on bearings, gears, seals, and rotor dynamics (specifically high speed balancing and dampers) is presented. The research pertains to problems in both aircraft turbine engines and helicopter transmissions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 273-308
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  • 8
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    Instrumentation technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Some of the efforts made in applying technologically new tools to today's propulsion measurement problems are described. They include: (1) a blade-tip clearance system; (2) a pulsed thermocouple system used to measure gas temperature with a thermocouple at temperatures above the melting point of the thermocouple; (3) an optical technique for measuring blade flutter; (4) a probe for dynamic flow and flow angle measurement; and (5) a laser anemometer system for rapidly mapping the flow profiles between the blades of a rotating compressor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 309-328
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  • 9
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    Turbomachinery technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: A technology assessment of turbomachinery is presented. The design of the fan, compressor, and turbine components for future advanced aircraft engines is discussed. Basic flow characteristics in compressors and turbines and the heat transfer phenomena in cooled turbines are also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 231-272
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  • 10
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    Computational fluid mechanics of internal flow (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Major solution techniques for internal computational fluid mechanics are discussed and some examples are presented. The major steps involved in developing a large computer code are then discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 187-230
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  • 11
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    Alternative jet aircraft fuels (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Potential changes in jet aircraft fuel specifications due to shifts in supply and quality of refinery feedstocks are discussed with emphasis on the effects these changes would have on the performance and durability of aircraft engines and fuel systems. Combustion characteristics, fuel thermal stability, and fuel pumpability at low temperature are among the factors considered. Combustor and fuel system technology needs for broad specification fuels are reviewed including prevention of fuel system fouling and fuel system technology for fuels with higher freezing points.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 129-148
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  • 12
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    Materials and structures technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Materials and structures performance limitations, particularly for the hot section of the engine in which these limitations limit the life of components, are considered. Failure modes for components such as blades, vanes, and combustors and how they are affected by the environment for such components are discussed. Methods used to improve the materials used for such components are: (1) application of directional structures to turbine components for high strength at high temperatures; (2) improved coatings to increase oxidation and corrosion resistance; (3) increase strength and stiffness with reduced weight by applying higher specific properties of composite materials; and (4) cost effective processing such as near net shape powder methods applied to disks. Life prediction techniques developed to predict component life accurately in advance of service and progress in improving the intermediate and cold section components of turbine engines are covered.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 149-186
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  • 13
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    Noise reduction (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: The turbofan engine's noise-producing components are discussed in terms of efficient and economical noise reduction techniques that do not penalize the engine performance or weight significantly. Specific topics covered include fan noise, acoustic suppression, jet noise technology, combustor noise, and aircraft noise prediction.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 85-128
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  • 14
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    Emission reduction (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Control of the gaseous pollutant emissions of aircraft engines is considered in terms of the emission standards for six classes of aircraft engines. Emphasis is placed on combustor design concepts to significantly reduce emissions levels and lean-burning techniques to lower flame temperature, to reduce the oxides of nitrogen in the gaseous emissions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 59-84
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  • 15
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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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  • 16
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    Aircraft engines (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Thrust and weight requirements of aircraft engines in general are discussed. The characteristics and operating principles of various types of air breathing and rocket engines are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Soviet Aircraft and Rockets (NASA-TT-F-770); p 81-139
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  • 17
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    Trends in aircraft noise control (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Flight vehicles are characterized according to their manner of operation and type of propulsion system; and their associated sources of noise are identified. Available noise reduction technology as it relates to engine cycle design and to powerplant component design is summarized. Such components as exhaust jets, fans, propellers, rotors, blown flaps, and reciprocating-engine exhausts are discussed, along with their noise reduction potentials. Significant aircraft noise reductions are noted to have been accomplished by the application of available technology in support of noise certification rules. Further noise reductions to meet more stringent future noise regulations will require substantial additional technology developments. Improved analytical prediction methods, and well-controlled validation experiments supported by advanced-design aeroacoustic facilities, are required as a basis for an effective integrated systems approach to aircraft noise control.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA/Univ. Conf. on Aeron.; p 103-130
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  • 18
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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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  • 19
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    New evidence of the mechanisms of noise generation and radiation of a subsonic jet (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Acoustical Society of America; vol. 57
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  • 20
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    Streamtube analysis of a hydrogen-burning scramjet exhaust and simulation technique (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A scramjet/airframe integration program and a technique for simulating thermally perfect scramjet exhaust flows (freon/argon gas blends) is studied to extend the technique to more complicated flows approaching the actual exhaust flow in complexity. The state of the flow and the accuracy of the substitute gas simulation are analyzed in the case of a shock discontinuity present. Findings are: scramjet exhaust flow is essentially frozen throughout the expansion at Mach 6 and Mach 8; flow behind moderate shocks remains frozen; the technique can accurately track static distributions in scramjet exhaust flows (shocked or unshocked).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Journal of Aircraft; 14; Sept
