Sverdrup Technology, Inc., Lewis Research Center Group, Cleveland, OH 444135, U.S.A.
Analex Corporation, Fairview Park, OH 44126, U.S.A.
Abstract:
Finite-element, transient heat transfer analyses were performed for the first-stage blades of the space shuttle main engine high-pressure fuel turbopump. The analyses were based on test engine data provided by Rocketdyne. Heat transfer coefficients were predicted by performing a boundary-layer analysis at steady-state conditions with the
5 boundary-layer code. Two different peak-temperature overshoots were evaluated for the startup transient. Cutoff transient conditions were also analyzed. A reduced gas temperature profile based on actual thermocouple data was also considered. Transient heat transfer analyses were conducted with the
finite-element computer code.