航天推进技术研究院主办
[1]王晓锋,李昌奂,韩 飞,等.动叶顶部间隙结构对涡轮性能影响的数值分析[J].火箭推进,2013,39(02):24-28.
WANG Xiao-feng LI Chang-huan HAN Fei CHEN Ben-sen.Numerical analysis on influence of rotor tip clearance structure on turbine performance[J].Journal of Rocket Propulsion,2013,39(02):24-28.
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WANG Xiao-feng LI Chang-huan HAN Fei CHEN Ben-sen.Numerical analysis on influence of rotor tip clearance structure on turbine performance[J].Journal of Rocket Propulsion,2013,39(02):24-28.
动叶顶部间隙结构对涡轮性能影响的数值分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
39
期数:
2013年02期
页码:
24-28
栏目:
研究与设计
出版日期:
2013-04-30
- Title:
- Numerical analysis on influence of rotor tip clearance structure on turbine performance
- 文章编号:
- 1672-9374(2013)02-0024-05
- Keywords:
- liquid rocket engines; turbin; tip clearance
- 分类号:
- V434+.211
- 文献标志码:
- A
- 摘要:
- 富氧燃气中工作的涡轮动叶顶部间隙较大，导致泄漏损失很大。通过对四种不同动叶顶部结构的涡轮级进行流场数值模拟，比较了其对涡轮性能、流场的影响。结果表明，动叶顶部围带与壳体迷宫结构的泄漏量最小，因而效率损失最小。
- Abstract:
- The large rotor tip clearance of the turbine operating in rich-oxygen gas leads to high leakage loss. In order to investigate the effect of rotor tip structure on turbine performance and flow field, numerical simulations of four rotor tip structures in turbine stage are conducted. The results show that the leakage through the tip clearance formed by tip shroud and labyrinth structure is minimal, so is the efficiency loss.
参考文献/References:
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[6]HELMERS L, KLINGMANN J. Unshrouded rotor tip clearance effects in expander cycle turbines[C]// Proceedings of the ASME Turbo Expo. New York: American Society of Mechanical Engineers, 2002: 111-121.
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备注/Memo
收稿日期：2012-11-06；修回日期：2012-12-28
基金项目：中国航天科技集团公司支撑项目（2008JY07)
作者简介：王晓锋（1976—），男，高级工程师，研究领域为液体火箭发动机涡轮泵设计
更新日期/Last Update:
1900-01-01