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  • 21
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    Fretting in aircraft turbine engines (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: The problems created by fretting in turbine engines are discussed. The areas of greatest wear identified with the fan, compressor, and turbine blade mountings being the most critical items. Various methods for reducing or eliminating fretting in a turbine engine are described. Vacuum deposition of coatings by sputtering and ion plating are recommended as an economic method of applying thin films to inhibit fretting.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Specialists Meeting on Fretting in Aircraft Systems; 17 p
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  • 22
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    Aeroacoustics: Jet noise, combustion and core engine noise (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The papers in this volume deal essentially with the question whether the amplification of noise is due to the jet noise phenomenon or perhaps an interaction of airframe and core engine noise. In the area of jet noise suppression, various promising suppressor concepts are examined. The swirling flow jet noise suppressor is shown to provide significant noise reduction with minimal thrust losses. Progress in the aircraft engine core noise problem is reflected by seven research-type papers. Two possible mechanisms are seen to be responsible for core noise. One is the direct noise radiated from the turbulent combustion in the primary combuster and transmitted through the turbine, passing out the nozzle into the far field. The other mechanism is the noise that is emitted from hot spots being convected through the turbine. Which of these mechanisms (or perhaps both mechanisms) is responsible for core noise, and what are the coupling mechanisms of core engine noise and jet noise are the questions confronting researchers.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 23
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    How good is jet lift VTOL technology (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The status of technologies for jet-lift V/STOL aircraft is examined, and a critical review of the performance of jet-lift VTOL aircraft built to date is made. Most jet-lift aircraft have suffered from adverse propulsion-induced effects during takeoff and landing. Flight dynamics of jet-lift aircraft have suffered from shortcomings in static and dynamic stability, control characteristics, and flight path control. Some of the main problems to be considered during the selection of a propulsion system arrangement for a V/STOL fighter are discussed. At present, experimental and analytical data on supersonic V/STOL configurations are insufficient to permit evaluating propulsion system arrangements.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 15; Dec. 197
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  • 24
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    Generalized dynamic engine simulation techniques for the digital computers (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: Recently advanced simulation techniques have been developed for the digital computer and used as the basis for development of a generalized dynamic engine simulation computer program, called DYNGEN. This computer program can analyze the steady state and dynamic performance of many kinds of aircraft gas turbine engines. Without changes to the basic program, DYNGEN can analyze one- or two-spool turbofan engines. The user must supply appropriate component performance maps and design point information. Examples are presented to illustrate the capabilities of DYNGEN in the steady state and dynamic modes of operation. The analytical techniques used in DYNGEN are briefly discussed, and its accuracy is compared with a comparable simulation using the hybrid computer. The impact of DYNGEN and similar digital programs on future engine simulation philosophy is also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Power Plant Controls for Aero-Gas Turbine Eng.; 23 p
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  • 25
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    Effect of endwall cooling on secondary flows in turbine stator vanes (1977)
    In:  CASI
    Details
    Publication Date: 2012-05-19
    Description: An experimental investigation was performed to determine the effect of endwall cooling on the secondary flow behavior and the aerodynamic performance of a coreturbine stator vane. The investigation was conducted in a cold-air, full-annular cascade, where three-dimensional effects could be obtained. Two endwall cooling configurations were tested. In the first configuration, the cooling holes were oriented so that the coolant was injected in line with the inviscid streamline direction. In the second configuration, the coolant was injected at an angle of 15 deg to the inviscid streamline direction and oriented toward the vane pressure surface. In both cases the stator vanes were solid and uncooled so that the effect of endwall cooling could be obtained directly. Total-pressure surveys were taken downstream of the stator vanes over a range of cooling flows at the design, mean-radius, critical velocity ratio of 0.778. Changes in the total-pressure contours downstream of the vanes were used to obtain the effect of endwall cooling on the secondary flows in the stator. Comparisons were made between the two cooled-endwall configurations and with the results obtained previously for solid endwalls.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Secondary Flows in Turbomachines; 29 p
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  • 26
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    QCSEE - The key to future short-haul air transport (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper describes the design and test procedure for the QCSEE (quiet, clean, short-haul experimental engine). The engines designed for the YC-14 and YC-15 STOL aircraft, both use a very low fan pressure ratio to keep jet-flap noise about 3 dB below total system noise. Other noise reducing features discussed are the low tip speed fans and a carefully selected number of fan blades and vanes with adequate spacing between them. Attention is also given to the development of a low emissions combustor, and reduction of fan frame weight, through the use of graphite/epoxy material. The YC-15 engine also employs variable pitch fans to provide thrust reversal, thus saving weight. Finally, it is noted that the tests have proven that the engines could be configurated to meet the needs of a powered lift system without excessively compromising performance or weight.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ICAO Bulletin; 34; Apr. 197
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  • 27
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    Gas turbine engine emissions - Problems, progress and future (1978)
    In:  Other Sources
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    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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  • 28
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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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  • 29
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    Propulsion (1978)
    In:  Other Sources
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    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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  • 30
