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  • 1
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    Preburner of Staged Combustion Rocket Engine (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A regeneratively cooled LOX/hydrogen staged combustion assembly system with a 400:1 expansion area ratio nozzle utilizing an 89,000 Newton (20,000 pound) thrust regeneratively cooled thrust chamber and 175:1 tubular nozzle was analyzed, assembled, and tested. The components for this assembly include two spark/torch oxygen-hydrogen igniters, two servo-controlled LOX valves, a preburner injector, a preburner combustor, a main propellant injector, a regeneratively cooled combustion chamber, a regeneratively cooled tubular nozzle with an expansion area ratio of 175:1, an uncooled heavy-wall steel nozzle with an expansion area ratio of 400:1, and interconnecting ducting. The analytical effort was performed to optimize the thermal and structural characteristics of each of the new components and the ducting, and to reverify the capabilities of the previously fabricated components. The testing effort provided a demonstration of the preburner/combustor chamber operation, chamber combustion efficiency and stability, and chamber and nozzle heat transfer.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-135356 , RI/RD78-114
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Small, high-performance engine component technology status (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Rocketdyne, under contract to NASA-Lewis Research Center, is engaged in developing the technology for major subsystems of a small, high-performance, liquid rocket engine with the capabilities required for high-energy, upper-stage applications. Included in these efforts are the high-pressure turbopumps, preburner, igniter components, and high-area-ratio thrust chamber. A brief description of the engine system and its subsystems is given. The status of the programs is reviewed and the results of the testing conducted are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 76-738 , Propulsion Conference; Jul 26, 1976 - Jul 29, 1976; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Space shuttle orbit maneuvering engine reusable thrust chamber program (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted on the regenerative cooled thrust chamber of the space shuttle orbit maneuvering engine. The conditions for the tests and the durations obtained are presented. The tests demonstrated thrust chamber operation over the nominal ranges of chamber pressure mixture ratio. Variations in auxiliary film coolant flowrate were also demonstrated. High pressure tests were conducted to demonstrate the thrust chamber operation at conditions approaching the design chamber pressure for the derivative space tug application.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-140321 , ASR-73-349
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Nondestructive assessment of penetration of electron-beam welds (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Empirical method correlates penetration of an electron-beam weld with external measurements of the weld. Empirical polygon accurately confirms full-penetration welds while a second, larger polygon provides for penetration of welds near the tip.
    Keywords: FABRICATION TECHNOLOGY
    Type: MSC-15955
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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