多级轴流压气机彻体力模型——理论方法及简化应用
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摘要
基于时间推进技术及有限体积法,将彻体力模型与基元叶栅法的思想相结合,提出了一个适用于预测大尺度进气畸变对多级轴流压气机气动性能及稳定性影响的三维数值计算模型。在进气条件轴对称的前提下,利用相应的简化模型重点分析了一台四级轴流压气机在均匀进气及叶尖径向总压畸变进气下的内部流场特征。均匀进气下的模型计算结果与相关试验结果相吻合。叶尖径向总压畸变进气下模型的计算结果表明:径向畸变在压气机流道内会发生显著的径向掺混作用,叶尖径向总压畸变对该压气机稳定性有显著恶化影响,随着畸变强度的增加,压气机稳定边界逐步下降。计算结果支持了该模型用于预测径向进气畸变影响的可能。
Based on the time marching technique and the finite volume method,a threedimensional numerical computational model was proposed through the combination of the body force model and elementary cascade method in order to predict the impact of the largescale inlet distortion on multistage axial compressor aerodynamic performance and stability.Under the premise of axisymmetric inlet condition,the corresponding simplified computational model was applied to analyze the internal flow field of a four-stage axial compressor under uniform and tip radial total pressure distorted inlet in detail.The calculated result with clean inlet was consistent with the related experimental result.The calculated result with tip radial total pressure distorted inlet indicated that a significant radial mixing was caused by the radial distortion in the compressor passage,and the tip radial total pressure distortioncould greatly worsen the compressor stability.The predicted stability boundary with tip radial inlet total pressure distortion gradually decreased with the increase of distortion intensity.The calculated results support the possibility of using the model to predict the radial inlet distortion impact.
Based on the time marching technique and the finite volume method,a threedimensional numerical computational model was proposed through the combination of the body force model and elementary cascade method in order to predict the impact of the largescale inlet distortion on multistage axial compressor aerodynamic performance and stability.Under the premise of axisymmetric inlet condition,the corresponding simplified computational model was applied to analyze the internal flow field of a four-stage axial compressor under uniform and tip radial total pressure distorted inlet in detail.The calculated result with clean inlet was consistent with the related experimental result.The calculated result with tip radial total pressure distorted inlet indicated that a significant radial mixing was caused by the radial distortion in the compressor passage,and the tip radial total pressure distortioncould greatly worsen the compressor stability.The predicted stability boundary with tip radial inlet total pressure distortion gradually decreased with the increase of distortion intensity.The calculated results support the possibility of using the model to predict the radial inlet distortion impact.
引文
[1]刘大响,叶培梁,胡骏,等.航空燃气涡轮发动机稳定性设计与评定技术[M].北京:航空工业出版社,2004.
[2]FIDALGO V J,HALL C A,COLIN Y.A study of fan-distortion interaction within the NASA Rotor 67transonic stage[J].Journal of Turbomachinery,2012,134(5):051011.1-051011.12.
[3]YAO J,GORRELL S E,WADIA A R.A time-accurate CFD analysis of inlet distortion induced swirl in multistage fans[R].AIAA-2007-5059,2007.
[4]LESSER A,ISELER J,NIEHUIS R.Numerical investigation of a highly loaded axial compressor stage with inlet distortions[R].ASME Paper GT-2011-46457,2011.
[5]陈美宁,朴英,王大磊.总压进气畸变对压气机转子气动影响的数值模拟[J].航空动力学报,2009,24(8):122-128.CHEN Meining,PIAO Ying,WANG Dalei.Numerical simulation of the effect of total pressure inlet distortion on a compressor rotor[J].Journal of Aerospace Power,2009,24(8):122-128.(in Chinese)
[6]刘雷,陈浮,陈焕龙,等.S弯进气道出口畸变对风扇性能影响研究[J].工程热物理学报,2014,35(4):655-658.LIU Lei,CHEN Fu,CHEN Huanlong,et al.Investigation on effect of S-shaped inlet distortion to rear fan stage aerodynamic performance[J].Journal of Engineering Thermophysics,2014,35(4):655-658.(in Chinese)
[7]屠宝锋,刘华,胡骏.弓形静子提高压气机抗旋流畸变能力研究[J].航空动力学报,2016,31(8):1943-1949.TU Baofeng,LIU Hua,HU Jun.Study on improvement of the compressor anti-swirl distortion capacity with bowed stator[J].Journal of Aerospace Power,2016,31(8):1943-1949.(in Chinese)
[8]屠宝锋,胡骏.旋流畸变影响低速轴流压气机数值模拟研究[J].推进技术,2016,37(9):1649-1656.TU Baofeng,HU Jun.Numerical simulation of low speed axial compressor with swirl distortion[J].Journal of Propulsion Technology,2016,37(9):1649-1656.(in Chinese)
[9]PEARSON H,MCKENZIE A B.Wakes in axial compressors[J].Journal of the Royal Aeronautical Society,1959,63(7):415-416.
