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  • AIRCRAFT PROPULSION AND POWER  (54)
  • 1980-1984
  • 1975-1979  (54)
  • 1935-1939
  • 1979  (54)
  • 1
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    Study of blade aspect ratio on a compressor front stage aerodynamic and mechanical design report (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A single stage compressor was designed with the intent of demonstrating that, for a tip speed and hub-tip ratio typical of an advanced core compressor front stage, the use of low aspect ratio can permit high levels of blade loading to be achieved at an acceptable level of efficiency. The design pressure ratio is 1.8 at an adiabatic efficiency of 88.5 percent. Both rotor and stator have multiple-circular-arc airfoil sections. Variable IGV and stator vanes permit low speed matching adjustments. The design incorporates an inlet duct representative of an engine transition duct between fan and high pressure compressor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159555 , PWA-5583-25
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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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
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Manufacture of low carbon astroloy turbine disk shapes by hot isostatic pressing. Volume 2, project 1 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The performance of a hot isotatic pressed disk installed in an experimental engine and exposed to realistic operating conditions in a 150-hour engine test and a 1000 cycle endurance test is documented. Post test analysis, based on visual, fluorescent penetrant and dimensional inspection, revealed no defects in the disk and indicated that the disk performed satisfactorily.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135410 , PWA-5574-37
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Quiet Clean Short-haul Experimental Engine (QCSEE). Double-annular clean combustor technology development report (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A sector combustor technology development program was conducted to define an advanced double annular dome combustor sized for use in the quiet clean short haul experimental engine (QCSEE). A design which meets the emission goals, and combustor performance goals of the QCSEE engine program was developed. Key design features were identified which resulted in substantial reduction in carbon monoxide and unburned hydrocarbon emission levels at ground idle operating conditions, in addition to very low nitric oxide emission levels at high power operating conditions. Their significant results are reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159483 , R79AEG397
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Effect of forward velocity and crosswind on the reverse-thrust performance of a variable-pitch fan engine (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Variable-pitch-fan engines may be attractive for future short-haul aircraft if sufficient reverse thrust is available for aircraft deceleration after touchdown. Thrust reversal is obtained in these engines by changing fan blade pitch about 90 deg, which causes the fan airflow to enter the fan duct nozzle and exhaust through the fan inlet. This capability would eliminate the heavy and costly thrust reverser system required for current fixed-pitch turbofan engines. NASA has, therefore, supported the development of advanced technology for a quiet, clean, high-bypass-ratio turbofan engine for future short-haul aircraft. In connection with this program, tests were conducted to determine the effect of forward velocity and angle of attack on steady-state reverse-thrust performance. Other objectives of the tests were related to the determination of the effect of forward velocity on forward-to-reverse thrust transient performance and the determination of the effectiveness of an overshoot blade angle technique to establish reverse thrust during a transient. The results of the tests are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 79-0105 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Design and performance of the propulsion system for the quiet short-haul research aircraft /QSRA/ (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the design and performance of the Quiet Short-Haul Research Aircraft (QSRA) propulsion system. A discussion of the mixed-flow boundary layer control (BLC) system, which uses high and low pressure engine bleed air, is included. This system seriously affected propulsion system performance, particularly engine acceleration characteristics, requiring an integration of BLC system and powerplant controls. Funding limitations for the QSRA Project prevented extensive full-scale testing and systems mockups, resulting in a high reliance on small-scale tests and analytical techniques. Ground tests of the actual aircraft systems showed that the extrapolation of small-scale tests and analytical techniques were in good agreement with measured full-scale results.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 79-1313 , AIAA, SAE, and ASME, Joint Propulsion Conference; Jun 18, 1979 - Jun 20, 1979; Las Vegas, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Effect of forward velocity and crosswind on the reverse-thrust performance of a variable-pitch fan engine (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A full-size variable-pitch fan engine was tested in the Ames 40 by 80 foot wind tunnel to determine the effect of forward velocity and crosswind on reverse-thrust performance. Two flight-type inlet configurations were tested, and a flared fan nozzle was installed as an inlet for reverse-thrust operation. Steady-state reverse-thrust performance was obtained up to 54 m/s (105 knots). An abrupt decrease in reverse thrust occurred at about 30 m/s (60 knots). Reverse thrust was established following forward-to-reverse thrust transients both statically and with forward velocities only up to 30 m/s.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-79059 , E-9873 , AIAA PAPER 79-0105 , Aerospace, Sci. Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    The effect of fuel sprays on emissions from a gas turbine combustor (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A research gas turbine combustor which allows for independent control of drop size, fuel/air ratio, air inlet temperature, pressure, reference velocity, and residence time has been used to study the influence of fuel spray characteristics on primary zone emissions. Local concentrations of oxides of nitrogen, carbon monoxide and unburned hydrocarbons at various locations in the flow, local gas temperature, gas velocity, and the turbulence intensity (measured with laser velocimetry) are obtained. A comprehensive data analysis program to compute the local fuel/air ratio and the sum of the mole fractions of the species present confirms the validity of the emissions data. Increasing drop size is correlated with an increase in unburned hydrocarbons, while increasing residence time is associated with sharp decreases in hydrocarbons and carbon monoxide and an increase in oxides of nitrogen.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 79-1321 , AIAA, SAE, and ASME, Joint Propulsion Conference; Jun 18, 1979 - Jun 20, 1979; Las Vegas, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Aerodynamics of a tilt-nacelle V/STOL propulsion system (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Tests were performed in the Ames 40 by 80 Foot Wind Tunnel on a large-scale, tilt-nacelle V/STOL propulsion system to determine its aerodynamic characteristics. Unpowered nacelle aerodynamics and power induced effects over an angle of attack range from 0 to 105 deg are presented. It is shown that: (1) the characteristics of the unpowered nacelle can be estimated with annular airfoil data, (2) the power-induced effects on the nacelle aerodynamics are significant, and (3) pitching moment can be correlated with lift and thrust.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78606 , A-7849 , Workshop of V/STOL Aerodynamics; May 01, 1979; Monterey, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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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
    Format: text
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    NASA TECHNICAL REPORTS
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