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    Engine requirements for future general aviation aircraft (1978)
    In:  Other Sources
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    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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  • 31
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    Review of the Rhein-Flugzeugbau Wankel powered aircraft program (1978)
    In:  Other Sources
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    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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  • 32
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    Update of development on the new Audi NSU rotary engine generation (1978)
    In:  Other Sources
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    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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  • 33
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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
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    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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  • 34
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    Development status of rotary engine at Toyo Kogyo (1978)
    In:  Other Sources
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    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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  • 35
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    General aviation energy-conservation research programs (1978)
    In:  Other Sources
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    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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  • 36
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    Advanced low-NO(x) combustors for supersonic high-altitude gas turbines (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The impact of gas-turbine-engine-powered aircraft on worldwide pollution was defined within two major areas of contribution. First, the contribution of aircraft to the local air pollution of metropolitan areas and, second, the long-term effects on the chemical balance of the stratosphere of pollutants emitted from future generations of high-altitude, supersonic commercial and military aircraft. Preliminary findings indicate that stratospheric oxides of nitrogen (NOx) emissions may have to be limited to very low levels if, for example, ozone depletion with concomitant increases in sea-level radiation, are to be avoided. Theoretical considerations suggest that (NOx) levels as low as 1.0 gram per kilogram of fuel and less should be attainable from a idealized premixed type of combustor. Experimental rig studies were intended to explore new combustor concepts designed to minimize the formation of (NOx) in aircraft gas turbines and to define their major operational problems and limitations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 393-415
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    Soot formation in a turbulent swirling flow (1977)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The qualitative understanding of soot formation in simple models of gas turbine primary-zone combustors is summarized. Soot formation in flame radiation and air pollution was investigated. Results are presented, namely: (1) if the fuel is premixed with air in approximately stoichiometric proportions, the sequence of states that a fluid element undergoes as it burns is quite different from the sequence when liquid or vapor fuel is injected into an air-flow; (2) swirling flows, as are typical or swirl-can combustors, when burning, can amplify small aerodynamic disturbances upstream of the swirl vanes; and (3) different fuels form significantly different amounts of soot. Each of these effects makes major changes in the amount of soot formed in a given combustor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 309-321
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  • 38
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    Pollution reduction technology program for turboprop engines (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The reduction of CO, HC, and smoke emissions while maintaining acceptable NO(x) emissions without affecting fuel consumption, durability, maintainability, and safety was accomplished. Component combustor concept screening directed toward the demonstration of advanced combustor technology required to meet the EPA exhaust emissions standards for class P2 turboprop engines was covered. The combustion system for the Allison 501-D22A engine was used, and three combustor design concepts - reverse flow, prechamber, and staged fuel were evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 125-147
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  • 39
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    Ceramic composite protection for turbine disc bursts (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Ceramic composite turbine disc protection panels for the A300B were developed using armor technology. Analytical predictions for modifying the ballistic projectile armor system were verified by a test program conducted to qualify the rotor containment system. With only a slight change in the areal density of the armor system a more than two-fold increase in kinetic energy protection level was achieved. Thickness of the fiberglass reinforced plastic backing material was increased to achieve an optimum ratio of ceramic thickness to backing thickness for the different ballistic defeat condition.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 277-293
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  • 40
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    Materials and manufacturing processes for increased life/reliability (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Improvements in both quality and durability of disk raw material for both military and commercial engines necessitated an entirely new concept in raw material process control which imposes careful selection, screening and sampling of the basic alloy ingredients, followed by careful monitoring of the melting parameters in all phases of the vacuum melting sequence. Special care is taken to preclude solidification conditions that produce adverse levels of segregation. Melt furnaces are routinely cleaned and inspected for contamination. Ingots are also cleaned and inspected before entering the final melt step.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 347-368
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  • 41
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    Numerical analysis of projectile impact in woven texile structures (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Computer codes were developed for simulating the dynamic fracture and viscoelastic constitutive response due to stress wave interaction and reflections caused by ballistic impact on woven textiles. The method, which was developed for use in the design and analysis of protection devices for personnel armor, has potential for use in studies of rotor blade burst containment at high velocity. Alterations in coding required for burst containment problems are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Assessment of Technol. for Turbojet Engine Rotor Failures; p 247-260
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  • 42
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    Lightweight engine containment (1977)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Kevlar fabric styles and weaves were studied, as well as methods of application for advanced gas turbine engines. The Kevlar material was subjected to high speed impacts by simple projectiles fired from a rifle, as well as more complex shapes such as fan blades released from gas turbine rotors in a spin pit. Just contained data was developed for a variety of weave and/or application techniques, and a comparative containment weight efficiency was established for Kevlar containment applications. The data generated during these tests is being incorporated into an analytical design system so that blade containment trade-off studies between Kevlar and metal case engine structures can be made. Laboratory tests and engine environment tests were performed to determine the survivability of Kevlar in a gas turbine environment.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 235-245
