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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