[10]EHRICH F.Circumferential inlet distortions in axial flow turbomachinery[J].Journal of the Aeronautical Sciences,1957,24(6):413-417.
[11]YEH H.An actuator disc analysis of inlet distortion and rotating stall in axial flow turbomachines[J].Journal of the Aerospace Sciences,2015,26(11):739-753.
[12]GONG Y F.A computational model for rotating stall and inlet distortions in multistage compressors[D].Cambridge,US:Massachusetts Institute of Technology,1998.
[13]THOLLET W,DUFOUR G,CARBONNEAU X,et al.Body-force modeling for aerodynamic analysis of air intake-fan interactions[J].International Journal of Numerical Methods for Heat and Fluid Flow,2015,26(7):2048-2065.
[14]HALE A,DAVIS M W,KNEILE K R.Turbine engine analysis compressor code TEACC:PartⅠtechnical approach and steady results[R].AIAA 94-0148,1994.
[15]HALE A,CHALK J,KLEPPER J,et al.Turbine engine analysis compressor code TEACC:PartⅡmulti-stage compressors and inlet distortion[R].AIAA 99-3214,1999.
[16]CHIMA R V.A three-dimensional unsteady CFD model of compressor stability[R].ASME Paper GT-2006-90040,2006.
[17]郑宁,邹正平,徐力平.风扇进气畸变三维非定常数值模拟技术研究[J].航空动力学报,2007,22(1):60-65.ZHENG Ning,ZOU Zhengping,XU Liping.3-D unsteady numerical simulation of fan/compressor with inlet distortion[J].Journal of Aerospace Power,2007,22(1):60-65.(in Chinese)
[18]许开富,乔渭阳,罗华玲.风扇/压气机稳定性三维模型的研究[J].推进技术,2008,29(3):344-348.XU Kaifu,QIAO Weiyang,LUO Hualing.A 3-D CFD analysis code of fan and compressor stability[J].Journal of Propulsion Technology,2008,29(3):344-348.(in Chinese)
[19]安玉戈,刘火星.压气机进气畸变数值模拟技术研究[J].航空学报,2012,33(9):1624-1632.AN Yuge,LIU Huoxing.Numerical simulation of compressor with inlet distortion[J].Acta Aeronautica et Astronautica Sinica,2012,33(9):1624-1632.(in Chinese)
[20]郭晋,胡骏,尹超,等.单级跨声速压气机进气畸变数值模拟[J].航空动力学报,2016,31(3):669-677.GUO Jin,HU Jun,YIN Chao,et al.Numerical simulation of single-stage transonic compressor with inlet distortion[J].Journal of Aerospace Power,2016,31(3):669-677.(in Chinese)
[21]SIMON J F.Contribution to throughflow modelling for axial flow turbomachines[D].Belgium,France:University of Liège,2007.
[22]TADDEI S R,LAROCCA F.CFD-based analysis of multistage throughflow surfaces with incidence[J].Mechanics Research Communications,2013,47:6-10.
[23]PACCIANI R,RUBECHINI F,MARCONCINI M,et al.A CFD-based throughflow method with an explicit body force model and an adaptive formulation for the S2streamsurface[J].Journal of Power and Energy,2016,230(1):16-28.
[24]李晓娟,金海良,桂幸民.风扇/增压级内外涵联算的特性数值模拟[J].航空动力学报,2009,24(12):2719-2726.LI Xiaojuan,JIN Hailiang,GUI Xingmin.Performance numerical investigation of double-channel fan/compressor[J].Journal of Aerospace Power,2009,24(12):2719-2726.(in Chinese)
[25]GALLIMORE S J,CUMPSTY N A.Spanwise mixing in multistage axial flow compressors:PartⅠexperimental investigation[R].ASME Paper 86-GT-20,1986.
[26]GALLIMORE S J.Spanwise mixing in multistage axial flow compressors:PartⅡthroughflow calculations including mixing[R].ASME Paper 86-GT-21,1986.
[27]EDWARDS J R.A low-diffusion flux-splitting scheme for Navier-Stokes calculations[J].Computers and Fluids,1997,26(6):635-659.
[28]CREVELING H F,CARMODY R H.Axial-flow compressor computer program for calculating off-design performance[R].NASA CR 72427,1968.
[29]MARBLE F E.Three-dimensional flow in turbomachines,aerodynamics of turbines and compressors[M].Princeton,US:Princeton University Press,1964.
