吸附式压气机叶栅气动性能计算模拟研究

周正贵; 王传宝

吸附式压气机叶栅气动性能计算模拟研究

周正贵¹,
王传宝²

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
中国航空工业第一集团公司, 沈阳发动机设计研究所, 沈阳 110015

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- 被引次数: 0
出版历程
- 收稿日期: 2007-08-13
- 修回日期: 2007-10-09
- 刊出日期: 2007-12-28

Investigation of aspirated compressor cascade flow fields using numerical simulation method

ZHOU Zheng-gui¹,
WANG Chuan-bao²

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Shenyang Aeroengine Research Institute, China Aviation Industry CorporationⅠ, Shenyang 110015, China

摘要

摘要: 为考察附面层吸附技术在压气机静子势流区叶型上的应用,采用流场数值计算方法对吸气叶栅流场进行模拟.结果表明:(1)对于高亚声速压气机叶栅,采用吸力面附面层吸除可提高叶栅的扩压度,但不一定能减小流动损失.(2)对于中亚声压气机叶栅,采用吸力面附面层吸除不仅可提高叶栅的扩压度而且能减小流动损失.(3)如果叶片吸力面靠后缘处有流动分离,吸气位置在分离区的上游较远处可抑制分离,若在分离区附近可能不利于抑制流动分离.
- 航空、航天推进系统 /
- 压气机 /
- 叶栅 /
- 吸附式 /
- 附面层 /
- 亚声速
Abstract: To explore the application of boundary layer aspiration technology in compressor stator blade profiles of potential regions,the cascade flow fields were simulated numerically.The results indicate that:(1) for high subsonic inlet flow,the boundary layer in blade suction surface being aspirated can increase the cascade pressure rate and flow turning angle,but not always reduce flow loss;(2) for middle subsonic inlet flow,the boundary layer in blade suction surface being aspirated can increase the cascade pressure rate,flow turning angle and reduce flow loss;(3) if there is flow separation region in rear part of blade suction surface,the aspiration position located upstream far from the region can eliminate flow separation;but the separation region can not be eliminated if the aspiration position is near or within the region.
- aerospace propulsion system /
- compressor /
- cascade /
- aspiration /
- boundary layer /
- subsonic

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参考文献(8)

[1]	方昌德.流动控制技术在航空涡轮推进系统上的应用[J].燃气涡轮试验与研究,2003,16(2):1-6.FANG Changde.Application of flow control technology in aero-engine propulsion system[J].Gas Turbine Experiment and Research,2003,16(2):1-6.
[2]	Merchant A,Kerrebrock J L.Experimental investigation of a high pressure ratio aspirated fan stage[J].Journal of Turbomachinery,2005,127:43-50.
[3]	Hubrich K,Bolcs P O.Boundary layer suction via a slot in a transonic compressor numerical parameter study and first experiments[R].ASME GT2004-53758,2004.
[4]	Kirtley P G,Graziosi P,Wood P,et al.Design and test of an ultralow solidity flow-controlled compressor stator[J].Journal of Turbomachinery,2005,27:689-698.
[5]	Merchant A.Aerodynamic design and performance of aspirated airfoils[J].Journal of Turbomachinery,2003,125:141-148.
[6]	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):562-566.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):562-566.
[7]	周海,李秋实,陆亚钧.跨声风扇转子叶片抽吸气数值实验探索[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.
[8]	周正贵.高亚声速压气机叶片优化设计[J].推进技术,2004,25(1):58-61.ZHOU Zhenggui.Optimization of high subsonic axial compressor blades[J].Journal of Propulsion and Techno-logy,2004,25(1):58-61.