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  • 1
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    Effects of engine inlet disturbances on engine stall performance (1971)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-20
    Beschreibung: Effects of engine inlet disturbances on engine stall performance
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 313-341
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 2
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    Technical and economic feasibility study of solar/fossil hybrid power systems (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Results show that new hybrid systems utilizing fossil fuel augmentation of solar energy can provide significant capital and energy cost benefits when compared with solar thermal systems requiring thermal storage. These benefits accrue from a reduction of solar collection area that results from both the use of highly efficient gas and combined cycle energy conversion subsystems and elimination of the requirement for long-term energy storage subsystems. Technical feasibility and fuel savings benefits of solar hybrid retrofit to existing fossil-fired, gas and vapor cycle powerplants was confirmed; however, economic viability of steam cycle retrofit was found to be dependent on the thermodynamic and operational characteristics of the existing powerplant.
    Schlagwort(e): ENERGY PRODUCTION AND CONVERSION
    Materialart: NASA-TM-73820 , E-9409
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 3
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    Effect of screen-induced total-pressure distortion on axial-flow compressor stability (1974)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An experimental investigation was made to determine the effects of screen-induced total-pressure distortions on two J85-GE-13 turbojet engines. Results were compared to those from a previous program run with a third engine. All compressors were found to be sensitive to a critical angle of circumferential distortion equal to 60 deg., and they all adhered closely to the parallel compressor model. The sensitivity of compressor exit pressure to virtually any type of distortion pattern can be determined by defining stall lines for undistorted, hub radial distorted, and tip radial distorted inflows. The effect of multiple sectors of circumferential distortion is defined.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-3017 , E-7792
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 4
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    Instantaneous distortion in a Mach 2.5, 40-percent-internal-contraction inlet and its effect on turbojet stall margin (1974)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An experimental wind tunnel investigation was conducted to determine the effects of time-variant distortions produced in a supersonic inlet on a J85-GE-13 turbojet engine. Results are presented principally in terms of instantaneous distortion amplitudes and total-pressure contours measured through compressor stall. They indicate that, although a time-averaged distortion may be far from a stall-inducing value, corresponding instantaneous distortion amplitudes can approach or exceed this value. Seven engine stall events were studied. In six of these events instantaneous distortion peaks of sufficient magnitude to cause stall were observed in the time period shortly before stall was detected.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-3002 , E-6294
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 5
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    Dynamic flow angle measurements at the diffuser exit of a Mach 2.5 mixed compression inlet (1972)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An exploratory investigation was made to determine the magnitude of the dynamic flow angle at a single point in the diffuser exit of a Mach 2.50 inlet. Results indicate that the maximum flow angle variation was + or - 3 degrees except when vortex generators were installed in the subsonic diffuser. The amplitude of these flow angle fluctuations was directly related to the amplitude of the total pressure fluctuations at the probe survey point. Flow angle fluctuations as high as + or - 11 degrees were recorded when vortex generators were installed near the probe survey point.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2497 , E-6606
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 6
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    Unbekannt
    Unstart and stall interactions between a turbojet engine and an axisymmetric inlet with 60-percent internal-area contraction (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Effects of turbojet engine unstart on engine operation and characteristics of stall propagation through compressor and inlet system
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2192 , E-5923
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 7
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    Experimental investigation of dynamic distortion in a Mach 2.50 inlet with 60 percent internal contraction and its effect on turbojet stall margin (1969)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Dynamic distortion of supersonic wind tunnel for turbojet engines
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-1842 , E-5102
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 8
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    Formulation of a distortion index based on peak compressor pressure ratios (1974)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: In order to effectively use a compressor face total-pressure distortion index as a measure of inlet-engine compatibility, a correlation of distortion amplitude with stall margin must be developed with minimal scatter. A recent analysis of data recorded in extensive distortion screen tests with the J85-GE-13 turbojet engine has resulted in a correlation based on compressor discharge pressure ratioed to the minimum pressure at the compressor face. Simply by determining compressor stall lines with a single hub radial distortion pattern, a single tip radial pattern, and with undistorted inflow, the overall compressor pressure ratio at stall for even the most complex distortion pattern was found to be predictable.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: National Conference on Environmental Effects on Aircraft and Propulsion Systems; May 21, 1974 - May 23, 1974; Trenton, NJ
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 9
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    Instantaneous distortion investigation (1972)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The results obtained in an inlet-engine compatibility test run in the 10x10 SWT of the NASA-Lewis Research Center are reviewed. This program was run to measure the time-variant distortions produced in a supersonic inlet and to relate a unique distortion peak, occurring in an instant of time, to the origin of stall in a compressor. The major stumbling block in this type of effort is the determination of a proper increment of time over which to average pressures before computing distortions. It is reasonable to expect that the proper averaging time is related to the particular compressor in question. The most significant point reported is that the proper averaging time may not be solely dependent on a particular compressor, and, in fact, may vary with operating conditions, even for the same inlet-engine combination.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-68189 , E-7329 , Tech. Interchange Meeting of Air Inlets and Diffusers Panel; Sep 19, 1972; Naval Aeroballistics Comm., Dahlgren, VA; United States
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 10
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    Unbekannt
    Instantaneous and dynamic analysis of supersonic inlet-engine compatibility (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Wind tunnel tests for instantaneous and dynamic analysis of effects of time-variant distortions produced in supersonic inlet on J85-GE-13 turbojet engine
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-67821
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
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