[30]赵勇.风扇/压气机非设计点性能计算和进气畸变影响预测方法研究[D].南京:南京航空航天大学,2008.ZHAO Yong.Investigations on off-design performance computation and predicting methods of inlet flow distortion for fan/compressor[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[31]ROBERTS W B,SEROVY G K,SANDERCOCKD M.Modeling the 3-D flow effects on deviation angle for axial compressor middle stages[J].Journal of Engineering for Gas Turbines and Power,1986,108(1):131-137.
[32]LAKSHMINARAYANA B.Methods of pedicting the tip clearance effects in axial flow turbomachinery[J].Journal of Fluids Engineering,1970,92(3):467-482.
[33]LIEBLEIN S,SCHWENK F C,BRODERICK R L.Diffusion factor for estimating losses and limiting blade loading in axial flow compressor blade elements[R].NACA RME53D01,1953.
[34]KOCH C C.Stalling pressure rise capability of axial flow compressor stages[J].Journal of Engineering for Gas Turbines and Power,1981,103(4):645-656.
[35]张晨凯.多级轴流压气机内复杂流动结构的实验和数值研究[D].南京:南京航空航天大学,2015.ZHANG Chenkai.Experimental and numerical investigations on complex flow structures of multistage axial flow compressors[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2015.(in Chinese)
[2]FIDALGO V J,HALL C A,COLIN Y.A study of fan-distortion interaction within the NASA Rotor 67transonic stage[J].Journal of Turbomachinery,2012,134(5):051011.1-051011.12.
[3]YAO J,GORRELL S E,WADIA A R.A time-accurate CFD analysis of inlet distortion induced swirl in multistage fans[R].AIAA-2007-5059,2007.
[4]LESSER A,ISELER J,NIEHUIS R.Numerical investigation of a highly loaded axial compressor stage with inlet distortions[R].ASME Paper GT-2011-46457,2011.
[5]陈美宁,朴英,王大磊.总压进气畸变对压气机转子气动影响的数值模拟[J].航空动力学报,2009,24(8):122-128.CHEN Meining,PIAO Ying,WANG Dalei.Numerical simulation of the effect of total pressure inlet distortion on a compressor rotor[J].Journal of Aerospace Power,2009,24(8):122-128.(in Chinese)
[6]刘雷,陈浮,陈焕龙,等.S弯进气道出口畸变对风扇性能影响研究[J].工程热物理学报,2014,35(4):655-658.LIU Lei,CHEN Fu,CHEN Huanlong,et al.Investigation on effect of S-shaped inlet distortion to rear fan stage aerodynamic performance[J].Journal of Engineering Thermophysics,2014,35(4):655-658.(in Chinese)
[7]屠宝锋,刘华,胡骏.弓形静子提高压气机抗旋流畸变能力研究[J].航空动力学报,2016,31(8):1943-1949.TU Baofeng,LIU Hua,HU Jun.Study on improvement of the compressor anti-swirl distortion capacity with bowed stator[J].Journal of Aerospace Power,2016,31(8):1943-1949.(in Chinese)
[8]屠宝锋,胡骏.旋流畸变影响低速轴流压气机数值模拟研究[J].推进技术,2016,37(9):1649-1656.TU Baofeng,HU Jun.Numerical simulation of low speed axial compressor with swirl distortion[J].Journal of Propulsion Technology,2016,37(9):1649-1656.(in Chinese)
[9]PEARSON H,MCKENZIE A B.Wakes in axial compressors[J].Journal of the Royal Aeronautical Society,1959,63(7):415-416.
[10]EHRICH F.Circumferential inlet distortions in axial flow turbomachinery[J].Journal of the Aeronautical Sciences,1957,24(6):413-417.
[11]YEH H.An actuator disc analysis of inlet distortion and rotating stall in axial flow turbomachines[J].Journal of the Aerospace Sciences,2015,26(11):739-753.
[12]GONG Y F.A computational model for rotating stall and inlet distortions in multistage compressors[D].Cambridge,US:Massachusetts Institute of Technology,1998.
[13]THOLLET W,DUFOUR G,CARBONNEAU X,et al.Body-force modeling for aerodynamic analysis of air intake-fan interactions[J].International Journal of Numerical Methods for Heat and Fluid Flow,2015,26(7):2048-2065.
[14]HALE A,DAVIS M W,KNEILE K R.Turbine engine analysis compressor code TEACC:PartⅠtechnical approach and steady results[R].AIAA 94-0148,1994.
[15]HALE A,CHALK J,KLEPPER J,et al.Turbine engine analysis compressor code TEACC:PartⅡmulti-stage compressors and inlet distortion[R].AIAA 99-3214,1999.
