Predicting method of safety life of reusable liquid rocket engine turbopump

Shijie LIU; Dengfeng LIU; Xiaoqiu MA; Guozhu LIANG

doi:10.13224/j.cnki.jasp.20210420

Chinese

您当前的位置：

首页 >

文章列表页 >

Predicting method of safety life of reusable liquid rocket engine turbopump

Rocket Engine | 更新时间：2025-04-07

- Predicting method of safety life of reusable liquid rocket engine turbopump
- Journal of Aerospace Power Vol. 37, Issue 5, Pages: 1079-1089(2022)
- 作者机构：
  
  1.中国航天科技集团有限公司北京航天动力研究所，北京 100076
  2.中国航天科技集团有限公司北京航天动力研究所;低温液体推进技术实验室，北京 100076
  3.北京航空航天大学宇航学院，北京 102206
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210420
  CLC：
- 稿件说明：
移动端阅览
Shijie LIU, Dengfeng LIU, Xiaoqiu MA, et al. Predicting method of safety life of reusable liquid rocket engine turbopump[J]. Journal of Aerospace Power, 2022, 37(5): 1079-1089.
DOI：

Shijie LIU, Dengfeng LIU, Xiaoqiu MA, et al. Predicting method of safety life of reusable liquid rocket engine turbopump[J]. Journal of Aerospace Power, 2022, 37(5): 1079-1089. DOI： 10.13224/j.cnki.jasp.20210420.

摘要

利用复杂系统寿命分布模型和故障树分析（FTA）理论建立了涡轮泵的安全寿命预估方法，并以航天飞机主发动机（SSME）高压液氢涡轮泵（HPFTP）的安全寿命预估为例，对该方法进行了说明。研究结果表明：①当待考核的HPFTP关键部件数大于10时，其寿命模型可以用指数分布近似表示，数目越多近似结果越可靠；②HPFTP的平均无故障工作时间（MTBF）为76 917 h，平均维修时间（MTTR）为8 879 h，0.998 8可靠度对应的安全寿命为25 575 s，可安全使用49次；0.999 6可靠度对应的安全寿命为8 521 s，可安全使用16次；安全使用11次对应的可靠度为0.999 7；③HPFTP涡轮叶片和喷嘴对应的关键重要度分别是0.217 5和0.216 6，集液器和叶轮对应的关键重要度都是0.174 2。该研究方法可为液体火箭发动机涡轮泵等复杂组件可重复使用性研究提供一定的参考。

Abstract

Based on the life distribution model of complex system and fault tree analysis （FTA） theory，a safety life prediction method of turbopump was established.As an example，the safety life of the high pressure liquid hydrogen turbopump （HPFTP） of the space shuttle main engine （SSME） was verified to demonstrate this method.The results showed that：（1） The life of complex system roughly followed the exponential distribution when the number of HPFTP critical components was more than 10，and a more reliable result accompanied a larger number.（2） The mean time between failure （MTBF） and mean time to repairment （MTTR）of HPFTP was 76 917 h and 8 879 h，respectively，and the safety life of 0.998 8 reliability was 25 575 s，which can be used 49 times safely；the safety life of 0.999 6 reliability was 8 521 s，which can be used for 16 times；the reliability was 0.999 7 for 11 times safety use.（3） The key components of HPFTP safety life were turbine blade and nozzle，and their corresponding critical importance was 0.217 5 and 0.216 6，respectively，and the critical importance of both liquid collector and the impeller was 0.174 2.This work can provide a reference for the reusability research of complex components such as liquid rocket engine turbopump.

关键词

Keywords

references

CIKANEK H A . Characteristics of space shuttle main engine failures [R]. AIAA⁃87 ⁃ 1939 ,1987.

ABDUL⁃AZIZ A , THOMPSON R L . Thermal⁃structural analysis of space shuttle main engine （SSME） hot section components [R]. NASA⁃22404 , 1988 .

PASTER R D , STOHLER S L . SSME evolution [R]. AIAA⁃1989⁃2618 ， 1989 .

WILLIAMS W C . Report of the SSME assessment team [R]. Washington DC ： National Aeronautics and Space Administration,N93⁃21645 , 1993 .

ABDUL⁃AZIZ A . Structural evaluation of a space shuttle main engine （SSME） high pressure fuel turbopump turbine blade [R]. NASA⁃CR⁃198428 , 1996 .

