喉衬组件界面密封失效敏感因素研究

推进技术 ›› 2016, Vol. 37 ›› Issue (6): 1151-1157.

喉衬组件界面密封失效敏感因素研究

闫宝任,张露,史宏斌,唐敏

西安航天动力技术研究所，陕西西安 710025,西安航天动力技术研究所，陕西西安 710025,西安航天动力技术研究所，陕西西安 710025,西安航天动力技术研究所，陕西西安 710025

发布日期:2021-08-15
作者简介:闫宝任，男，硕士生，研究领域为固体火箭发动机热结构。

Ivestigation on Sensitive Factors of Seal Interface

Xi’an Institute of Aerospace Propulsion ，Xi’an 710025，China,Xi’an Institute of Aerospace Propulsion ，Xi’an 710025，China,Xi’an Institute of Aerospace Propulsion ，Xi’an 710025，China and Xi’an Institute of Aerospace Propulsion ，Xi’an 710025，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究更为准确的边界仿真方法，针对典型长时间工作发动机，基于ABAQUS软件，通过二次开发建立一套工程可用的喉衬组件传热和背壁热解的数值模拟方法，并对影响喉衬组件温度场的主要影响因素进行分析；对影响背壁热解的关键材料参数进行统计，获得其分布规律；采用Mote-Carlo法获得随机输入参数，通过大量计算，建立输入和输出的近似模型；应用神经网络模拟方法，获得了影响喉衬组件界面密封状态的主要敏感参数。结果表明，数值模拟方法具有较高的精度。

关键词: 喉衬组件；温度场；神经网络；敏感参数；数值模拟

Abstract: In order to study more accurate boundary simulation method，firstly，based on ABAQUS software，this paper established a secondary development method to simulate the throat liner component heat transfer and insulator pyrolysis，and study the main factors influencing temperature field of throat liner component aiming at a typical long time working engine. Secondly，statistics of key parameters affecting insulator pyrolysis were accomplished to obtain the regularity of distribution. Then，the Mote-Carlo method was used to obtain random input parameters，and the approximate model of input and output was established through a large amount of calculation. Finally，the main sensitive parameters that affect sealed interface of throat liner component were obtained by using neural network simulation method. The results show that the simulation method has high accuracy.

Key words: Throat liner component；Temperature field；Neural network；Sensitive factor；Numerical simulation

闫宝任,张露,史宏斌,唐敏. 喉衬组件界面密封失效敏感因素研究[J]. 推进技术, 2016, 37(6): 1151-1157.

YAN Bao-ren,ZHANG Lu,SHI Hong-bin,TANG Min. Ivestigation on Sensitive Factors of Seal Interface[J]. Journal of Propulsion Technology, 2016, 37(6): 1151-1157.

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