Predicting method of safety life of reusable liquid rocket engine turbopump

被引：0

作者：

Liu S. ^{[1
,2
]}

Liu D. ^{[1
]}

Ma X. ^{[1
,2
]}

Liang G. ^{[3
]}

机构：

[1] Beijing Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Beijing

[2] Laboratory of Science and Technology on Cryogenic Liquid Propulsion, Beijing Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Beijing

[3] School of Astronatuics, Beihang University, Beijing

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2022年 / 37卷 / 05期

关键词：

Fault tree analysis; Life distribution; Liquid rocket engine; Reliability; Turbopump;

D O I：

10.13224/j.cnki.jasp.20210420

中图分类号：

学科分类号：

摘要：

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. © 2022, Editorial Department of Journal of Aerospace Power. All right reserved.

引用

页码：1079 / 1089

页数：10

共 18 条

[1]

CIKANEK H A., Characteristics of space shuttle main engine failures, (1987)

[2]

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

[3]

PASTER R D, STOHLER S L., SSME evolution, (1989)

[4]

WILLIAMS W C., Report of the SSME assessment team, (1993)

[5]

ABDUL-AZIZ A., Structural evaluation of a space shuttle main engine (SSME) high pressure fuel turbopump turbine blade, (1996)

[6]

BLAIR J C, RYAN R S., Lessons learned in engineering, (2011)

[7]

LIU Shijie, LIANG Guozhu, Failure modes of space shuttle main engine high‑pressure fuel turbopump, Journal of Aerospace Power, 30, 3, (2015)

[8]

DRENICK R F., The failure law of complex equipment, Journal of the Society for Industrial and Applied Mathematics, 8, 4, (1960)

[9]

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

[10]

COLLINS D H, WARR R L., Failure time distributions for complex equipment, Quality and Reliability Engineering International, 35, 1, pp. 1-9, (2018)

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