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  • 43
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    Approaches to rotor fragment protection (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Key airworthiness design criteria considerations for fragment protection as found in various FAA requirements in FAR Parts 25 and 33, and in interpretive 8110 orders are reviewed. The impact of providing aircraft armor in lieu of engine armor for typical three- and four-engine wide bodied transports for protection within the length of the engine case as well as from fragments exiting ahead of the enlet engine inlet flange is assessed. For protection within the length of the engine case, armor weight penalties, plus fuel burned and dollar cost of carrying the armor protection are defined. Immediately ahead of the inlet flange, direct tangential impacts are predominant, but further forward, rebound impacts predominate. Armor thickness requirements and fuel cost impact of protection are given.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 101-103
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  • 44
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    Engine Non-Containment: The UK CAA View (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Airworthiness accidents account for roughly one quarter of the total number of accidents to public transport turbojet aircraft. The most reliable, practicable, and cost-effective means of minimizing damage outside the confines of the nacelle is to make the aircraft design invulnerable to any debris which may affect the aircraft. A failure model was developed for use by aircraft builders in measuring the freedom from catastrophe factor of their design.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 11-32
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  • 45
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    Engine sealing and lubrication systems (1975)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Engine sealing programs are discussed which are directed toward the two major classes of engine seals: engine shaft seals and primary gas path seals. In addition, some concepts and results from fundamental lubrication research, as it pertains to the lubrication of bearings, are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 305-327
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  • 46
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    Refan program (1975)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The JT8D Refan Program for noise reduction is outlined, and the overall objectives and program status, test results, and current noise level predictions are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 81-97
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  • 47
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    Propulsion system noise reduction (1975)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The progress in propulsion system noise reduction is reviewed. The noise technology areas discussed include: fan noise; advances in suppression including conventional acoustic treatment, high Mach number inlets, and wing shielding; engine core noise; flap noise from both under-the-wing and over-the-wing powered-lift systems; supersonic jet noise suppression; and the NASA program in noise prediction.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 1-63
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  • 48
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    Installation drag considerations as related to turboprop and turbofan engines (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Some of the specific areas associated with straight jet and turboprop engine installations are outlined where drag reduction and, thus, improved aircraft system performance is obtained. Specific areas constitute air intake sizing for general aviation aircraft, exhaust duct geometries and cooling system arrangements for propeller powered aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 245-256
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  • 49
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    Hypersonic propulsion (1975)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The NASA research on scramjet technology for speeds above Mach 5 is reported. A brief overview of the NASA Hypersonic Research Engine (HRE) project is presented with emphasis on the most significant contributions on the HRE to scramjet technology. The work on high-performance airframe-integrated scramjet engines is described, and a new versatile research airplane is discussed with emphasis on propulsion.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 459-474
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  • 50
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    Turbine materials and life prediction (1975)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The recent developments and future potential of advanced materials for turbine components are described. The components discussed in detail are disks, blades, and vanes.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 209-288
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  • 51
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    Fuel-conservative engine technology (1975)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Aircraft fuel consumption is discussed in terms of its efficient use, and the conversion of energy from sources other than petroleum. Topics discussed include: fuel from coal and oil shale, hydrogen deficiency of alternate sources, alternate fuels evaluation program, and future engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 157-190
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  • 52
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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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  • 53
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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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  • 54
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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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  • 55
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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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  • 56
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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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  • 57
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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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  • 58
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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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  • 59
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    CF6 performance improvement (1978)
    In:  CASI
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    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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  • 60
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    ACEE Propulsion Overview (1978)
    In:  CASI
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    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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  • 61
