自适应处理机匣在多级轴流压气机中的应用
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摘要
设计了一种环腔导流片式自适应处理机匣,采用定常数值方法研究了不同导流片形式对亚声多级轴流压气机流场的影响。结果表明:导流片与转子弦向垂直时的处理机匣减弱了叶尖前缘溢流强度,抑制了间隙泄漏流发展,提高了转子叶尖通道的流通能力,使得压气机在0.8倍设计转速以上特性基本保持不变的同时,大幅度提高了低转速的稳定裕度,其中0.7倍设计转速时近失速点总压比增大10.2%,近失速流量拓宽8.5%,体现出较好的自适应扩稳能力。
An adaptive treatment casing with annular cavity guide vane was designed.The influence of different guide vanes on the flow field of subsonic multistage axial compressor was studied by means of steady numerical method.Results showed that when the guide vane perpendicular to the rotor chord wise weakened the leading edge overflow intensity of the blade tip,the treatment casing restrained the development of clearance leakage flow,improved the flow capacity of the rotor blade tip passage,and made the compressor basically unchanged while the speed characteristic was above 0.8 design speed,the stability margin of low speed was greatly improved,in which the total pressure ratio at the near-stall point increased by 10.2% at 0.7 design speed and the near-stall flow rate expanded by 8.5%,showing the strong adaptive stability-expanding ability.
An adaptive treatment casing with annular cavity guide vane was designed.The influence of different guide vanes on the flow field of subsonic multistage axial compressor was studied by means of steady numerical method.Results showed that when the guide vane perpendicular to the rotor chord wise weakened the leading edge overflow intensity of the blade tip,the treatment casing restrained the development of clearance leakage flow,improved the flow capacity of the rotor blade tip passage,and made the compressor basically unchanged while the speed characteristic was above 0.8 design speed,the stability margin of low speed was greatly improved,in which the total pressure ratio at the near-stall point increased by 10.2% at 0.7 design speed and the near-stall flow rate expanded by 8.5%,showing the strong adaptive stability-expanding ability.
引文
[1]MOORE F K,GREITZER E M.A theory of post-stall transients in axial compressors:PartⅠdevelopment of the equations[J].Journal of Engineering for Gas Turbines and Power,1986,108(1):68-76.
[2]GREITZER E M,MOORE F K.A theory of post-stall transients in axial compressors:PartⅡapplication[J].Journal of Engineering for Gas Turbines and Power,1986,108(2):231-239.
[3]VO H D.Role of tip clearance flow on axial compressor stability[D].Cambridge,Massachusetts:Massachusetts Institute of Technology,2001.
[4]吴艳辉,朱俊强,刘志伟.多级轴流压气机处理机匣级的探讨[J].航空动力学报,2002,17(5):542-548.WU Yanhui,ZHU Junqiang,LIU Zhiwei.Research on the axial position of treated casing in multistage axial-flow compressors[J].Journal of Aerospace Power,2002,17(5):542-548.(in Chinese)
[5]TONG Z T,LIN F.The self-induced unsteadiness of tip leakage vortex and its effect on compressor stall inception[R].ASME Paper GT2007-27010,2007.
[6]DANNER F C T,KAU H P,MULLER M M.Experimental and numerical analysis of axial skewed slot casing treatments for a transonic compressor stage[R].ASME Paper GT2009-59647,2009.
[7]HAH C.Role of tip clearance flows on flow instability in axial flow compressors[R].International Society for Air Breathing Engines,ISABE-2001-1223,2001.
[8]张皓光,王云鹏,吴俊,等.组合型处理机匣提高轴流压气机稳定性的机理[J].航空动力学报,2015,30(1):228-236.ZHANG Haoguang,WANG Yunpeng,WU Jun,et al.Mechanism of improvement on axial-flow compressor stability with assembled casing treatment[J].Journal of Aerospace Power,2015,30(1):228-236.(in Chinese)
[9]WILKE I,KAU H P.A numerical investigation of the flow mechanisms in a HPC front stage with axial slots[R].ASME Paper GT2003-38481,2003.
[10]MULLER M W.Interaction of rotor and casing treatment flow in an axial single-stage transonic compressor with circumferential grooves[R].ASME Paper GT-2008-50135,2008.
[11]MULLER M W.Effect of circumferential grooves on the aerodynamic performance of an axial single-stage transonic compressor[R].ASME Paper GT2007-27365,2007.
[12]VOGES M.Investigation of blade tip interaction with casing treatment in a transonic compressor:PartⅠparticle image velocimety[R].ASME Paper GT2008-50210,2008.
[13]VOGES M.Investigation of blade tip interaction with casing treatment in a transonic compressor:PartⅡnumerical results[R].ASME Paper GT2008-50212,2008.
[14]EMMRICH R.Time resolved investigations of an axial compressor with casing treatment:Part 1experiment[R].ASME Paper GT2007-27581,2007.
[15]EMMRICH R.Time resolved investigations of an axial compressor with casing treatment:Part 2simulation[R].ASME Paper GT2007-27582,2007.
[16]HALL E J,CROOK A J.Aerodynamic analysis of compressor casing treatment with a 3D Navier-Stokes solver[R].AIAA 94-2796,1994.
[17]HALL E J,DELANEY R A.Performance prediction of end-wall treat-fan rotors with inlet distortion[R].AIAA96-0244,1996.
[18]HILA A A,OURLIDAKIS A T.Computational analysis of passive stall delay through vaned recess treatment[R].ASME Paper 2001-GT-0342,2001.