BLAIR J C , RYAN R S . Lessons learned in engineering [R]. NASA/CR⁃216468 , 2011 .

刘士杰 , 梁国柱 . 航天飞机主发动机高压燃料涡轮泵的故障模式 [J]. 航空动力学报， 2015 , 30 （ 3 ）: 611 ⁃ 626 .

LIU Shijie , LIANG Guozhu . Failure modes of space shuttle main engine high‑pressure fuel turbopump [J]. Journal of Aerospace Power , 2015 , 30 （ 3 ）: 611 ⁃ 626 . （in Chinese）

DRENICK R F . The failure law of complex equipment [J]. Journal of the Society for Industrial and Applied Mathematics ， 1960 , 8 （ 4 ）: 680 ⁃ 690 .

TANG S D , WANG F Q . Reliability analysis for a repairable parallel system with time⁃varying failure rates [J]. Applied Mathematics:A Journal of Chinese Universities ， 2005 , 20 （ 1 ）: 85 ⁃ 90 .

COLLINS D H , WARR R L . Failure time distributions for complex equipment [J]. Quality and Reliability Engineering International , 2018 , 35 （ 1 ）: 1 ⁃ 9 .

刘士杰 , 梁国柱 . FTA方法在SSME高压氢泵可靠性分析中的应用 [C]∥ 2011年中国航天第三专业信息网学术交流会论文集 . 甘肃敦煌：中国航天第三专业信息网 , 2011 : 790 ‑ 797 .

刘士杰 , 康红雷 , 梁国柱 , 液体火箭发动机重复使用性指标分配方法的初探 [C]∥ 第三届空天推进技术会议论文集 . 福建厦门 : 中国航天科技集团第六研究院有限公司， 2021 : 82 ‑ 91 .

金星 , 洪延姬 , 沈怀荣 , 等 . 工程系统可靠性数值分析方法 [M]. 北京 : 国防工业出版社 , 2002 .

FRAGOLA J R , MAGGIO G . Probabilistic risk assessment of the space shuttle.phase 3:a study of the potential of losing the vehicle during nominal operation [R]. NASA⁃CR⁃197810 , 1995 .

丁定浩,可靠性与维修性工程:系统与电路结构的分析和设计 [M]. 北京 : 电子工业出版社 , 1986 .

SINGH C . Calculating the time⁃specific frequency of system failure [J]. IEEE Transactions on Reliability ， 1979 ,R⁃ 28 （ 2 ）: 124 ⁃ 126 .

SINGH C , BILINTON R . A new method to determine the failure frequency of a complex system [J]. Microelectronics Reliability ， 1973 , 12 （ 5 ）: 459 ⁃ 465 .

石彬,基于故障树的EPS系统可靠性及失效模式仿真研究 [D]: 杭州:浙江大学 , 2007 .

SHI Bin . Study on the reliability and failure modes simulation of EPS system based on FTA [D]. Hangzhou : Zhejiang University , 2007 . （in Chinese）

刘士杰 , 梁国柱 , 重复使用液体火箭发动机可用度的数字仿真 [J]. 北京航空航天大学学报， 2015 , 41 （ 12 ）: 132 ⁃ 140 .

LIU Shijie , LIANG Guozhu . Digital simulation on resuable liquid rocket engine availability [J]. Journal of Beijing University of Aeronautics and Astronautics , 2015 , 41 （ 12 ）: 132 ⁃ 140 . （in Chinese）

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Failure mechanism and improvement of ball bearing in aliquid rocket engine turbopump

A multi cycle propulsion system for amphibious unmanned aerial vehicle with repeatable water exit

Cavitation modeling and start⁃up under⁃rated pressure simulation of liquid rocket engine

Analysis of scrapping characteristics and reliability of civil aero engine high pressure turbine blade in dual failure modes

Rolling bearing reliability evaluation method based on LTSA fusion dimensionality reduction method

Related Author

ZHANG Wenhu

LI Wenchao

DENG Sier

ZHANG Song

ZHENG Yanwei

Jun TIAN

Yufan XIE

Fei LONG

Related Institution

China Special Vehicle Research Institute，Aviation Industry Corporation of China，Limited

Airport Support Bureau，Air Force Logistics Department

Nanjing Puguo Technology Company，Limeted

National Key Laboratory of Science and Technology on Liquid Rocket Engines，Xi'an Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation

System Engineering Department，MTU Maintenance Zhuhai Company Limited

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