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  • PROPULSION SYSTEMS  (266)
  • ASTROPHYSICS
  • 1970-1974  (307)
  • 11
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    Extended temperature range ACPS thruster investigation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The successful hot fire demonstration of a pulsing liquid hydrogen/liquid oxygen and gaseous hydrogen/liquid oxygen attitude control propulsion system thruster is described. The test was the result of research to develop a simple, lightweight, and high performance reaction control system without the traditional requirements for extensive periods of engine thermal conditioning, or the use of complex equipment to convert both liquid propellants to gas prior to delivery to the engine. Significant departures from conventional injector design practice were employed to achieve an operable design. The work discussed includes thermal and injector manifold priming analyses, subscale injector chilldown tests, and 168 full scale and 550 N (1250 lbF) rocket engine tests. Ignition experiments, at propellant temperatures ranging from cryogenic to ambient, led to the generation of a universal spark ignition system which can reliably ignite an engine when supplied with liquid, two phase, or gaseous propellants. Electrical power requirements for spark igniter are very low.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134655
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    A study of the use of liquid base foams for jet noise reduction (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Acoustical properties of liquid base foams and application for jet noise reduction
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-1695
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Auxiliary power unit design studies. Space shuttle APU system selection and performance (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Space shuttle auxiliary power unit design selection and performance evaluation
    Keywords: PROPULSION SYSTEMS
    Type: NASA. MARSHALL SPACE FLIGHT CENTER PROC.- SPACE TRANSPORTATION SYSTEM PROPULSION TECHNOL. CONF., VOL. 3 28 APR. 1971; P 1099-1122
    Format: text
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    NASA TECHNICAL REPORTS
  • 14
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    Investigation of noise from full-scale high bypass engine and blown flap system (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A summary is presented of an acoustic test program for investigating engine noise suppression and jet/flap interaction noise associated with an EBF STOL powered lift system. A highly suppressed TF-34 engine and EBF wing were used in the investigation. The engine was suppressed 21 PndB to a level of 94 PndB. An UTW powered lift system was tested with conventional, mixer, and decayer-type nozzles. The configuration with velocity decayer nozzle and acoustically treated shroud had the lowest noise (98 PndB). An OTW configuration with non-decayer nozzle was about 10 db quieter than the corresponding UTW system. UTW and OTW noise data are compared with scale model correlations.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71539 , E-7946 , Air Transport Meeting; Apr 30, 1974 - May 02, 1974; Dallas
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    Solid propellant rocket motor (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The characteristics of a solid propellant rocket engine with a controlled rate of thrust buildup to a desired thrust level are discussed. The engine uses a regressive burning controlled flow solid propellant igniter and a progressive burning main solid propellant charge. The igniter is capable of operating in a vacuum and sustains the burning of the propellant below its normal combustion limit until the burning propellant surface and combustion chamber pressure have increased sufficiently to provide a stable chamber pressure.
    Keywords: PROPULSION SYSTEMS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 16
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    Highly noise suppressed bypass 6 engine for STOL application (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A TF-34 engine with an acoustically treated ground test nacelle was built and tested to determine the feasibility of suppressing fan and core engine noise to the stringent levels required for STOL or short-haul commercial aircraft. The design incorporates wall treatment for the fan and core plus three treated splitter rings in the inlet and two treated splitters in the aft fan duct. Maximum suppression of fan tone noise of 40-45 dB was obtained from both the inlet and aft fan treatment. At rated fan speed, overall noise was reduced by 21 PNdB to a value of 94 PNdB on a 500-foot sideline. The overall noise reduction value was limited by the jet noise floor. Thrust losses due to the acoustic treatment are also discussed.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1031 , Aero-Acoustics Conference; Oct 15, 1973 - Oct 17, 1973; Seattle, WA
    Format: text
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    NASA TECHNICAL REPORTS
  • 17
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    An injector design model for predicting rocket engine performance and heat transfer (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A model is formulated for estimating the performance and chamber heat transfer in rocket injectors/chambers operating with gaseous H2-O2 propellants. The model quantifies the combustion performance and chamber heat flux for variables such as chamber length, element type, element area ratio, impingement angle, thrust/element, mixture ratio, moment ratio, element spacing, and physical size. Design equations are given and curves are plotted for evaluation of combustion performance in injectors comprised of F-O-F triplet, premix, coaxial and swirl coaxial element types. Curve plots and equations are also included for estimation of the chamber wall heat fluxes generated by these element types.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1242 , Propulsion Conference; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 18
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    Sealing technology for aircraft gas turbine engines (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Experimental evaluation under simulated engine conditions revealed that conventional mainshaft seals have disadvantages of high gas leakage rates and wear. An advanced seal concept, the self-acting face seal, has a much lower gas leakage rate and greater pressure and speed capability. In endurance tests (150 hr) to 43 200 rpm the self-acting seal wear was not measurable, indicating noncontact sealing operation was maintained even at this high rotative speed. A review of published data revealed that the leakage through gas path seals has a significant effect on TSFC, stall margin and engine maintenance. Reducing leakages by reducing seal clearances results in rubbing contact, and then the seal thermal response and wear determines the final seal clearances. The control of clearances requires a material with the proper combination of rub tolerance (abradability) and erosion resistance. Increased rub tolerance is usually gained at the expense of reduced erosion resistance and vice versa.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71607 , E-8096 , Propulsion Conf.; Oct 21, 1974 - Oct 24, 1974; San Diego, CA; United States
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    NASA TECHNICAL REPORTS
  • 19
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    Internal streamline flow analysis for turbopump inducers under cavitating and noncavitating conditions (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Hydrodynamic internal streamline flow analysis for turboprop inducer blades under cavitating and noncavitating conditions
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 70-629 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, PROPULSION JOINT SPECIALIST CONFERENCE, 6TH; Jun 15, 1970 - Jun 19, 1970; SAN DIEGO, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 20
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    Evaluation of acoustic cavities for combustion stabilization. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The stabilizing influence of acoustic cavities (quarterwave acoustic resonators) on acoustic modes of combustion instability has been studied. The ability to analytically predict cavity damping was improved. Relatively good agreement between predicted damping and measured stability was demonstrated. Full-scale motor firings were made to evaluate the influence of several parameters on stability. Results from these firings showed that stability was changed, but not dramatically, by changes in the engine operating conditions. Variations in the film-coolant flowrate do not significantly affect cavity stabilization. The ability to stabilize an engine with unconventional cavity configurations was demonstrated.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 72-1147 , Joint Propulsion Specialist Conference; Nov 29, 1972 - Dec 01, 1972; New Orleans, LA; US
    Format: text
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    NASA TECHNICAL REPORTS
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