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    Effect of ambient temperature and humidity on emissions of an idling gas turbine (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effects of inlet pressure, temperature, and humidity on the oxides of nitrogen produced by an engine operating at takeoff power setting were investigated and numerous correction factors were formulated. The effect of ambient relative humidity on gas turbine idle emissions was ascertained. Experimentally, a nonvitiating combustor rig was employed to simulate changing combustor inlet conditions as generated by changing ambient conditions. Emissions measurements were made at the combustor exit. For carbon monoxide, a reaction kinetic scheme was applied within each zone of the combustor where initial species concentrations reflected not only local combustor characteristics but also changing ambient conditions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 437-456
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  • 62
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    Global atmospheric sampling program (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Automated instruments were installed on a commercial B-747 aircraft, during the program, to obtain baseline data and to monitor key atmospheric constituents associated with emissions of aircraft engines in order to determine if aircraft are contributing to pollution of the upper atmosphere. Data thus acquired on a global basis over the commercial air routes for 5 to 10 years will be analyzed. Ozone measurements in the 29,000 to 45,000 foot altitude were expanded over what has been available from ozonesondes. Limited aerosol composition measurements from filter samples show low levels of sulfates and nitrates in the upper troposphere. Recently installed instruments for measurement of carbon monoxide and condensation nuclei are beginning to return data.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 323-355
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  • 63
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    Emissions control for ground power gas turbines (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The similarities and differences of emissions reduction technology for aircraft and ground power gas turbines is described. The capability of this technology to reduce ground power emissions to meet existing and proposed emissions standards is presented and discussed. Those areas where the developing aircraft gas turbine technology may have direct application to ground power and those areas where the needed technology may be unique to the ground power mission are pointed out. Emissions reduction technology varying from simple combustor modifications to the use of advanced combustor concepts, such as catalysis, is described and discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 203-242
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  • 64
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    Pollution reduction technology program for small jet aircraft engines: Class T1 (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Small jet aircraft engines (EPA class T1, turbojet and turbofan engines of less than 35.6 kN thrust) were evaluated with the objective of attaining emissions reduction consistent with performance constraints. Configurations employing the technological advances were screened and developed through full scale rig testing. The most promising approaches in full-scale engine testing were evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 149-180
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  • 65
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    Emissions Reduction Technology Program (1977)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Combustor concepts having the potential for significantly lower emissions levels were investigated. The combustor emissions reduction was measured in an engine test. Emission characteristics common to all engine classes are shown. Multiple-burning zone combustors, specifically the double-annular and swirl-can combustors were studied. Airblast and air-assist fuel injection techniques were evaluated for emissions control potential. The combustor sceening and refining phases are summarized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 19-58
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  • 66
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    Turbine disks for improved reliability (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Advanced disk structural concepts were employed to improve the cyclic lives and reliability of turbine disks. Analytical studies were conducted to evaluate bore-entry disks as potential replacements for the existing first-stage turbine disks in the CF6-50 and JT8D-17 engines. Results of low cycle fatigue, burst, fracture mechanics, and fragment energy analyses are summarized for the advanced disk designs and the existing disk designs, with both conventional and advanced disk materials. Other disk concepts such as composite, laminated, link, multibore, multidisk, and spline disks were also evaluated for the CF6-50 engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 389-411
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  • 67
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    Analysis methods for Kevlar shield response to rotor fragments (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Several empirical and analytical approaches to rotor burst shield sizing are compared and principal differences in metal and fabric dynamic behavior are discussed. The application of transient structural response computer programs to predict Kevlar containment limits is described. For preliminary shield sizing, present analytical methods are useful if insufficient test data for empirical modeling are available. To provide other information useful for engineering design, analytical methods require further developments in material characterization, failure criteria, loads definition, and post-impact fragment trajectory prediction.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 261-275
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  • 68
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    Rotor burst protection criteria and implications (1977)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Current aircraft design practices to minimize the hazard from rotor bursts are described. The consequences of non-contained engine failures and the impact of rotor burst protection systems on aircraft design are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 37-43
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  • 69
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    Propellers of Minimum Induced Loss, and Water Tunnel Tests of Such a Propeller (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The fundamental vortex theory for a single rotation propeller with a finite number of blades is reviewed. The theory leads to the specification of a radial distribution of bound circulation on each blade for minimum induced loss, analogous to the elliptic spanwise distribution of bound circulation on a wing for minimum induced drag. A propeller designed in accord with this theory has been tested in a water tunnel where it exhibited high efficiency in spite of localized cavitating flow. A knowledge of the flow field for an optimum propeller is of value to the airframe designer seeking to maximize the performance of the airplane-propeller combination.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 273-293
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    Supersonic propulsion (1975)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The Supersonic Cruise Airplane Research (SCAR) technology program is reported. Mission requirements, cycle considerations, engine evaluation, and SCAR test results are discussed. It is concluded that improved aerodynamics and structures, greater use of composites, and more-refined active controls are needed in the airframe area for designing an economically viable, environmental acceptable supersonic aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 441-457
