In order to evaluate the structural reliability of regenerative cooling channel in thrust chamber body for liquid rocket engine

a structural reliability simulation procedure was established based on finite element thermal-structure coupling calculation. Considering the stochastic influence of engine systems interfering factors

the chambers machining dimension and material performance of the chamber wall

the distribution type of equivalent stress in dangerous points was determined by means of Monte Carlo(MC) simulation and Epps-Pulley(EP) test method. Lower confidence limit of reliability for cooling channel was determined by use of a stress-strength interference model based on the parameter estimation interval

point-low confidence limit method and Lindstrom-Maddens(L-M) method. Then parameter sensitivity was analyzed. Results indicated that dangerous points of inner wall were determined according to the structure reliability simulation

and lower confidence limit of reliability was obtained

making it more practical in engineering. The strength margin of outer wall was much greater than that of inner wall and the structural reliability of cooling channel depended on inner wall. It was an efficient approach to improve structural reliability by enhancing combustion efficiency or selecting inner materials with slightly lower thermal conductivity and higher strength.