吸力面附面层抽吸在三维高负荷扩压叶栅中的作用机制
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摘要
对某矩形高负荷扩压叶栅在不同弦向位置开设全叶高抽吸槽的5组方案进行了数值研究,分析了抽吸槽弦向位置等参数对抽吸量分布规律的影响;通过叶栅实验探究了局部展向抽吸方案的效果.数值仿真的计算域包含吸附叶片内部的真空腔,边界条件按照实验条件设置.研究发现:全叶高抽吸方案的抽吸量沿展向大致呈C型分布;叶高中部和端部的主要抽吸效果都体现在叶高中部流场,端部的抽吸量对叶栅角区的回流有一定的抑制效果.抽吸量沿展向的分布规律受叶栅流道和叶片内腔流场的共同作用,因此应根据三维高负荷扩压叶栅流场的具体特性对吸力面抽吸槽/孔进行细化设计.
The highly loaded diffuser compressor cascade with a full-span suction slot was numerically simulated under five different chordwise suction positions in the first step.The influences of aerodynamic parameters such as suction position on the suction flow distribution were studied in detail.Then experiments on the effects of partly-span suction flow on the performance of a three-dimensional cascade were carried out.The simulation region includs the inner cavity of the suctior blade,and the boundary conditions in simulations are setaccording to the experimental conditions.The suction flow is C-type distributed along the spanwise direction in full-span suction schemes.Both of the partly-span suction schemes mainly improve the flow field around the midspan,while the suction flow around the blade roots also suppress the back flow in the corner region.Both the three-dimensional flow field of the cascade passage and inner cavity of the aspirate blade influenced the spanwise distribution of the suction flow.Therefore it is necessary to design tailored suction slots/orifices according to the characteristics of the three-dimensional high loading diffuser compressor cascades.
The highly loaded diffuser compressor cascade with a full-span suction slot was numerically simulated under five different chordwise suction positions in the first step.The influences of aerodynamic parameters such as suction position on the suction flow distribution were studied in detail.Then experiments on the effects of partly-span suction flow on the performance of a three-dimensional cascade were carried out.The simulation region includs the inner cavity of the suctior blade,and the boundary conditions in simulations are setaccording to the experimental conditions.The suction flow is C-type distributed along the spanwise direction in full-span suction schemes.Both of the partly-span suction schemes mainly improve the flow field around the midspan,while the suction flow around the blade roots also suppress the back flow in the corner region.Both the three-dimensional flow field of the cascade passage and inner cavity of the aspirate blade influenced the spanwise distribution of the suction flow.Therefore it is necessary to design tailored suction slots/orifices according to the characteristics of the three-dimensional high loading diffuser compressor cascades.
引文
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[15]GUO Shuang,LU Huawei,CHEN Fu,et al.Vortex control and aerodynamic performance improvement of a highly loaded compressor cascade via inlet boundary layer suction[J].Experiments in Fluids,2013,54(7):1-11.
[16]ZHANG Hualiang,WANG Songtao,WANG Zhongqi.Variation of vortex structure in a compressor cascade at different incidences[J].Journal of Propulsion and Power,2007,23(1):221-226.
[17]Sachdeva A,Leboeuf F.Topological studies of three-dimensional flows in a high pressure compressor stator blade row without and with boundary layer aspiration[J].Chinese Journal of Aeronautics,2011,24(5):541-549.
[18]KANG Shun.Investigation of the three dimensional flow within a compressor cascade with and without tip clearance[D].Brussel:University of Brussel,1993.
[2]Kerrebrock J L,Reijnen D P,Ziminsky W S,et al.Aspirated compressors[R]ASME Paper 1997-GT-525,1997.
[3]Merchant A A.Design and analysis of supercritical airfoils with boundary layer suction[D].Cambridge,Massachusetts:Massachusetts Institute of Technology,1996.
[4]Merchant A A,Drela M,Kerrebrock J M.Aerodynamic design and analysis of a high pressure ratio aspirated compressor stage[R].ASME Paper 2000-GT-619,2000.
[5]Reijnen D P.Experimental study of boundary layer suction in a transonic compressor[D].Cambridge,Massachusetts:Massachusetts Institute of Technology,1997.
[6]牛玉川,朱俊强,聂超群,等.吸附式亚声速压气机叶栅气动性能实验及分析[J].航空动力学报,2008,23(3):483-489.NIU Yuchuan,ZHU Junqiang,NIE Chaoqun,et al.Experimental investigations of aerodynamics performance of aspirate subsonic compressor cascade[J].Journal of Aerospace Power,2008,23(3):483-489.(in Chinese)
[7]南向谊,刘波,靳军,等.超声速压气机转子叶片吸力面抽气抑制附面层分离的机理[J].航空动力学报,2007,22(7):1093-1099.NAN Xiangyi,LIU Bo,JIN Jun,et al.Study of suppression boundary layer separation on the suction surface of supersonic compressor rotor[J].Journal of Aerospace Power,2007,22(7):1093-1099.(in Chinese)
[8]SONG Yanping,CHEN Fu,YANG Jun,et al.A numerical investigation of boundary layer suction in compound lean compressor cascades[J].Journal of Turbomachinery,2006,128(2):357-366.
[9]GUO Shuang,CHEN Shaowen,SONG Yanping,et al.Effects of boundary layer suction on aerodynamic performance in a high-load compressor cascade[J].Chinese Journal of Aeronautics,2010,23(2):179-186.
[10]Gbadebo S A,Cumpsty N A,Hynes T P.Control of threedimensional separations in axial compressors by tailored boundary layer suction[J].Journal of Turbomachinery,2008,130(1):1-8.
[11]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.(in Chinese)
[12]WANG Yangang,GUO Rui,ZHAO Longbo,et al.Numerical investigation on the effects of re-organized shock waves on the flow separation for a highly-loaded transonic compressor cascade[J].Journal of Thermal Science,2012,21(1):13-20.
[13]Gmelin C,Thiele F,Liesner K,et al.Investigations of secondary flow suction in a high speed compressor cascade[R].Vancouver,Canada:ASME Turbo Expo 2011,Power for Land,Sea and Air Report,2011.
[14]韩万今,吕红卫,卢文才,等.进口附面层厚度对大转角弯叶片损失的影响[J].工程热物理学报,1994,15(3):391-394.HAN Wanjin,LHongwei,LU Wencai,et al.The influence of thicknesses of inlet boundary layers on losses in cascades of high-turning curved blades[J].Journal of Engineering Thermophysics,1994,15(3):391-394.(in Chinese)
[15]GUO Shuang,LU Huawei,CHEN Fu,et al.Vortex control and aerodynamic performance improvement of a highly loaded compressor cascade via inlet boundary layer suction[J].Experiments in Fluids,2013,54(7):1-11.
[16]ZHANG Hualiang,WANG Songtao,WANG Zhongqi.Variation of vortex structure in a compressor cascade at different incidences[J].Journal of Propulsion and Power,2007,23(1):221-226.
[17]Sachdeva A,Leboeuf F.Topological studies of three-dimensional flows in a high pressure compressor stator blade row without and with boundary layer aspiration[J].Chinese Journal of Aeronautics,2011,24(5):541-549.
[18]KANG Shun.Investigation of the three dimensional flow within a compressor cascade with and without tip clearance[D].Brussel:University of Brussel,1993.