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    Engine systems technology (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Current full-scale engine development programs are discussed, and efforts to improve the available technology base are presented. The Lewis full-scale engine test facilities are described. Several typical engine programs and plans for research in aeromechanical instability or flutter are summarized. An overview of Lewis studies of flow distortion and its effects on engine stability is presented. The origins and nature of the distortion problem are summarized, and some of the results and methods for both steady and time-varying distortions are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 329-385
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  • 72
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    Composites for fans and compressors (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The composites research being conducted at Lewis for the application of composite materials to fan and compressor blades, is reviewed. The major areas discussed include the development of improved materials and fabrication methods, recent progress in providing composite fan and compressor blades with improved resistance to foreign object damage, and the development of advanced design and analysis procedures for composite blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 191-208
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  • 73
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    QCSSE program (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The objectives, scope, and status of the NASA Quiet, Clean, Short-Haul Experimental Engine program are reviewed. The progress reported is concerned with engine design concepts for short-haul aircraft where part of the engine thrust is used to help lift the aircraft. Both under-the-wing, and over-the-wing configurations are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 65-80
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  • 74
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    Upper atmosphere pollution measurements (GASP) (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The environmental effects are discussed of engine effluents of future large fleets of aircraft operating in the stratosphere. Topics discussed include: atmospheric properties, aircraft engine effluents, upper atmospheric measurements, global air sampling, and data reduction and analysis
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 139-156
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  • 75
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    Propulsion systems technology (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The selection of components, control design, simulation, and tests are examined for designing supersonic propulsion systems. Inlet-engine combination under electronic control are shown. Design and test results from the integrated control for afterburning turbofan and supersonic cruise inlet are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 387-440
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  • 76
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    Bearings and gears for advanced turbine engines and transmissions (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The improved technology is discussed of engine main-shaft ball bearings, and spur gears in power transmission drive trains. Much of the technology can be applied to other ball and roller bearings, and to other spur and bevel gears throughout the engine, drive train, and accessory systems.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 289-303
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  • 77
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    Combustion and emissions technology (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Combustor development is discussed as it relates to emissions reduction. The nature of the aircraft pollution problem is examined along with the aircraft pollution standards that have been established by the Environmental Protection Agency. The effect of engine operating conditions on pollutant formation levels is shown, as well as how close present-day engines are to meeting the established standards. The magnitude of the emissions reductions required to meet these standards is indicated. The progress that has been made in evolving the needed emissions reduction technology is the main topic.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 99-137
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  • 78
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    Turbofan compressor dynamics during afterburner transients (1976)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The effects of afterburner light-off and shut-down transients on the compressor stability are investigated. The reported experimental results are based on detailed high response pressure and temperature measurements on the TF30-P-3 turbofan engine. The tests were performed in an altitude test chamber simulating high altitude engine operation. It is shown that during both types of transients, flow breaks down in the forward part of the fan bypass duct. At a sufficiently low engine inlet pressure this resulted in a compressor stall. Complete flow breakdown within the compressor was preceded by a rotating stall. At some locations in the compressor, rotating stall cells initially extended only through part of the blade span. For the shutdown transient the time between first and last detected occurrence of rotating stall is related to the flow Reynolds number. An attempt was made to deduce the number and speed of propagation of rotating stall cells.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Unsteady Phenomena in Turbomachinery; 12 p
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  • 79
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    Supersonic unstalled flutter (1979)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A parametric study to show the effects of cascade geometry, inlet Mach number, and backpressure on the onset of single and multi degree of freedom unstalled supersonic flutter is presented. Several of the results are correlated against experimental qualitative observation to validate the models.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Stresses, Vibrations, Struct. Integration and Eng. Integrity (Including Aeroelasticity and Flutter); 14 p
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  • 80
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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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  • 81
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    Review of the AGARD S and M panel evaluation program of the NASA-Lewis SRP approach to high-temperature LCF life prediction (1979)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The strain range partitioning SRP method method presented is a significant step forward in high temperature low cycle fatigue life prediction. Several concerns and recommendations regarding SRP were described. These dealt primarily with the problems associated with the application of SRP to cases involving small inelastic strains (and therefore long lives). The difficulties associated with partitioning these narrow hysteresis loops and the present inability of SRP to handle mean stress effects were also noted.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Stresses, Vibrations, Struct. Integration and Eng. Integrity (Including Aeroelasticity and Flutter); 9 p
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  • 82
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    Assessment of Variable-Cycle Engines for Supersonic Transports (1976)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Propulsion systems are evaluated in terms of relative aircraft range for a fixed payload and takeoff gross weight with a design cruise Mach number of 2.7. In order to put the performance of these engines in perspective, a comparison of these engines and the former U.S. SST engine is made with an idealized variable cycle engine whose performance at all operating points matches that of an optimized point design cycle within specified limits. Range comparisons are made with and without noise level constraints to determine the influence of noise upon cycle selection. The critical areas requiring new or improved technology for each cycle are delineated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Variable Geometry and Multicycle Eng.; 19 p