[19]杜辉,朱俊强,楚武利.凹槽叶片式处理机匣的结构尺寸优化研究[J].推进技术,1998,19(1):71-75.DU Hui,ZHU Junqiang,CHU Wuli.Optimization ofstructural parameters of recess vaned casing treatment[J].Journal of Propulsion Technology,1998,19(1):71-75.(in Chinese)
[20]ENGEL K,ZSCHERP C,WOLFRUM N,et al.CFD simulations of the TP400IPC with enhanced casing treatment in off-design operating conditions[R].ASME Paper GT2009-60324,2009.
[21]KROECKEL T,HILLER S J,ESCHKE P J.Application of a multistage casing treatment in a high speed axial compressor test rig[R].ASME Paper GT2011-46315,2011.
[22]楚武利,刘志伟,朱俊强.折线斜缝式处理机匣的实验研究及机理分析[J].航空动力学报,1999,14(3):270-274.CHU Wuli,LIU Zhiwei,ZHU Junqiang.Experimental research and analysis of sloped slotted casing treatment[J].Journal of Aerospace Power,1999,14(3):270-274.(in Chinese)
[2]GREITZER E M,MOORE F K.A theory of post-stall transients in axial compressors:PartⅡapplication[J].Journal of Engineering for Gas Turbines and Power,1986,108(2):231-239.
[3]VO H D.Role of tip clearance flow on axial compressor stability[D].Cambridge,Massachusetts:Massachusetts Institute of Technology,2001.
[4]吴艳辉,朱俊强,刘志伟.多级轴流压气机处理机匣级的探讨[J].航空动力学报,2002,17(5):542-548.WU Yanhui,ZHU Junqiang,LIU Zhiwei.Research on the axial position of treated casing in multistage axial-flow compressors[J].Journal of Aerospace Power,2002,17(5):542-548.(in Chinese)
[5]TONG Z T,LIN F.The self-induced unsteadiness of tip leakage vortex and its effect on compressor stall inception[R].ASME Paper GT2007-27010,2007.
[6]DANNER F C T,KAU H P,MULLER M M.Experimental and numerical analysis of axial skewed slot casing treatments for a transonic compressor stage[R].ASME Paper GT2009-59647,2009.
[7]HAH C.Role of tip clearance flows on flow instability in axial flow compressors[R].International Society for Air Breathing Engines,ISABE-2001-1223,2001.
[8]张皓光,王云鹏,吴俊,等.组合型处理机匣提高轴流压气机稳定性的机理[J].航空动力学报,2015,30(1):228-236.ZHANG Haoguang,WANG Yunpeng,WU Jun,et al.Mechanism of improvement on axial-flow compressor stability with assembled casing treatment[J].Journal of Aerospace Power,2015,30(1):228-236.(in Chinese)
[9]WILKE I,KAU H P.A numerical investigation of the flow mechanisms in a HPC front stage with axial slots[R].ASME Paper GT2003-38481,2003.
[10]MULLER M W.Interaction of rotor and casing treatment flow in an axial single-stage transonic compressor with circumferential grooves[R].ASME Paper GT-2008-50135,2008.
[11]MULLER M W.Effect of circumferential grooves on the aerodynamic performance of an axial single-stage transonic compressor[R].ASME Paper GT2007-27365,2007.
[12]VOGES M.Investigation of blade tip interaction with casing treatment in a transonic compressor:PartⅠparticle image velocimety[R].ASME Paper GT2008-50210,2008.
[13]VOGES M.Investigation of blade tip interaction with casing treatment in a transonic compressor:PartⅡnumerical results[R].ASME Paper GT2008-50212,2008.
[14]EMMRICH R.Time resolved investigations of an axial compressor with casing treatment:Part 1experiment[R].ASME Paper GT2007-27581,2007.
[15]EMMRICH R.Time resolved investigations of an axial compressor with casing treatment:Part 2simulation[R].ASME Paper GT2007-27582,2007.
[16]HALL E J,CROOK A J.Aerodynamic analysis of compressor casing treatment with a 3D Navier-Stokes solver[R].AIAA 94-2796,1994.
[17]HALL E J,DELANEY R A.Performance prediction of end-wall treat-fan rotors with inlet distortion[R].AIAA96-0244,1996.
[18]HILA A A,OURLIDAKIS A T.Computational analysis of passive stall delay through vaned recess treatment[R].ASME Paper 2001-GT-0342,2001.
[19]杜辉,朱俊强,楚武利.凹槽叶片式处理机匣的结构尺寸优化研究[J].推进技术,1998,19(1):71-75.DU Hui,ZHU Junqiang,CHU Wuli.Optimization ofstructural parameters of recess vaned casing treatment[J].Journal of Propulsion Technology,1998,19(1):71-75.(in Chinese)
[20]ENGEL K,ZSCHERP C,WOLFRUM N,et al.CFD simulations of the TP400IPC with enhanced casing treatment in off-design operating conditions[R].ASME Paper GT2009-60324,2009.
[21]KROECKEL T,HILLER S J,ESCHKE P J.Application of a multistage casing treatment in a high speed axial compressor test rig[R].ASME Paper GT2011-46315,2011.
[22]楚武利,刘志伟,朱俊强.折线斜缝式处理机匣的实验研究及机理分析[J].航空动力学报,1999,14(3):270-274.CHU Wuli,LIU Zhiwei,ZHU Junqiang.Experimental research and analysis of sloped slotted casing treatment[J].Journal of Aerospace Power,1999,14(3):270-274.(in Chinese)