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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    Title :

    Space Shuttle Orbiter engine main combustion chamber cooling and life


    Contributors:
    Cook, R. T. (author) / Coffey, G. A. (author)

    Conference:

    Propulsion Conference ; 1973 ; Las Vegas, NV, US


    Publication date :

    1973-11-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





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