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  • 83
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    Laboratory studies of lean combustion (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The fundamental processes controlling lean combustion were observed for better understanding, with particular emphasis on the formation and measurement of gas-phase pollutants, the stability of the combustion process (blowout limits), methods of improving stability, and the application of probe and optical diagnostics for flow field characterization, temperature mapping, and composition measurements. The following areas of investigation are described in detail: (1) axisymmetric, opposed-reacting-jet-stabilized combustor studies; (2) stabilization through heat recirculation; (3) two dimensional combustor studies; and (4) spectroscopic methods. A departure from conventional combustor design to a premixed/prevaporized, lean combustion configuration is attractive for the control of oxides of nitrogen and smoke emissions, the promotion of uniform turbine inlet temperatures, and, possibly, the reduction of carbon monoxide and hydrocarbons at idle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 417-436
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  • 84
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    Alternative fuels (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Potential problems related to the use of alternative aviation turbine fuels are discussed and both ongoing and required research into these fuels is described. This discussion is limited to aviation turbine fuels composed of liquid hydrocarbons. The advantages and disadvantages of the various solutions to the problems are summarized. The first solution is to continue to develop the necessary technology at the refinery to produce specification jet fuels regardless of the crude source. The second solution is to minimize energy consumption at the refinery and keep fuel costs down by relaxing specifications.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 277-308
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  • 85
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    Summary of emissions reduction technology programs (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The NASA emissions reduction contract programs for EPA aircraft engine classes P2 (turboshaft engines), T1 (jet engines with thrust under 8000 lb), T4 (JT8D) engines), and T2 (jet engines with thrust over 8000 lb) are discussed. The most important aspects of these programs, the commonality of approaches used, the test results, and assessments regarding applications of the derived technology are summarized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 181-202
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  • 86
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    NASA/Pratt and Whitney experimental clean combustor program: Engine test results (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A two-stage vorbix (vortex burning and mixing) combustor and associated fuel system components were successfully tested in an experimental JT9D engine at steady-state and transient operating conditions, using ASTM Jet-A fuel. Full-scale JT9D experimental engine tests were conducted in a phase three aircraft experimental clean combustor program. The low-pollution combustor, fuel system, and fuel control concepts were derived from phase one and phase two programs in which several combustor concepts were evaluated, refined, and optimized in a component test rig. Significant pollution reductions were achieved with the combustor which meets the performance, operating, and installation requirements of the engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 91-123
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  • 87
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    Stratospheric cruise emission reduction program (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A recently implemented NASA effort specifically aimed at reducing cruise oxides of nitrogen from high-altitude aircraft is discussed. The desired emission levels and the combustor technology required to achieve them are discussed. A brief overview of the SCERP operating plan is given. Lean premixed-prevaporized combustion and some of the potential difficulties that are associated with applying this technique to gas turbine combustors are examined. Base technology was developed in several key areas. These fundamental studies are viewed as a requirement for successful implementation of the lean premixed combustion technique.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 357-391
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  • 88
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    General aviation piston-engine exhaust emission reduction (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: To support the promulgation of aircraft regulations, two airports were examined, Van Nuys and Tamiami. It was determined that the carbon monoxide (CO) emissions from piston-engine aircraft have a significant influence on the CO levels in the ambient air in and around airports, where workers and travelers would be exposed. Emissions standards were set up for control of emissions from aircraft piston engines manufactured after December 31, 1979. The standards selected were based on a technologically feasible and economically reasonable control of carbon monoxide. It was concluded that substantial CO reductions could be realized if the range of typical fuel-air ratios could be narrowed. Thus, improvements in fuel management were determined as reasonable controls.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 243-275
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  • 89
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    Pollution reduction technology program for class T4(JT8D) engines (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The technology required to develop commercial gas turbine engines with reduced exhaust emissions was demonstrated. Can-annular combustor systems for the JT8D engine family (EPA class T4) were investigated. The JT8D turbofan engine is an axial-flow, dual-spool, moderate-bypass-ratio design. It has a two-stage fan, a four-stage low-pressure compressor driven by a three-stage low-pressure turbine, and a seven-stage high-pressure compressor driven by a single-stage high-pressure turbine. A cross section of the JT8D-17 showing the mechanical configuration is given. Key specifications for this engine are listed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 29-89
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  • 90
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    Blade fragment energy analysis (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Two classes of fan blade fragments were considered in an analysis of blade fragment energy. The first, of relatively small size (.15 pound) and energy, tends to rebound from the fan and case when liberated in an FOD encounter. These small fragments have relatively low secondary damage potential and are less demanding in terms of protection. The larger fan blade fragments are ejected in a more direct release trajectory with higher energy and hence can represent a higher potential hazard. Simplified analytical methods were used to describe blade fragment energy transfer kinematics, establish fragment energy levels, evaluate damage potential and configure protection. The approach, methodology, and application are discussed as a possible building block for other applications. Development of effective local protection using Kevlar is also discussed. Analysis methods developed and applied to the rebound fragment problem and to the large direct release fragment problem are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 93-95
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  • 91
