叶尖间隙对轴流压气机近失速叶尖流动的影响
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摘要
为研究动叶间隙大小对轴流压气机近失速叶尖流动的影响,以一台高亚声速一级半压气机级为研究对象,在设计间隙、小间隙及2个大间隙下进行定常三维数值模拟。计算结果表明,设计间隙下压气机喘振裕度最大,随着间隙增大,裕度近似呈线性降低,失速形式由动叶吸力面分离引起的"叶尖失速"转变为"泄漏涡堵塞失速"。大间隙情况下,叶尖前缘附近发出的泄漏流形成松散的涡系结构,诱导中部及尾缘附近泄漏流共同形成回流及大量二次泄漏,堵塞转子通道进口,引起失速的发生。
Three-dimensional steady RANS simulations were conducted on a 1.5 compressor stage at small,nominal and large clearances to study the influence of tip clearance height on near stall tip flow fields in the axial compressor stage. The calculation results show that the compressor stage achieved the largest stall margin at the nominal tip clearance.With the increase of the clearance height,the stall margin decreased linearly,the form of compressor stall changed from "blade tip stall" caused by lifting of movable vane suction surface to "tip clearance vortex blockage stall". Under the near stall condition with a large clearance,a loose vortex structure was formed by tip leakage flow originating from leading edge of blade tip,inducing the tip leakage flow from central and downstream locations together to form backward flow and tremendous secondary leakage,blocking the inlet of the rotor passage,which led to stall occurrence.
Three-dimensional steady RANS simulations were conducted on a 1.5 compressor stage at small,nominal and large clearances to study the influence of tip clearance height on near stall tip flow fields in the axial compressor stage. The calculation results show that the compressor stage achieved the largest stall margin at the nominal tip clearance.With the increase of the clearance height,the stall margin decreased linearly,the form of compressor stall changed from "blade tip stall" caused by lifting of movable vane suction surface to "tip clearance vortex blockage stall". Under the near stall condition with a large clearance,a loose vortex structure was formed by tip leakage flow originating from leading edge of blade tip,inducing the tip leakage flow from central and downstream locations together to form backward flow and tremendous secondary leakage,blocking the inlet of the rotor passage,which led to stall occurrence.
引文
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[8]黄旭东,陈海昕,符松.Rotor 37顶隙泄漏流的演化、影响及机匣处理[J].航空动力学报,2010,25(12):2673-2682.
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[10]刘波,茅晓晨,张鹏,等.叶尖间隙效应对跨声速压气机性能影响的研究[J].推进技术,2016,37(8):1401-1409.
[11]杨晰琼,刘波,曹志远,等.跨声速风扇转子间隙流动结构分析[J].航空动力学报,2016,31(9):2258-2267.
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[13]谢芳,楚武利,李相君,等.叶尖间隙对跨声速轴流压气机近失速的影响[J].航空动力学报,2014,29(10):2417-2423.
[14]何成,王如根,胡加国,等.不同转速下叶尖间隙流对跨声速压气机失速的影响[J].推进技术,2016,37(9):1657-1663.
[15]Reid L,Moore D.Performance of a single-stage axialflow transonic compressor with rotor and stator aspect Rrtios of 1.19 and 1.26,respectively,and with design pressure ratio 1.82[R].NASA TP-1338,1978.
[16]Wilke I,Kau H P,Brignole G.Numerically aided design of a high-efficient casing treatment for a transonic compressor[C]//ASME Paper No.GT2005-68993,2005.
[17]祝华云,徐志明,胡国军,等.尾缘厚度对压气机叶栅气动性能的影响研究[J].机电工程,2016,33(2):187-190.
[18]Vo H D,Tan C S,Greitzer E M.Criteria for spike initiated rotating stall[J].Journal of Turbomachinery,2008,130(1):011023.
[2]吴艳辉,楚武利,刘志伟.轴流压气机转子性能及间隙流动研究[J].西北工业大学学报,2005,23(6):737-741.
[3]高翔,晁晓亮,贾一哲.轴流压气机转子端壁造型多目标优化的数值研究[J].流体机械,2017,45(3):26-32.
[4]Denton J.Loss mechanisms in turbomachines[J].Journal of Turbomachinery,1993,115(4):621-656.
[5]Koch C C.Stalling pressure rise capability of axial flow compressor stages[J].Journal of Engineering for Power,1981,103(4):645-656.
[6]Suder K L.Blockage development in a transonic axial compressor rotor[J].Journal of Turbomachinery,1998,120(3):465-476.
[7]张晨凯,胡骏,王志强,等.轴流压气机转子叶尖间隙流动结构的数值研究[J].航空学报,2014,35(5):1236-1245.
[8]黄旭东,陈海昕,符松.Rotor 37顶隙泄漏流的演化、影响及机匣处理[J].航空动力学报,2010,25(12):2673-2682.
[9]Sakulkaew S,Tan C S,Donahoo E.Compressor efficiency variation with rotor tip gap from vanishing to large clearance[J].Journal of Turbomachinery,2013,135(3):1-10.
[10]刘波,茅晓晨,张鹏,等.叶尖间隙效应对跨声速压气机性能影响的研究[J].推进技术,2016,37(8):1401-1409.
[11]杨晰琼,刘波,曹志远,等.跨声速风扇转子间隙流动结构分析[J].航空动力学报,2016,31(9):2258-2267.
[12]Schlechtriem S,Lotzerich M.Breakdown of tip leakage vortices in compressors at flow conditions close to stall[R].ASME Paper 1997-GT-41,1997.
[13]谢芳,楚武利,李相君,等.叶尖间隙对跨声速轴流压气机近失速的影响[J].航空动力学报,2014,29(10):2417-2423.
[14]何成,王如根,胡加国,等.不同转速下叶尖间隙流对跨声速压气机失速的影响[J].推进技术,2016,37(9):1657-1663.
[15]Reid L,Moore D.Performance of a single-stage axialflow transonic compressor with rotor and stator aspect Rrtios of 1.19 and 1.26,respectively,and with design pressure ratio 1.82[R].NASA TP-1338,1978.
[16]Wilke I,Kau H P,Brignole G.Numerically aided design of a high-efficient casing treatment for a transonic compressor[C]//ASME Paper No.GT2005-68993,2005.
[17]祝华云,徐志明,胡国军,等.尾缘厚度对压气机叶栅气动性能的影响研究[J].机电工程,2016,33(2):187-190.
[18]Vo H D,Tan C S,Greitzer E M.Criteria for spike initiated rotating stall[J].Journal of Turbomachinery,2008,130(1):011023.