涡轮平面叶栅设计工况下旋涡结构分析
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摘要
为了揭示涡轮流道内旋涡结构的空间演化规律,本文采用数值模拟方法对某型涡轮平面叶栅内部流场进行了详细的拓扑分析。首先,利用已有的平面叶栅吹风实验结果对数值模拟结果做了详细的校核,对比结果表明实验结果和数值模拟结果在叶栅气动性能的变化趋势上保持一致,因此用数值模拟结果来定性分析叶栅旋涡结构具有可行性。通过对叶栅流道内部和出口若干个截面上的二次流流线的分析,建立起该涡轮平面叶栅流道旋涡结构,结果表明该叶栅旋涡结构呈上下对称分布,共存在六个旋涡,即上、下马蹄涡、上、下通道涡、上、下集中脱落涡。最终,通过建立叶栅三维定常旋涡结构,明确了叶栅流场内旋涡演化规律。
In order to indicate the evolution rule of the vortex structure in the flow passage of a turbine cascade,it was analyzed in detail by using the numerical simulation method,that the vortex structures of a certain type of turbine planar cascade. Firstly,this numerical simulation method was verified against existing planar cascade experimental results carefully,and the results show that experimental and numerical simulation results on the change tendency of the cascade aerodynamic performance are consistent,so it is feasible to qualitative analysis of the vortex structure by the results of numerical simulation. Through both internal and export sections of cascade passage,the secondary flow streamlines were analyzed,and then vortex structure of the turbine planar cascade were established,the results show that the distribution of the vortex structure is symmetrical,altogether there are six vortexes,namely the up and down horseshoe vortex,the up and down passage vortex,the up and down concentrated shedding vortex. Finally,through the establishment of three-dimensional unsteady vortex structures of this turbine cascade,it has been clear about the evolution rule of the turbine cascade flow field.
In order to indicate the evolution rule of the vortex structure in the flow passage of a turbine cascade,it was analyzed in detail by using the numerical simulation method,that the vortex structures of a certain type of turbine planar cascade. Firstly,this numerical simulation method was verified against existing planar cascade experimental results carefully,and the results show that experimental and numerical simulation results on the change tendency of the cascade aerodynamic performance are consistent,so it is feasible to qualitative analysis of the vortex structure by the results of numerical simulation. Through both internal and export sections of cascade passage,the secondary flow streamlines were analyzed,and then vortex structure of the turbine planar cascade were established,the results show that the distribution of the vortex structure is symmetrical,altogether there are six vortexes,namely the up and down horseshoe vortex,the up and down passage vortex,the up and down concentrated shedding vortex. Finally,through the establishment of three-dimensional unsteady vortex structures of this turbine cascade,it has been clear about the evolution rule of the turbine cascade flow field.
引文
[1]姜正礼,凌代军,王晖.高压涡轮导向器扇形叶栅试验研究[J].燃气涡轮试验与研究,2006,19(1):17-20,53
[2]龚建波,俞镔,朱俊强,等.超音速涡轮叶栅气动性能实验及分析[J].工程热物理学报,2006,27(增刊1):125-128.
[3]D.Kuchmann.The Aerodynamic Design of Aircraft[M].Pergamon Press,1978.
[4]张妍,韩万金.间隙尺寸对涡轮叶栅气动性能影响的实验研究[J].节能技术,2004,22(4):11-12.
[5]H.P.Wang.Flow Visualization in a Linear Turbine Cascade of high Performance Turbine Blades[J].Journal of Turbomachinery,1997,119(1):1-8.
[6]W.R.Hawthorne.Rational Flow through Cascades[J].J.Mech.and Appl.Mach,1955,8(3):266-279.
[7]唐晓雷,罗磊,温风波,等.跨音速气冷涡轮S1流面气动优化设计研究[J].节能技术,2016,34(5):400-405.
[8]杨杰,刘冬华,潘尚能,等.动力涡轮动叶预扭对涡轮部件气动影响研究[J].热能动力工程,2016,31(8):44-50.
[9]韩万金,钟兢军,黄洪雁,等.具有叶顶间隙的涡轮正弯叶栅流场的拓扑与旋涡结构[J].空气动力学学报,1999(2):20-28.
[10]王松涛,王仲奇,袁宁,等.正弯涡轮叶栅内旋涡结构的数值模拟[J].航空动力学报,1999(4):393-396,453.
[11]周逊,韩万金,王仲奇.后加载叶型叶栅的拓扑与旋涡结构[J].热力透平,2005(1):1-6,20.
