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.
Space Shuttle Orbiter engine main combustion chamber cooling and life
Propulsion Conference ; 1973 ; Las Vegas, NV, US
1973-11-01
Conference paper
No indication
English
Space Shuttle Orbiter Main Engine Design
SAE Technical Papers | 1972
|Maintainability of the Space Shuttle Orbiter Main Engine
SAE Technical Papers | 1972
|