等离子体气动激励扩大低速轴流式压气机稳定性的实验

吴云; 李应红; 朱俊强; 苏长兵; 梁华; 宋慧敏; 李刚

等离子体气动激励扩大低速轴流式压气机稳定性的实验

1.
空军工程大学工程学院, 西安 710038
2.
中国科学院工程热物理研究所, 北京 100080

基金项目: 国家"863计划"(2005AA753031);教育部"新世纪优秀人才支持计划";空军工程大学工程学院优秀博士学位论文创新基金(BC06001)

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出版历程
- 收稿日期: 2007-06-12
- 修回日期: 2007-09-25
- 刊出日期: 2007-12-28

Experimental investigation of using plasma aerodynamic actuation to extend low-speed axial compressor's stability

1.
The Engineering Institute, Air Force Engineering University, Xi'an 710038, China
2.
Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100080, China

摘要

摘要: 在低速轴流式压气机孤立转子实验台上进行了等离子体气动激励扩大压气机稳定性的实验研究.研制了等离子体气动激励处理机匣,通过比较一定转速下施加等离子体气动激励前后的压升系数和流量系数,研究压气机稳定性的变化.施加等离子体气动激励后,转速为900 r/min和1 080 r/min时,压气机近失速流量系数分别降低5.2%和5.07%.等离子体气动激励电压增大后,扩稳效果更好.在距离转子叶片前缘49.5%弦长处施加等离子体气动激励,扩稳效果更好.
- 航空、航天推进系统 /
- 等离子体气动激励 /
- 压气机 /
- 稳定性 /
- 实验
Abstract: The effect of plasma aerodynamic actuation on low-speed axial compressor performance and stability range was investigated experimentally.Aplasma aerodynamic actuation treated casing(PAATC^TM) was designed.Asingle low-speed axial compressor rotor with no inlet guide vanes was tested.Pressure rise coefficient and flow coefficient for the compressor test rig were calculated with/without plasma actuation at a constant rotor speed to represent compressor performance and stability range.The experimental results show that,with plasma actuation,the mass flow coefficients near stall is decreased by 5.2% and 5.07% when the rotor speed reaches 900 r/min and 1080 r/min respectively.The influences of different actuation voltages and different actuation locations were investigated experimentally.Compressor's stability became larger along with the rise of actuation voltage.The actuation away from rotor's leading edge for 49.5% axial chord can extend compressor's stability more than the actuation away from the rotor's leading edge for 8.3% axial chord.
- aerospace propulsion system /
- plasma aerodynamic actuation /
- compressor /
- stability /
- experiment

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参考文献(14)

[1]	Lord W K,MacMartin D G,Tillman T G.Flow control opportunities in gas turbine engines[R].AIAA 2000-2234,2000.
[2]	Furukawa M,Inoue M,Saiki K,et al.The role of tip leakage vortex breakdown in compressor rotor aerodyna-mics[J].ASME Journal of Turbomachinery,1999,121(4):469-480.
[3]	Hathaway M D.Self-recirculating casing treatment concept for enhanced compressor performance[R].ASME Paper No.GT-2002-30368,2002.
[4]	Lu X,Chu W,Zhu J,et al.Experimental and numerical investigation of a subsonic compressor with bend skewed slot casing treatment[R].ASME Paper No.GT2006-90026,2006.
[5]	Beheshti B H,Ghorbanian K,Farhanieh B,et al.A new design for tip injection in transonic axial compressors[R].ASME Paper No.GT-2006-90007,2006.
[6]	Roth J R.Aerodynamic flow acceleration using paraelectric and peristaltic electrohydrodynamic effects of one atmosphere uniform glow discharge plasma[J].Physics of Plasmas,2003,10(5):2117-2126.
[7]	Corke T C,Post M L.Overview of plasma flow control:concepts,optimization,and applications[R].AIAA 2005-0563,2005.
[8]	Post M L,Corke T C.Separation control on high angle of attack airfoil using plasma actuators[R].AIAA 2003-1024,2003.
[9]	WU Yun,LI Yinghong,ZHANG Pu,et al.Experimental investigation of plasma assisted flow control on NACA 0015 airfoil[R]//XVI International Conference on Gas Discharges and Their Applications.Xi'an:2006,2:833-836.
[10]	Roupassov D,Zavialov I,Starikovskii A,et al.Boundary layer separation plasma control using low-temperature non-equilibrium plasma of gas discharge[R].AIAA 2006-0373,2006.
[11]	Huang J,Corke T,Thomas F.Plasma actuators for separation control of low pressure turbine blades[R].AIAA 2003-1027,2003.
[12]	LI Yinghong,SONG Huimin,WU Yun,et al.Experiments of plasma actuation based compressor cascade flow separation suppression[R].The First International Symposium on Jet Propulsion and Power Engineering.Kunming:2006-ISJPE-5008,2006.
[13]	Morris S,Corke T C,Van Ness D,et al.Tip clearance control using plasma actuators[R].AIAA 2005-0782.
[14]	Deng X,Zhang H,Chen J,et al.Unsteady tip clearance flow in low-speed axial compressor rotor with upstream and downstream stators[R].ASME GT2005-68571,2005.