Numerical Investigation on the Service Life of a Liquid Rocket Engine Thrust Chamber

Rocket engine thrust chambers withstand very high temperatures and thermal gradients during service that induce multiple damaging phenomena such as plasticity, low-cycle-fatigue (LCF) creep. Numerical models can be used the design of these mechanical components in order to simulate main processes, accounting for complex material behavior due non-linear hardening viscoplasticity. This work represents an improvement upon previous research by authors, with particular reference addition Wang–Brown fatigue criterion, consider effects multiaxiality non-proportionality loads, Voce model account isotropic hardening. A precipitation hardened copper alloy has been considered chamber internal structure. The most critical areas resulted on surface correspondence throat region, consistently experimental tests available literature conducted similar geometries. Results demonstrated low cycle ratcheting (plastic instability) are dominant test case.