变冲角条件下等离子体对扩压叶栅性能的影响

刘华坪; 陈焕龙; 袁继来; 陈浮

变冲角条件下等离子体对扩压叶栅性能的影响

哈尔滨工业大学能源科学与工程学院,哈尔滨 150001

基金项目: 国家自然科学基金(50976026)

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- 文章访问数: 1917
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- 被引次数: 0
出版历程
- 收稿日期: 2010-07-16
- 修回日期: 2010-12-03
- 刊出日期: 2011-08-28

Influence on the performance of compressor cascade with alterative incidence angles by the plasma

School of Energy Science and Engineering, Harbin Institute of Technology,Harbin 150001,China

摘要

摘要: 进行了不同冲角、不同电压以及不同电极安装位置下等离子体对大折转角扩压叶栅性能的影响研究.结果表明,当冲角增大时,分离流动加剧是叶栅损失增加的主要原因,而端壁附面层内的摩擦损失则由于流向速度的减小反而减少;等离子体在三种工况下(i=0°,5°,-5°)均可有效控制栅内流动分离、减小叶栅损失、增加叶片负荷,电压越大、电极安装位置越接近分离起始位置,其控制效果越明显;随着冲角的增加,等离子体减小能量损失的效果减弱;虽然电极沿整个叶高方向布置,但等离子体仅对约10%叶高以上的损失影响较为明显,同一电压下该范围内各叶高处的损失减小量也基本相同.
- 等离子体 /
- 扩压叶栅 /
- 附面层 /
- 流动控制 /
- 叶栅损失
Abstract: The plasma effect on the performance of high-turning compressor cascade was investigated at different incidence angles,voltages and electrodes locations.The results show that,with the increase of the incidence angle,the aggravation of the flow separation is a primary reason for the increase of the cascade losses,while the boundary layer losses near the end-wall decrease due to the reduction of the flow velocity.At all the incidence angles (i=0°,5°,-5°),the plasma actuator could weaken the separation,reduce the cascade losses and increase the blade loading effectively.The bigger the voltage and the closer the electrodes to the separation line,the more obvious the plasma effect becomes.And the bigger incidence angle leads to weaker plasma effect.Although the electrodes are installed along the whole blade height,the plasma merely reduces the losses in the region above 10% blade height,and the loss reduction is almost the same in this zone.
- plasma /
- compressor cascade /
- boundary layer /
- flow control /
- cascade lose

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参考文献(20)

[1]	Post M L,Corke T C.Separation control using plasma actuators dynamic stall control on an oscillating airfoil.AIAA 2004-2517,2004.
[2]	Patel M P,Ng T T,Vasudevan S,et al.Plasma actuators for hingeless aerodynamic control of an unmanned air vehicle.AIAA 2006-3495,2006.
[3]	Gaitonde D V,Visbal M R,Roy S.Control of flow past a wing section with plasma-based body forces.AIAA 2005-5302,2005.
[4]	刘万刚,李一滨.应用等离子体实现主动流动控制的实验研究[J].弹箭与制导学报,2006,26(2):110-111. LIU Wangang,LI Yibin.Experimental study of using plasma to induce flow in the quiet air[J].Journal of Projectiles,Rockets,Missiles and Guidance,2006,26(2):110-111.(in Chinese)
[5]	张攀峰,王晋军,施威毅,等.等离子体激励低速分离流动控制实验研究[J].实验流体力学,2007,21(2):35-39. ZHANG Panfeng,WANG Jinjun,SHI Weiyi,et al.Experimental study on the separation control by plasma actuator in subsonic flow[J].Journal of Experiments in Fluid Mechanics,2007,21(2):35-39.(in Chinese)
[6]	Huang J,Corke T C,Thomas F O.Plasma actuators for separation control of low-pressure turbine blades[J].AIAA Journal,2006,44(1):51-57.
[7]	Huang J,Corke T C,Thomas F O.Unsteady plasma actuators for separation control of low pressure turbine blades[J].AIAA Journal,2006,44(7):1477-1487.
[8]	Van Ness D K Ⅱ,Corke T C,Morris S C.Turbine tip clearance flow control using plasma actuators.AIAA 2006-0021,2006.
[9]	Wang C C,Roy S.Active cooling of turbine blades using horse-shoe plasma actuator.AIAA 2009-0679,2009.
[10]	Vo H D.Control of rotating stall in axial compressors using plasma actuators.AIAA 2007-3845,2007.
[11]	Vo H D,Cameron J D,Morris S C.Control of short length-scale rotating stall inception on a high-speed axial compressor with plasma actuation.ASME Paper GT-2008-50967,2008.
[12]	Lemire S,Vo H D,Benner M W.Performance improvement of axial compressors and fans with plasma actuation[J].International Journal of Rotating Machinery,2009,2009:Article ID 247613(13 pages).
[13]	Lemire S,Vo H D.Reduction of fan and compressor wake defect using plasma actuation for tonal noise reduction.ASME Paper GT-2008-50821,2008.
[14]	吴云,李应红,朱俊强,等.等离子体气动激励扩大低速轴流式压气机稳定性的实验[J].航空动力学报,2007,22(12):2025-2030. WU Yun,LI Yinghong,ZHU Junqiang,et al.Experimental investigation of using plasma aerodynamic actuation to extend low-speed axial compressor's stability[J].Journal of Aerospace Power,2007,22(12):2025-2030.(in Chinese)
[15]	吴云,李应红,朱俊强,等.等离子体气动激励抑制压气机叶栅角区流动分离的仿真与实验[J].航空动力学报,2009,24(4):830-835. WU Yun,LI Yinghong,ZHU Junqiang,et al.Computational and experimental investigation of plasma aerodynamic actuation based corner flow separation control in a compressor cascade[J].Journal of Aerospace Power,2009,24(4):830-835.(in Chinese)
[16]	Orlov D M,Corke T C.Numerical simulation of aerodynamic plasma actuator effects.AIAA 2005-1083,2005.
[17]	刘华坪,颜培刚,陈浮.利用等离子控制凸包分离流动的数值模拟[J].航空动力学报,2009,24(3):596-601. LIU Huaping,YAN Peigang,CHEN Fu.Numerical simulation of plasma-based separation control over a hump[J].Journal of Aerospace Power,2009,24(3):596-601.(in Chinese)
[18]	Enloe C L,McLaughlin T E,Van Dyken R D,et al.Plasma structure in the aerodynamic plasma actuator.AIAA 2004-0844,2004.
[19]	李钢.等离子体流动控制机理及其应用研究.北京:中国科学院工程热物理研究所,2008. LI Gang.Investigation of dielectric barrier discharge plasma flow control mechanism and its application.Beijing:Institute of Engineering Thermophysics,Chinese Academy of Sciences,2008.(in Chinese)
[20]	冯冬民.孔隙射流对大折转角压气机叶栅分离流动的影响.哈尔滨:哈尔滨工业大学,2009. FENG Dongmin.Investigation in effects of air-injection on flow separation in a high turning compressor cascade.Harbin:Harbin Institute of Technology,2009.(in Chinese)