ANSYS Rocket Engine Turbopump Flowguide Analysis

http://www.cadfamily.com/downinfo/301954.html

In this exercise, we will perform a thermal transient/static structural analysis of
a rocket engine turbo pump flow guide. The flow guide redirects combustion
gases through the pump during operation. Before launch, the flow guide is
cooled to cryogenic temperatures as liquid oxygen is pumped through it.
During launch, the superheated combustion gases heat the flow guide from
cryogenic temperatures (-350F) to over 1400F in approximately 10-seconds.
Although there are negligible mechanical stresses on the part, thermal
gradients are very severe.
The rocket engine is part of a reusable vehicle, which is designed to last for 50
missions. Post flight inspections reveal that the flow guide develops thermo
mechanical fatigue (TMF) cracks in the guide vanes after only one flight.
The goal of the analysis is to determine the time point after launch that has the
highest thermal gradient through the wall of the flow guide, and perform a
stress analysis at this limiting point.