[16]CHIMA R V.A three-dimensional unsteady CFD model of compressor stability[R].ASME Paper GT-2006-90040,2006.
[17]郑宁,邹正平,徐力平.风扇进气畸变三维非定常数值模拟技术研究[J].航空动力学报,2007,22(1):60-65.ZHENG Ning,ZOU Zhengping,XU Liping.3-D unsteady numerical simulation of fan/compressor with inlet distortion[J].Journal of Aerospace Power,2007,22(1):60-65.(in Chinese)
[18]许开富,乔渭阳,罗华玲.风扇/压气机稳定性三维模型的研究[J].推进技术,2008,29(3):344-348.XU Kaifu,QIAO Weiyang,LUO Hualing.A 3-D CFD analysis code of fan and compressor stability[J].Journal of Propulsion Technology,2008,29(3):344-348.(in Chinese)
[19]安玉戈,刘火星.压气机进气畸变数值模拟技术研究[J].航空学报,2012,33(9):1624-1632.AN Yuge,LIU Huoxing.Numerical simulation of compressor with inlet distortion[J].Acta Aeronautica et Astronautica Sinica,2012,33(9):1624-1632.(in Chinese)
[20]郭晋,胡骏,尹超,等.单级跨声速压气机进气畸变数值模拟[J].航空动力学报,2016,31(3):669-677.GUO Jin,HU Jun,YIN Chao,et al.Numerical simulation of single-stage transonic compressor with inlet distortion[J].Journal of Aerospace Power,2016,31(3):669-677.(in Chinese)
[21]SIMON J F.Contribution to throughflow modelling for axial flow turbomachines[D].Belgium,France:University of Liège,2007.
[22]TADDEI S R,LAROCCA F.CFD-based analysis of multistage throughflow surfaces with incidence[J].Mechanics Research Communications,2013,47:6-10.
[23]PACCIANI R,RUBECHINI F,MARCONCINI M,et al.A CFD-based throughflow method with an explicit body force model and an adaptive formulation for the S2streamsurface[J].Journal of Power and Energy,2016,230(1):16-28.
[24]李晓娟,金海良,桂幸民.风扇/增压级内外涵联算的特性数值模拟[J].航空动力学报,2009,24(12):2719-2726.LI Xiaojuan,JIN Hailiang,GUI Xingmin.Performance numerical investigation of double-channel fan/compressor[J].Journal of Aerospace Power,2009,24(12):2719-2726.(in Chinese)
[25]GALLIMORE S J,CUMPSTY N A.Spanwise mixing in multistage axial flow compressors:PartⅠexperimental investigation[R].ASME Paper 86-GT-20,1986.
[26]GALLIMORE S J.Spanwise mixing in multistage axial flow compressors:PartⅡthroughflow calculations including mixing[R].ASME Paper 86-GT-21,1986.
[27]EDWARDS J R.A low-diffusion flux-splitting scheme for Navier-Stokes calculations[J].Computers and Fluids,1997,26(6):635-659.
[28]CREVELING H F,CARMODY R H.Axial-flow compressor computer program for calculating off-design performance[R].NASA CR 72427,1968.
[29]MARBLE F E.Three-dimensional flow in turbomachines,aerodynamics of turbines and compressors[M].Princeton,US:Princeton University Press,1964.
[30]赵勇.风扇/压气机非设计点性能计算和进气畸变影响预测方法研究[D].南京:南京航空航天大学,2008.ZHAO Yong.Investigations on off-design performance computation and predicting methods of inlet flow distortion for fan/compressor[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[31]ROBERTS W B,SEROVY G K,SANDERCOCKD M.Modeling the 3-D flow effects on deviation angle for axial compressor middle stages[J].Journal of Engineering for Gas Turbines and Power,1986,108(1):131-137.
[32]LAKSHMINARAYANA B.Methods of pedicting the tip clearance effects in axial flow turbomachinery[J].Journal of Fluids Engineering,1970,92(3):467-482.
[33]LIEBLEIN S,SCHWENK F C,BRODERICK R L.Diffusion factor for estimating losses and limiting blade loading in axial flow compressor blade elements[R].NACA RME53D01,1953.
[34]KOCH C C.Stalling pressure rise capability of axial flow compressor stages[J].Journal of Engineering for Gas Turbines and Power,1981,103(4):645-656.
[35]张晨凯.多级轴流压气机内复杂流动结构的实验和数值研究[D].南京:南京航空航天大学,2015.ZHANG Chenkai.Experimental and numerical investigations on complex flow structures of multistage axial flow compressors[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2015.(in Chinese)