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  • AIRCRAFT PROPULSION AND POWER
  • Biochemistry and Biotechnology
  • Engineering
  • 1975-1979  (493)
  • 1975  (493)
  • 1
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    Aircraft fuel conservation technology. Task force report, September 10, 1975 (1975)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An advanced technology program is described for reduced fuel consumption in air transport. Cost benefits and estimates are given for improved engine design and components, turboprop propulsion systems, active control systems, laminar flow control, and composite primary structures.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-74295
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Predicted exhaust emissions from a methanol and jet fueled gas turbine combustor (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A computer model of a gas turbine combustor has been used to predict the kinetic combustion and pollutant formation processes for methanol and simulated jet fuel. Use of the kinetic reaction mechanisms has also allowed a study of ignition delay and flammability limit of these two fuels. The NOX emissions for methanol were predicted to be from 69 to 92% lower than those for jet fuel at the same equivalence ratio which is in agreement with experimentally observed results. The high heat of vaporization of methanol lowers both the combustor inlet mixture temperatures and the final combustion temperatures. The lower combustion temperatures lead to low NOX emissions while the lower inlet mixture temperatures increase methanol's ignition delay. This increase in ignition delay dictates the lean flammability limit of methanol to be 0.8, while jet fuel is shown to combust at 0.4.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1266
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Application of real-time engine simulations to the development of propulsion system controls (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The development of digital controls for turbojet and turbofan engines can be facilitated by the use of real-time computer simulations of the engines. The engine simulation provides a 'test-bed' for evaluating new control laws and for checking and 'debugging' control software and hardware prior to engine testing. This paper describes the development and use of real-time, hybrid computer simulations of the Pratt & Whitney TF30-P-3 and F100-PW-100 augmented turbofans in support of a number of controls research programs at the Lewis Research Center. The role of engine simulations in solving the propulsion systems integration problem is also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1176
    Format: text
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  • 4
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    Effect of fuel properties on performance of a single aircraft turbojet combustor (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The performance of a single-can JT8D combustor was investigated with a number of fuels exhibiting wide variations in chemical composition and volatility. Performance parameters investigated were combustion efficiency, emissions of CO, unburned hydrocarbons and NOx, as well as liner temperatures and smoke. At the simulated idle condition no significant differences in performance were observed. At cruise, liner temperatures and smoke increased sharply with decreasing hydrogen content of the fuel. No significant differences were observed in the performance of an oil-shale derived JP-5 and a petroleum-based Jet A fuel except for emissions of NOx which were higher with the oil-shale JP-5. The difference is attributed to the higher concentration of fuel-bound nitrogen in the oil-shale JP-5.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Combustion Institute, Fall Meeting; October 20, 21, 1975; Palo Alto, CA
    Format: text
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  • 5
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    An early glimpse at long-term subsonic commercial turbofan technology requirements (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: This paper reports on the exploratory investigation and initial findings of the study of future turbofan concepts to conserve fuel. To date, these studies have indicated a potential reduction in cruise thrust specific fuel consumption in 1990 turbofans of approximately 15% relative to present day new engines through advances in internal aerodynamics, structure-mechanics, and materials. Advanced materials also offer the potential for fuel savings through engine weight reduction. Further studies are required to balance fuel consumption reduction with sound airlines operational economics.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1207
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Turbofan compressor dynamics during afterburner transients (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The effects of afterburner light-off and shut-down transients on the compressor stability are investigated. The reported experimental results are based on detailed high-response pressure and temperature measurements on the TF30-P-3 turbofan engine. The tests were performed in an altitude test chamber simulating high-altitude engine operation. It is shown that during both types of transients, flow breaks down in the forward part of the fan-bypass duct. At a sufficiently low engine inlet pressure this resulted in a compressor stall. Complete flow breakdown within the compressor was preceded by a rotating stall. At some locations in the compressor, rotating stall cells initially extended only through part of the blade span. For the shut-down transient the time between first and last detected occurrence of rotating stall is related to the flow Reynolds number. An attempt was made to deduce the number and speed of propagation of rotating stall cells.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NATO, AGARD, Symposium on Unsteady Phenomena in Turbomachinery; Sept. 22-26, 1975; Monterey, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Gas turbine combustor stabilization by heat recirculation (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The feasibility of heat recirculation for stabilization of lean mixtures and emission reduction has been studied in detail for a typical aircraft gas turbine combustor. Thermodynamic calculations have indicated temperature and heat recirculation rates for operation of the combustor over a range of combustion zone equivalence ratios and for varying modes of desired engine operation. Calculations indicate the feasibility of stabilizing the combustion zone at equivalence ratios as low as 0.2 with achievable heat recirculation rates. Detailed chemical kinetic calculations suggest that combustor heat release is maintained with reaction completion substantially before the NO forming reactions, even though CO is rapidly oxidized in this same region.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1304
    Format: text
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  • 8
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    Propulsion system structural integration and engine integrity; Proceedings of the Symposium, U.S. Naval Postgraduate School, Monterey, Calif., September 3-6, 1974 (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Current problems involving the structural integrity of propulsion systems, and proposed approaches to solving them, are reviewed. Areas investigated include the stall hammershock at the engine inlet, distortion-induced vibration in fan and compressor blading, modeling engine static structures with conical-shell finite elements, design and development of low-cost, self-contained bearing lubrication systems for turbine engines, and roller bearing slip and skidding damage. Individual items are announced in this issue.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion system structural integration and engine integrity; Symposium; Sept. 3-6, 1974; Monterey, CA
    Format: text
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  • 9
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    Application of real-time engine simulations to the development of propulsion system controls (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: The development of digital controls for turbojet and turbofan engines is presented by the use of real-time computer simulations of the engines. The engine simulation provides a test-bed for evaluating new control laws and for checking and debugging control software and hardware prior to engine testing. The development and use of real-time, hybrid computer simulations of the Pratt and Whitney TF30-P-3 and F100-PW-100 augmented turbofans are described in support of a number of controls research programs at the Lewis Research Center. The role of engine simulations in solving the propulsion systems integration problem is also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71764 , E-8416
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Experimental verification of film-cooling concepts on a turbine vane (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: Film cooling concepts applied to gas turbine vanes were investigated. The filming cooling air was ejected from a single row of holes on the convex surface and a double row of holes of the concave surface. Tests were conducted at a gas temperature of 1260 K, a gas pressure of 3 atmospheres, and a coolant temperature of 280 K. Mass velocity ratios were varied between 0 and 2.0. Data were taken without film cooling holes, with film cooling holes but without blowing, and with blowing. A small amount of blowing into a nonturbulent boundary layer caused an increase in vane temperatures. Film cooling when combined with convection cooling was verified to be more effective than either film or convection cooling alone.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71777 , E-8435
    Format: application/pdf
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