Structural reliability simulation and parameter sensitivity analysis of cooling channel for thrust chamber

被引：0
|
作者：
Zhang S. [1 ]
Jin P. [1 ]
Cai G. [1 ]
机构：
[1] School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing
来源：
Jin, Ping (jinping@buaa.edu.cn) | 2018年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 33期
关键词：
Equivalent stress; Lower confidence limit; Monte Carlo(MC); Regenerative coolingchannel; Stress-strength interference; Structural reliability simulation; Thrust chamber of liquid rocket engine;
D O I：
10.13224/j.cnki.jasp.2018.11.011
中图分类号：
学科分类号：
摘要：
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. © 2018, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：2651 / 2659
页数：8
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