A reusable life requirement of 100 missions is met by controlling the combustion chamber hot-gas wall temperature and strain levels. Maximum life, maximum performance, and minimum engine weight are attained through a descriptive parametric assessment of the regenerative cooling circuit, combustor length, contraction area ratio, and coolant passage geometry. Life is categorized by low-cycle fatigue and creep-stress rupture. Relationships are developed to determine the impact of heat transfer rate, thermal strain level, and geometric influence parameters on life. It is empirically shown that a throat heat flux of 100 Btu/sq in./sec can be accommodated.


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    Titel :

    Space Shuttle Orbiter engine main combustion chamber cooling and life


    Beteiligte:
    Cook, R. T. (Autor:in) / Coffey, G. A. (Autor:in)

    Kongress:

    Propulsion Conference ; 1973 ; Las Vegas, NV, US


    Erscheinungsdatum :

    01.11.1973


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Space Shuttle Orbiter Main Engine Design

    Wilhelm, W. F. | SAE Technical Papers | 1972



    Maintainability of the Space Shuttle Orbiter Main Engine

    Goe, R. T. | SAE Technical Papers | 1972


    Space Shuttle Orbiter Alternate Ground Cooling Test Project

    Black, Stephen / Cole, Deborah / Lackie, Warren | AIAA | 1995