| 跨声压气机周向槽处理机匣非设计工况研究 |
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| 引用本文： | 祝剑虹,朴英,周建兴,岂兴明.跨声压气机周向槽处理机匣非设计工况研究[J].航空动力学报,2008,23(4):687-692. |
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| 作者姓名： | 祝剑虹 朴英 周建兴 岂兴明 |
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| 作者单位： | 清华大学航天航空学院,北京,100084 |
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| 摘 要： | 设计了某单级跨声压气机周向槽处理机匣,利用全三维定常数值模拟方法研究了三种典型转速下的机匣扩稳机理;对比分析得出处理机匣扩稳性能与压气机工况、处理槽位置的关系:转速越高,处理槽扩稳效果越好,而且位于叶尖弦长中部的处理槽更有效.当转速降低时,扩稳效果减弱,靠近尾沿的处理槽更为明显.研究表明,该压气机在降转速过程中存在一个扩稳机理的转变:在高转速下扩稳以抑制间隙涡破裂为主,而低转速下则以抑制叶尖吸力面附面层分离为主.
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| 关 键 词： | 航空、航天推进系统 压气机 机匣处理 数值模拟 失速 |
| 文章编号： | 1000-8055(2008)04-0687-06 |
| 收稿时间： | 2007/3/29 0:00:00 |
| 修稿时间： | 2007年3月29日 |
Investigation of off design performance of a transonic compressor with circumferential grooves |
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| ZHU Jian-hong,PIAO Ying,ZHOU Jian-xing and QI Xing-ming.Investigation of off design performance of a transonic compressor with circumferential grooves[J].Journal of Aerospace Power,2008,23(4):687-692. |
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| Authors: | ZHU Jian-hong PIAO Ying ZHOU Jian-xing and QI Xing-ming |
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| Affiliation: | School of Aerospace, Tsinghua University, Beijing 100084, China;School of Aerospace, Tsinghua University, Beijing 100084, China;School of Aerospace, Tsinghua University, Beijing 100084, China;School of Aerospace, Tsinghua University, Beijing 100084, China |
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| Abstract: | A case with circumferential grooves was designed for a transonic compressor.And 3-D numerical simulations were carried out for stall mechanism in three operative modes at representative speed.Comparison study between compressors with and without casing treatment shows that: with the rotation speed rising,stall margin gain increases dramatically under the help of casing treatments;and the case with middle grooves has better compromise between stall margin and efficiency.Under low speed,the gain reduces,and the last grooves on the chord of blade tip have greater influence on the stall boundary.Further investigation shows that there is a translation in the mechanism of compressor stall when its speed reduces: the stall margin gain mainly results from suppression of tip leakage vortex by casing treatments under high rotation speed;whereas under low rotation speed,the gain benefits more from reduction of the boundary layer separation on suction side of blade tip. |
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| Keywords: | aerospace propulsion system compressor case treatment numerical simulation stall |
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