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  • 1
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    Evaluation of seals for high-performance cryogenic turbomachines (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An approach to computing flow and dynamic characteristics for seals or bearings is discussed. The local average velocity was strongly influenced by inlet and exit effects and fluid injection, which in turn drove zones of secondary flow. For the restricted three-dimensional model considered, the integral averaged results were in reasonable agreement with selected data. Unidirectional pressure measurements alone were insufficient to define such flow variations. However, for seal and bearing leakage correlations the principles of corresponding states were found to be useful. Also discussed are three phenomena encountered during testing of three eccentric nonrotating seal configurations for the Space Shuttle Main Engine (SSME) Program. Fluid injection, choking within a seal, and pressure profile crossover are related to postulated zones of secondary flow or separation and to direct stiffness.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-88919 , E-3348 , NAS 1.15:88919
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Qualitative investigation of cryogenic fluid injection into a supersonic flow field (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The behavior of liquid nitrogen injected into a supersonic nitrogen flow field was investigated using an experimental apparatus in which a Mach 2.7 2D gas nitrogen tunnel is coupled with a high-pressure cryogenic source. Observations were monitored and recorded via a video camera and a motion picture camera. It was found that the penetration of a supersonic flow field by injection of liquid nitrogen is strongly dependent on the flow Mach number, the cryogen injection pressure (Pi/Pc), the injector configuration, and the cryogen temperature. For a 2D gaseous N2, Mach 2.7 tunnel, with cryogen injection Pi/Pc approaching 2, the injected fluid penetration for the 1/8-in. injection port approached one half of the tunnel width at 90-deg injection, and one fourth of the tunnel width at 20-deg injection.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: 1989 Cryogenic Engineering Conference; Jul 24, 1989 - Jul 28, 1989; Los Angeles, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Seals For Cryogenic Turbomachines (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Analysis considers effects of seals on stability. Report presents method of calculation of flows of cryogenic fluids through shaft seals. Key to stability is local average velocity in seal. Local average velocity strongly influenced by effects of inlet and outlet and injection of fluid.
    Keywords: MACHINERY
    Type: LEW-14556 , NASA Tech Briefs (ISSN 0145-319X); 12; 8; P. 82
    Format: text
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    NASA TECHNICAL REPORTS
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