|Table of Contents|

Numerical simulation of opening force for circumferential segmented seal(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2019年05期
Page:
45-51
Research Field:
研究与设计
Publishing date:

Info

Title:
Numerical simulation of opening force for circumferential segmented seal
Author(s):
LI Xiaofen1;  ZHOU Rui2;  TU Ting1
(1.Beijing Aerospace Propulsion Institute, Beijing 100076, China;2.Xi’an Aerospace Propulsion Institute, Xi’an 710100, China)
Keywords:
circumferential segmented seal;  Rayleigh step hydrodynamic lift pad;  opening force;  three-dimensional numerical simulation
PACS:
V434.1
DOI:
-
Abstract:
The helium gas isolation seal in the oxygen turbopump of LOX/LH2 rocket engine is used to prevent the mixture of the liquid oxygen and the hydrogen-enriched gas driving the turbine.At present, the main application of helium seal abroad is the circumferential segmented seal with Rayleigh step hydrodynamic lift pad, which can effectively reduce the helium leakage.The key to this seal design is to calculate the opening force generated by Rayleigh step hydrodynamic lift pad.In this paper, the opening force was calculated by Fluent fluid analysis software, andthe accuracy of the three-dimensional simulation calculation method was verifiedby compared with the results of one-dimensional calculation method and the calculation results in foreign literatures.In addition, the effects of the gas film thickness, the number and the depth of Rayleigh steps, the distortion of shaft and Rayleigh step caused by machining errors on the opening force were analyzed.The opening force decreases with the gas film thickness increasing.The opening force reaches its maximum when the depth of Rayleigh steps is 0.01 mm.The larger the shaft distortion and the Rayleigh step, the smaller the opening force.

References:

[1] 郑大勇, 陶瑞峰, 张玺, 等.大推力氢氧发动机关键技术及解决途径[J].火箭推进, 2014, 40(2): 22-27, 35.ZHENG D Y, TAO R F, ZHANG X, et al.Study on key technology for large thrust LOX/LH2 rocket engine[J].Journal of Rocket Propulsion, 2014, 40(2): 22-27, 35.
[2] 周芮, 孙晓伟, 吴玉珍, 等.氢氧发动机氧涡轮泵圆周分段氦密封研究现状[C]//中国航天第三专业信息网第三十八届技术交流会暨第二届空天动力联合会议论文集.大连:中国航天第三专业信息网,2017.
[3] OIKE M, NAGAO R.Characteristics of a shaft seal system for the LE-7 liquid oxygen turbopump:AIAA 95-3102[R].USA:AIAA,1995.
[4] BURCHAM R E.High-speed cryogenic self-acting shaft seals for liquid rocket turbopumps:NASA CR 168194 [R].USA:NASA, 1983.
[5] 王飞, 刘向锋, 刘莹.浅槽环瓣型浮动环密封的性能分析[J].润滑与密封, 2005, 30(6): 74-76, 85.
[6] BUECHAM R E.Liquid rocket engine turbopump rotating-shaft seals:NASA SP-8121 [R].USA:NASA, 1978.
[7] SHAOIRO W, LEE C C.Advanced helium purge seals for liquid oxygen(LOX)turbopumps: NASA CR 182105 [R].USA:NASA,1989.
[8] ZUK J.Fundamentals of fluid sealing: NASA TN D-8121[R].USA:NASA, 1976.
[9] BRUNETIERE N, TOURNERIE B, FRENE J.Influence of fluid flow regine on performances of non-contacting liquid face seals[J].Journal of Tribology, 2002, 124(3): 515.
[10] OIKE M, NOSAKA M.Study on a carbon segmented circumferential seal for a liquid oxygen turbopump[C]// Proceeding of the Japan International Tribology Conference.Nagoya,Japan:Japan Association of Tribologists,1990.

Memo

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Last Update: 2019-10-25