|Table of Contents|

Design and flow analysis of partial admission turbine for rocket engine(PDF)

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

Issue:
2018年03期
Page:
30-36
Research Field:
研究与设计
Publishing date:

Info

Title:
Design and flow analysis of partial admission turbine for rocket engine
Author(s):
MAO Kai;  WANG Xiaofeng;  LI Changhuan;  YUAN Weiwei
Xi'an Aerospace Propulsion Institute, Xi'an 710100, China
Keywords:
partial admission turbine;  supersonic impulse turbine;  turbine design;  flow analysis
PACS:
V343.21-34
DOI:
-
Abstract:
According to the overall performance and structure requirements of a liquid rocket engine, a partial admission, conical nozzle and single-stage supersonic impulse turbine were designed with one-dimensional engineering method. By solving Reynolds-averaged Navier-Stocks(RANS)equations, the three-dimensional viscous steady-state simulation and analysis are performed for the internal flow field of the turbine. For the rotor cascade channel, the influence of area varieties on turbine performance is studied. The results show that the internal streamline of the partial admission turbine is irregular, and there are more eddy flows, complicated rotor cascade shock and serious separation in the blade channel. The total pressure loss in the nozzle channel and rotor cascade channel is more than 20%, and the pressure loss in the later is greater. The variation of rotor cascade channel area has little effect on the overall performance of turbine, but the convergent-divergent type channel can reduce the flow velocity and relieve the gas flow separation, which is helpful in reducing the temperature difference stress of blade.

References:

[1] 隋秀明.低进气度部分进气涡轮气动设计与内部流动研究[J].工程热物理学报,2013,34(3):419-422
[2] 隋秀明.导叶展弦比对部分进气涡轮性能影响的数值研究[J].工程热物理学报,2015,36(7):1442-1446.
[3] 严俊峰, 逯婉若.冲击式涡轮内部流动数值研究[J].火箭推进,2009,35(1):31-35.
Yan Junfeng, LU Wanre. Numerical analysis of inner flow field for an impulse turbine [J]. Journal of rocket propulsion, 2009, 35(1): 31-35.
[4] 伊进宝.部分进气燃气涡轮机叶轮流场数值模拟[J].鱼雷技术,2010,18(6):456-460.
[5] 李旭升.动叶围带顶部泄漏对冲击式涡轮气动性能影响的研究[J].导弹与航天运载技术,2015(1):17-21.
[6] 奥夫相尼科夫.液体火箭发动机涡轮泵装置原理与计算[M]. 任汉芬译.北京:航天工业总共公司第十一研究所,1999.
[7] 刘国球.液体火箭发动机原理[M].北京:中国宇航出版社,2009.
[8] 张远君.液体火箭发动机涡轮泵设计[M].北京:北京航空航天大学出版社.1995.
[9] 王雨琦.部分进气超临界二氧化碳向心透平气动性能研究[J].热力透平,2016,45(3):184-188.
[10] 屈焕成.汽轮机调节级三维复杂流动的数值研究[J].热科学与技术,2011,10(1):82-87.
[11] 蒋彬.微型冲动式部分进气涡轮机的流程特性及气动损失[J].热能与动力工程,2015,30(6):873-879.
[12] 郑晓宇, 林奇燕, 王磊.小型部分进气亚声速涡轮流动损失研究及优化[J].火箭推进,2017,43(1):32-37.
ZHENGXiaoyu, LI Qiyan, WANG Lei. Research and optimization for flow loss of a small partial admission subsonic turbine [J]. Journal of rocket propulsion, 2017, 43(1): 32-37.

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Last Update: 2018-06-30