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    Development of fiber shields for engine containment (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Tests were conducted in translational launchers and spin pits to generate empirical data used in the design of a Kevlar shield for containing engine burst debris. Methods are given for modeling the relationship of fragment characteristics to shielding requirements. The change in relative importance of shield mounting provisions as fragment energy is increased is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 217-234
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  • 92
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    Types of rotor failure and characteristics of fragments (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Noncontained rotor failures in U.K. engines resulting from low cycle fatigue, low cycle fatigue with superimposed high cycle fatigue, and overheating and-or overspeeding were analyzed. The size, shape, weight, velocity, energy, and direction of the fragments released from turbines and compressors were studied and are presented in graph.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 65-92
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  • 93
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    Designing the L-1011 to minimize rotor failures effects (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Design philosophies used in the L-1011 aircraft to provide protection against rotor fragments include: (1) incorporating into the rotor design features that tend to promote small fragments if failure occurs; (2) containing the fragments within the engine shell or greatly reducing the energy content of those fragments that are eventually uncontained; (3) shielding vulnerable elements or systems with heavy structural members that tend to stop or deflect high velocity fragments; and (4) incorporating redundant and/or backup systems into the basic design and separating these systems so as to minimize the probability that more than one system will be damaged by an uncontained rotor fragment. Some of the design features that were incorporated into the Rolls-Royce RB211 engine are discussed, and two in-service experiences are considered in order to illustrate the practical operation of these features.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 97-100
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  • 94
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    Considerations of high altitude emissions (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The status of the Federal Aviation Administration's High Altitude Pollution Program is described which was instituted to develop the detailed quantitative information needed to judge whether or not regulatory action to limit such exhaust emissions would be necessary. The complexities of this question and the nature and magnitude of uncertainties still present in our scientific understanding of the potential interactions between aircraft exhaust emissions and stratospheric ozone and climate are reviewed. The direction and scope of future Federal and international activities are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center Proc. of the SCAR Conf., Pt. 2,; 10 p
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  • 95
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    Technology for controlling emissions of oxides of nitrogen from supersonic cruise aircraft (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Various experiments are sponsored and conducted by NASA to explore the potential of advanced combustion techniques for controlling aircraft engine emissions into the upper atmosphere. Of particular concern are the oxide of nitrogen (NOx) emissions into the stratosphere. The experiments utilize a wide variety of approaches varying from advanced combustor concepts to fundamental flame tube experiments. Results are presented which indicate that substantial reductions in cruise NOx emissions should be achievable in future aircraft engines. A major NASA program is described which focuses the many fundamental experiments into a planned evolution and demonstration of the prevaporized-premixed combustion technique in a full-scale engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Proc. of the SCAR Conf., Pt. 2,; 22 p
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  • 96
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    Composite materials research in support of supersonic propulsion systems (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Two engine components, fan blades and exhaust systems, were selected for composite materials development efforts in support of the supersonic cruise aircraft research (SCAR) engine program. The materials selected were boron/aluminum for fan blades and silicon carbide/superalloy sheet for the exhaust system. The current status of the research into applying these two composite materials to SCAR engines is reviewed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Proc. of the SCAR Conf., Part 1; p 457-468
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  • 97
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    YF-12 propulsion research program and results (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objectives and status of the propulsion program, along with the results acquired in the various technology areas, are discussed. The instrumentation requirements for and experience with flight testing the propulsion systems at high supersonic cruise are reported. Propulsion system performance differences between wind tunnel and flight are given. The effects of high frequency flow fluctuations (transients) on the stability of the propulsion system are described, and shock position control is evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Proc. of the SCAR Conf., Part 1; p 417-456
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  • 98
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    Control of propulsion systems for supersonic cruise aircraft (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The propulsion control requirements of supersonic aircraft are presented. Integration of inlet, engine, and airframe controls is discussed. The application of recent control theory developments to propulsion control design is described. Control component designs for achieving reliable, responsive propulsion control are also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Proc. of the SCAR Conf., Part 1; p 399-415
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  • 99
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    Supersonic cruise inlets for variable-cycle engines (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The performance of candidate supersonic cruise inlets is reviewed and the aerodynamic installation penalties for each type are defined. The main characteristics that affect the airflow schedules of variable cycle engines are defined. These schedules are compared with the airflow schedules of the candidate inlets, and appropriate inlets are matched to the variable-cycle engine characteristics. Auxiliary inlets are also considered.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Proc. of the SCAR Conf., Part 1; p 387-397
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  • 100
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    Variable stream control engine concept for advanced supersonic aircraft: Features and benefits (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Variable Stream Control Engine is studied for advanced supersonic cruise aircraft. Significant environmental and performance improvements relative to first generation supersonic turbojet engines are cited. Two separate flow streams, each with independent burner and nozzle systems are incorporated within the engine. By unique control of the exhaust temperatures and velocities in two coannular streams, significant reduction in jet noise is obtained.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center Proc. of the SCAR Conf., Part 1; p 341-352
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