[12]林奇燕,郑群,岳国强.叶栅二次流旋涡结构与损失分析[J].航空动力学报,2007(9):1518-1525.
[13]冯子明,李青燕,邢宗涛,等.冲角对导向涡轮叶栅气动性能影响研究[J].节能技术,2011,29(6):486-489.
[14]刘正,陈榴,戴韧.燃气透平叶片3种出气边冷却结构中流动与传热性能的比较[J].热能动力工程,2016,31(11):32-37.
[15]马永峰,低压涡轮导向叶片平面叶栅试验及数值模拟[J].航空发动机,2012(6):20-23.
[16]阚晓旭.矩形扩压叶栅中应用叶尖小翼的性能研究[D].大连:大连海事大学,2012:22.
[17]刘壮,阚晓旭,陆华伟,等.跨音速涡轮平面叶栅气动性能试验研究[J].大连海事大学学报,2013,39(2):123-127.
[18]邓学鎣,刘谋佶,吕志咏.油流显示技术和油流谱分析原理[J].空气动力学学报,1987(2):122-131.
[19]Kang Shun,Wang Zhongqi.Application of topo-logical analysis to studying the three-dimensional flow in cascades;part i.topo-logical rules for skin-friction lines and section streamlines[J].Applied Mathematics and Mechanics,1990,11(5):489-495.
[20]吴兆滨.叶片弯曲降低泄漏损失的实验研究[J].节能技术,2003,21(4):11-13.
[2]龚建波,俞镔,朱俊强,等.超音速涡轮叶栅气动性能实验及分析[J].工程热物理学报,2006,27(增刊1):125-128.
[3]D.Kuchmann.The Aerodynamic Design of Aircraft[M].Pergamon Press,1978.
[4]张妍,韩万金.间隙尺寸对涡轮叶栅气动性能影响的实验研究[J].节能技术,2004,22(4):11-12.
[5]H.P.Wang.Flow Visualization in a Linear Turbine Cascade of high Performance Turbine Blades[J].Journal of Turbomachinery,1997,119(1):1-8.
[6]W.R.Hawthorne.Rational Flow through Cascades[J].J.Mech.and Appl.Mach,1955,8(3):266-279.
[7]唐晓雷,罗磊,温风波,等.跨音速气冷涡轮S1流面气动优化设计研究[J].节能技术,2016,34(5):400-405.
[8]杨杰,刘冬华,潘尚能,等.动力涡轮动叶预扭对涡轮部件气动影响研究[J].热能动力工程,2016,31(8):44-50.
[9]韩万金,钟兢军,黄洪雁,等.具有叶顶间隙的涡轮正弯叶栅流场的拓扑与旋涡结构[J].空气动力学学报,1999(2):20-28.
[10]王松涛,王仲奇,袁宁,等.正弯涡轮叶栅内旋涡结构的数值模拟[J].航空动力学报,1999(4):393-396,453.
[11]周逊,韩万金,王仲奇.后加载叶型叶栅的拓扑与旋涡结构[J].热力透平,2005(1):1-6,20.
[12]林奇燕,郑群,岳国强.叶栅二次流旋涡结构与损失分析[J].航空动力学报,2007(9):1518-1525.
[13]冯子明,李青燕,邢宗涛,等.冲角对导向涡轮叶栅气动性能影响研究[J].节能技术,2011,29(6):486-489.
[14]刘正,陈榴,戴韧.燃气透平叶片3种出气边冷却结构中流动与传热性能的比较[J].热能动力工程,2016,31(11):32-37.
[15]马永峰,低压涡轮导向叶片平面叶栅试验及数值模拟[J].航空发动机,2012(6):20-23.
[16]阚晓旭.矩形扩压叶栅中应用叶尖小翼的性能研究[D].大连:大连海事大学,2012:22.
[17]刘壮,阚晓旭,陆华伟,等.跨音速涡轮平面叶栅气动性能试验研究[J].大连海事大学学报,2013,39(2):123-127.
[18]邓学鎣,刘谋佶,吕志咏.油流显示技术和油流谱分析原理[J].空气动力学学报,1987(2):122-131.
[19]Kang Shun,Wang Zhongqi.Application of topo-logical analysis to studying the three-dimensional flow in cascades;part i.topo-logical rules for skin-friction lines and section streamlines[J].Applied Mathematics and Mechanics,1990,11(5):489-495.
[20]吴兆滨.叶片弯曲降低泄漏损失的实验研究[J].节能技术,2003,21(4):11-13.