叶顶喷气对跨声转子近失速点流动的影响

贾惟; 刘火星

叶顶喷气对跨声转子近失速点流动的影响

贾惟,
刘火星

北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室, 北京 100191

基金项目: 重点实验室基金(9140C4103091003)

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出版历程
- 收稿日期: 2010-01-13
- 修回日期: 2011-03-10
- 刊出日期: 2011-12-28

Effect of tip injection on the flow of near-stall condition in a transonic rotor

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 利用数值模拟的方法研究了叶顶喷气对跨声转子性能及近失速点流动的影响.研究表明:在+65?的喷气角度下,喷气能保持效率不降低的同时使转子喘振裕度的绝对值提高4.48%.此外喷气还能改善转子叶片吸力面的流动,减弱叶尖泄漏涡的强度,同时使泄漏涡的轨迹更贴近叶片吸力面,这也是喘振裕度大幅提高的物理原因.
- 跨声转子 /
- 叶顶喷气 /
- 近失速 /
- 泄漏涡 /
- 喘振裕度
Abstract: Effect of tip injection on the performance and the flow of near-stall condition of transonic axial compressor rotor was investigated numerically.The result shows that the stall margin of this transonic rotor gains an absolute improvement of 4.48% by tip injection while the efficiency remains unchanged at the injection angle of +65?.Furthermore,the separation on the suction side of the rotor and intensity of the tip leakage vortex are both weakened.Besides,the trajectory of the tip leakage is more inclined to the suction side of the blade which mainly leads to the increase of stall margin.
- transonic rotor /
- tip injection /
- near stall /
- leakage vortex /
- stall margin

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参考文献(18)

[1]	Pouagare M,Lazarus K,Weinhold W P.Tip leakage reduction through tip injection in turbomachines[R].AIAA-1986-1746,1986.
[2]	Leinhos D C,Scheidler S,Fottner L.Active stabilization of a low pressure compressor in a turbofan engine with constant air injection[R].AIAA-2001-3312,2001.
[3]	SHENG Chunhua,Remotigue M.Numerical simulation of rotor 35 with and without tip injection using an arbitrary Mach number flow solver[R].AIAA-2004-372,2004.
[4]	Suder K,Hathaway M D,Thorp S,A,et al.Compressor stability enhancement using discrete tip injection[J].Journal of Turbomachinery,2001,123(1):14-23.
[5]	Weigl H J,Paduano J D,Frechette L G,et al.Active sta-bilization of rotating stall and surge in a transonic single stage axial compressor[J].Journal of Turbomachinery,1998,120(4):625-636.
[6]	Koch C C,Smith L H.Experimental evaluation of outer casing blowing or bleeding of single stage axial flow compressor Part Ⅳ:performance of bleed insert configuration No.3[R].NASA-CR-54590,2008.
[7]	Lee N K W,Greitzer E M.Effects of endwall suction and blowing on compressor stability enhancement[J].Journal of Turbomachinery,1990,112(1):133-144.
[8]	Khaleghi H,Teixeria J A,Tousi A M,et al.Parametric study of injection angle effects on stability of transonic axial compressors[J].Journal of Propulsion and Power,2008,24(5):1100-1107.
[9]	Beheshti B H,Ghorbanian K,Farhanieh B,et al.A new design for tip injection in transonic axial compressors[R].ASME Paper GT 2006-90007,2006.
[10]	童志庭,聂超群.微喷气提高轴流压气机稳定性的研究[J].工程热物理学报,2006,27(3):121-123. TONG Zhiting,NIE Chaoqun.Investigation on micro tip injection improving the stability of an axial compressor[J].Journal of Engineering Thermophysics,2006,27(3):411-413.(in Chinese)
[11]	徐纲,聂超群,黄伟光,等.低速轴流压气机顶部微量喷气控制失速机理的数值模拟[J].工程热物理学报,2004,25(1):37-40. XU Gang,NIE Chaoqun,HUANG Weiguang, et al.Numerical simulation of micro injection in a low-speed axial compressor[J].Journal of Engineering Thermophysics,2004,25(1):37-40.(in Chinese)
[12]	耿少娟,朱俊强,戴冀,等.叶尖喷气影响低离心压气机特性的数值分析[J]. 工程热物理学报,2006,27(3):411-413. GENG Shaojuan,ZHU Junqiang,DAI Ji,et al.Numerical study of the effects of steady tip injection on the performance of low-speed centrifugal compressor[J].Journal of Engineering Thermophysics,2006,27(3):411-413.(in Chinese)
[13]	耿少娟,张宏武,朱俊强,等.喷气对低速轴流压气机转子叶顶区域流动的影响[J].工程热物理学报,2007,28(3):395-398. GENG Shaojuan,ZHANG Hongwu,ZHU Junqiang,et al. Effects of micro air injection on rotor tip flow in a low-speed isolated axial compressor rotor[J].Journal of Engineering Thermophysics,2007,28(3):395-398.(in Chinese)
[14]	马文生,顾春伟.轴流压气机跨声级转子叶顶喷气的流动特性[J].推进技术,2009,30(3):302-307. MA Wensheng,GU Chunwei.Tip injection in transonic axial compressor rotor[J].Journal of Propulsion Technology,2009,30(3):302-307.(in Chinese)
[15]	Khalrghi H,Boroomand M,Teixeria J A,et al.A nume-rical study of the effects of injection velocity on stabi-lity improvement in high-speed compressors[J].Proceedings of the Institution of Mechanical Engineers Part A:Journal of Power and Energy,2008,222(2):189-198.
[16]	Leihman B A,Cumpsty N A,Denton J D.Effects of bleed rate and endwall location on the aerodynamic behavior of a circular hole bleed off-take[R].ASME Paper GT-2004-54719,2004.
[17]	Moove R D,Moore,Lonnie R.Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26,respectively,and with design pressure ratio of 2.05[R].NASA Technical Paper 1659,1980.
[18]	Hathaway M D.Self-recirculating casing treatment concept for enhanced compressor performance[R].ASME Paper GT 2002-30368,2002.