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  • Aircraft Propulsion and Power  (11)
  • EOS
  • 1995-1999
  • 1950-1954  (16)
  • 1935-1939
  • 1954  (6)
  • 1952  (10)
Sammlung
Schlagwörter
Erscheinungszeitraum
  • 1995-1999
  • 1950-1954  (16)
  • 1935-1939
Jahr
  • 1
    facet.materialart.
    Unbekannt
    Waves from blasts recorded in Southern California (1952)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 33, no. 6, pp. 427-431, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1952
    Schlagwort(e): Waves ; Seismometer ; Seismology ; EOS
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    BIBLIOGRAFIE SEISMOLOGIE
  • 2
    facet.materialart.
    Unbekannt
    SV and SH (1952)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 33, no. 6, pp. 573-584, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1952
    Schlagwort(e): Waves ; SV waves ; Shear waves ; Seismology ; SH waves ; EOS
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    BIBLIOGRAFIE SEISMOLOGIE
  • 3
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    Unbekannt
    Progress report, Seismological Laboratory, California Institute of Technology, 1951 (1952)
    In:  Trans., Am. Geophys. Union, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 33, no. 6, pp. 759-762, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1952
    Schlagwort(e): Seismology ; Project report/description ; EOS
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    BIBLIOGRAFIE SEISMOLOGIE
  • 4
    facet.materialart.
    Unbekannt
    On the relation between Green's functions and covariances of certain stochastic processes and its application to unbiased linear prediction (1952)
    In:  Transactions Am. Math. Soc., Amsterdam, Academic Press (Elsevier), vol. 72, no. 2, pp. 519-550, pp. 2486, (ISBN 1-86239-117-3)
    Details
    Publikationsdatum: 1952
    Schlagwort(e): Filter- ; Statistical investigations ; Data analysis / ~ processing ; EOS
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    BIBLIOGRAFIE SEISMOLOGIE
  • 5
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    Unbekannt
    Progress report, Seismological Laboratory, California Institute of Technology, 1953 (1954)
    In:  Trans. Am. Geophys. Union, Beijing, Pergamon, vol. 35, no. 3-4, pp. 979-987, pp. 1246
    Details
    Publikationsdatum: 1954
    Schlagwort(e): Seismology ; Project report/description ; EOS
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    BIBLIOGRAFIE SEISMOLOGIE
  • 6
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    Unbekannt
    Investigation of Noise Field and Velocity Profiles of an Afterburning Engine (1954)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Sound pressure levels, frequency spectrum, and jet velocity profiles are presented for an engine-afterburner combination at various values of afterburner fuel - air ratio. At the high fuel-air ratios, severe low-frequency resonance was encountered which represented more than half the total energy in the sound spectrum. At similar thrust conditions, lower sound pressure levels were obtained from a current fighter air craft with a different afterburner configuration. The lower sound pressure levels are attributed to resonance-free afterburner operation and thereby indicate the importance of acoustic considerations in afterburner design.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-E54G07
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 7
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    Unbekannt
    An Investigation in the Ames 40- by 80-Foot Wind Tunnel of a YT-56A Turboprop Engine Incorporating a Decoupler and a Controlled-Feathering Device (1954)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation of a decoupler and a controlled-feathering device incorporated with the YT-56A turboprop engine has been made to determine the effectiveness of these devices in reducing the high negative thrust (drag) which accompanies power failure of this type of engine. Power failures were simulated by fuel cut-off, both without either device free to operate, and with each device free to operate singly. The investigation was made through an airspeed range from 50 to 230 mph. It was found that with neither device free to operate, the drag levels realized after power failures at airspeeds above 170 mph would impose vertical tail loads higher than those allowable for the YC-130, the airplane for which the test power package was designed. These levels were reached in approximately one second. The maximum drag realized after power failure was not appreciably altered by the use of the decoupler although the decoupler did put a limit on the duration of the peak drag. The controlled-feathering device maintained a level of essentially zero drag after power failure. The use of the decoupler in the YT-56A engine complicates windmilling air-starting procedures and makes it necessary to place operating restrictions on the engine to assure safe flight at low-power conditions,
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SA54I09
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 8
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    Unbekannt
    Preliminary Altitude Operational Characteristics of a J57-P1 Turbojet Engine (1954)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: The operational characteristics of a J57-P1 turbojet engine have been investigated at altitudes between 15,000 and 66,000 feet in the Lewis altitude wind tunnel. Included in this study is a discussion of fuel nozzle coking, the altitude operating limits with and without the standard engine control, the compressor surge characteristics, and the engine starting and windmilling characteristics. Severe circumferential turbine outlet temperature gradients which occurred at high altitude as a result of fuel nozzle coking were alleviated by the manufacturer's change in the fuel flow divider schedule and in a nozzle gasket material. Compressor air bleed is required to prevent surge of the outboard compressor in the low engine speed region. The maximum altitude at which the engine was operated without the control was about 66,000 feet at 0.8 flight Mach number and at a reduced engine speed to avoid compressor surge; with the engine control in operation, the altitude operating limit is reduced to approximately 59,000 feet. The maximum altitude at which the engine was started was about 40,000 feet.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE54C31
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 9
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    Unbekannt
    Effect of Rotor- and Stator-Blade Modifications on Surge Performance of an 11-Stage Axial-Flow Compressor. I - Original Production Compressor of XJ40-WE-6 Engine (1952)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds was conducted at the NACA Lewis altitude wind tunnel. This report evaluates the compressor modifications which were restricted to (1) twisting rotor blades (in place) to change blade section angles and (2) inserting new stator diaphragms with different blade angles. Such configuration changes could be incorporated quickly and easily in existing engines at overhaul depots. It was found that slight improvements in the compressor surge limit were possible by compressor blade adjustment. However, some of the modifications also reduced the engine air flow and hence penalized the thrust. The use of a mixer assembly at the compressor outlet improved the surge limit with no appreciable thrust penalty.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE52G03
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 10
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    Unbekannt
    Thrust Augmentation of a Turbojet Engine at Simulated Flight Conditions by Introduction of a Water-Alcohol Mixture into the Compressor (1952)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation was conducted at simulated high-altitude flight conditions to evaluate the use of compressor evaporative cooling as a means of turbojet-engine thrust augmentation. Comparison of the performance of the engine with water-alcohol injection at the compressor inlet, at the sixth stage of the compressor, and at the sixth and ninth stages was made. From consideration of the thrust increases achieved, the interstage injection of the coolant was considered more desirable preferred over the combined sixth- and ninth-stage injection because of its relative simplicity. A maximum augmented net-thrust ratio of 1.106 and a maximum augmented jet-thrust ratio of 1.062 were obtained at an augmented liquid ratio of 2.98 and an engine-inlet temperature of 80 F. At lower inlet temperatures (-40 to 40 F), the maximum augmented net-thrust ratios ranged from 1.040 to 1.076 and the maximum augmented jet-thrust ratios ranged from 1.027 to 1.048, depending upon the inlet temperature. The relatively small increase in performance at the lower inlet-air temperatures can be partially attributed to the inadequate evaporation of the water-alcohol mixture, but the more significant limitation was believed to be caused by the negative influence of the liquid coolant on engine- component performance. In general, it is concluded that the effectiveness of the injection of a coolant into the compressor as a means of thrust augmentation is considerably influenced by the design characteristics of the components of the engine being used.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-E52F20
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
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