| 动叶顶部间隙结构对涡轮性能影响的数值分析 |
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| 引用本文： | 王晓锋,李昌奂,韩飞,陈本森.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(2):24-28. |
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| 作者姓名： | 王晓锋 李昌奂 韩飞 陈本森 |
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| 作者单位： | 西安航天动力研究所,陕西西安,710100 |
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| 基金项目： | 中国航天科技集团公司支撑项目 |
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| 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。
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| 关 键 词： | 液体火箭发动机 涡轮 顶部间隙 |
Numerical analysis on influence of rotor tip clearance structure on turbine performance |
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| WANG Xiao-feng
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LI Chang-huan
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HAN Fei
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CHEN Ben-sen.Numerical analysis on influence of rotor tip clearance structure on turbine performance[J].Journal of Rocket Propulsion,2013,39(2):24-28. |
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| Authors: | WANG Xiao-feng LI Chang-huan HAN Fei CHEN Ben-sen |
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| Institution: | (Xi＇ an Aerospace Propulsion Institute, Xi＇ an 710100, China ) |
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| 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. |
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| Keywords: | liquid rocket engines turbin tip clearance |
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