超声速压气机转子叶片吸力面抽气抑制附面层分离的机理

南向谊; 刘波; 靳军; 陈云永; 侯为民

超声速压气机转子叶片吸力面抽气抑制附面层分离的机理

西北工业大学动力与能源学院, 西安 710072

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出版历程
- 收稿日期: 2006-06-12
- 修回日期: 2006-11-18
- 刊出日期: 2007-07-28

Study of suppression boundary layer separation on the suction surface of supersonic compressor rotor

School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 针对压气机叶片在高负荷及非设计工况下经常出现的附面层分离状况, 采用数值方法研究了叶片吸力面不同位置、不同吸气量时附面层抽吸对压气机转子气动性能的影响.数值结果表明:抽吸位置对抽吸效果有重要的影响, 通过在分离区下游一定位置处抽吸, 能够很好的抑制附面层分离, 改善气流在大分离点处的剧烈变化, 减少流动损失, 使得级效率和压比均有显著的提高;而在分离区上游或者分离区下游的较远处开缝抽吸, 则效果不理想.吸气量对抽吸效果也有一定影响, 存在一个最佳吸气量, 吸气量过大或者过小都会对结果产生不利影响.
- 航空、航天推进系统 /
- 压气机转子 /
- 附面层抽吸 /
- 吸气位置 /
- 吸气量
Abstract: To provide a further prospective of the boundary layer separation of compressor rotor under high load and off-design working conditions,numerical method was used to study the effects of boundary layer suction of compressor rotor at different suction positions and suction flow rates on the aerodynamic performance of rotor.The results show that the suction position has great effect on the suction result.The boundary layer separation on the suction surface can be suppressed effectively through suction in proper downstream separation section.And,the dramatic change of gas flow at the separation point could be improved with lower flow loss,while the stage efficiency and pressure ratio can be improved remarkably.The effect is unsatisfactory in the event of slotted suction far away from the upstream or downstream of separation point.As suction flow rate also has a certain influence upon the suction effect,either bigger or lower suction flow rate has adverse effect on the result.
- aerospace propulsion system /
- compressor rotor /
- boundary layer suction /
- suction position /
- suction flow rate

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参考文献(9)

[1]	Schuler B J,Kerrebrock J L,Merchant A A,et al.Design analysis,fabrication and test of an aspirated fan stage[R].ASME 2000-GT-618.
[2]	Bolln G W Jr,Field K J,Burnes R.F414 Engine today and growth potential for 21st century fighter mission challenges[R].ISABE 99-7113.
[3]	Kerrebrock J L,Reijnen D P,Ziminsky W S,et al.Aspirated Compressors[R].ASME 97-GT-525.
[4]	Kerrebrock J L,Drela M,Merchant A,et al.A Family of Design for Aspirated Compressors[R].ASME 98-GT-198.
[5]	Merchant A A.Aerodynamic design and performance of aspirated airfoil[R].ASME Paper 2002-GT-30369.
[6]	Schuler B J,Kerrebrock J L,Merchant A A.Experimental investigation of an aspirated fan stage[R].ASME Paper 2002-GT-3370.
[7]	Hubrich K,Bolcs A,Ott P.Boundary layer suction via a slot in a transonic compressor-numerical parameter study and first experiments[R].ASME Paper,GT2004-53758.
[8]	周海,李秋实,陆亚钧.跨声风扇转子叶片抽吸气数值试验探索[J].航空动力学报,2004,19(3):408-412.ZHOU Hai,LI Qiushi,LU Yajun.Prospects of numerical analysis of an aspirated transonic fan rotor[J].Journal of Aerospace Power,2004,19(3):408-412.
[9]	宋彦萍,陈浮,赵桂杰,等.附面层吸除对大转角压气机叶栅气动性能影响的数值研究[J].航空动力学报,2005,20(4):561-566.SONG Yanping,CHEN Fu,ZHAO Guijie,et al.Numerical investigation of boundary layer suction in compressor cascade with large turning angles[J].Journal of Aerospace Power,2005,20(4):561-566.