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  • 1970-1974  (2)
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  • 1
    Publication Date: 2019-07-13
    Description: 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.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1310 , Propulsion Conference; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; US
    Format: text
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  • 2
    Publication Date: 2019-07-13
    Description: An empirical separation and side load model to obtain applied aerodynamic loads has been developed based on data obtained from full-scale J-2S (265K-pound-thrust engine with an area ratio of 40:1) engine and model testing. Experimental data include visual observations of the separation patterns that show the dynamic nature of the separation phenomenon. Comparisons between measured and applied side loads are made. Correlations relating the separation location to the applied side loads and the methods used to determine the separation location are given.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1284 , Propulsion Conference; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; US
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