多级高负荷风扇处理机匣扩稳与静子匹配研究
|
摘要
以双级高负荷风扇为研究对象,以三维数值模拟为手段,探索一种适合多级高负荷风扇而又不影响其大流量点性能的扩稳方案。最终,对风扇采用周向槽对风扇小流量点进行扩稳,同时调节处理机匣上游静子局部基元使之与处理机匣相匹配,解决了风扇大流量点的堵塞问题。风扇的稳定裕度提高到16.3%,同时风扇大流量点的流量也没有减小,从而兼顾了设计状态的推力水平。
A two-stage high-loading fan with three-dimensional numerical simulations was studied.The simulation results were used to propose a scheme that enlarged the stall margin of multistage high-loading fans without sacrifice of the flow capacity when operating with a large mass flow rate.Furthermore,a circumferential groove casing treatment was used and adjustments were made to the upstream stator angle to match the casing treatment.The stall margin was thus increased to 16.3%,without reduction in the maximum mass flow rate or the design thrust performance.
A two-stage high-loading fan with three-dimensional numerical simulations was studied.The simulation results were used to propose a scheme that enlarged the stall margin of multistage high-loading fans without sacrifice of the flow capacity when operating with a large mass flow rate.Furthermore,a circumferential groove casing treatment was used and adjustments were made to the upstream stator angle to match the casing treatment.The stall margin was thus increased to 16.3%,without reduction in the maximum mass flow rate or the design thrust performance.
引文
[1]陈仲光,张志舒,李德旺,等.F119发动机总体性能特点分析与评估[J].航空科学技术,2013(3):39-42.CHEN Zhonggunag,ZHANG Zhishu,LI Dewang,et al.Analysis and evaluation of F119engine overall performance[J].Aeronautical Science and Technology,2013(3):39-42.(in Chinese)
[2]VIARS P R.The impact of IHPTET on the engine/aircraft system[R].AIAA 89-2137,1989.
[3]MERCHANT A A.Aerodynamic design and performance of aspirated airfoil[R].ASME Paper 2002-GT-30369,2002.
[4]金海良,金东海,桂幸民.某高负荷跨声双级风扇气动设计与数值模拟[J].航空动力学报,2011,26(2):272-280.JIN Hailiang,JIN Donghai,GUI Xingmin.Aerodynamic design and numerical simulation of a highly loaded transonic two-stage fan[J].Journal of Aerospace power,2011,26(2):272-280.(in Chinese)
[5]陈葆实,胡国荣,魏玉冰,等.高马赫数、高负荷单级风扇设计和试验研究[J].航空发动机,2000(3):28-35.
[6]吴艳辉,张皓光,楚武利,等.双级跨音风扇轴向缝处理机匣结构优化的数值研究[J].西北工业大学学报,2010,28(2):228-233.WU Yanhui,ZHANG Haoguang,CHU Wuli,et al.Further numerical investigation of optimum structure of axial slot casing treatment on a two-stage transonic fan[J].Journal of Northwestern Polytechnical University,2010,28(2):228-233.(in Chinese)
[7]吴艳辉,张皓光,楚武利,等.双级跨声风扇双段轴向缝式机匣扩稳机理分析[J].推进技术,2010,31(2):181-186,192.WU Yanhui,ZHANG Haoguang,CHU Wuli,et al.Mechanism of stall margin improvement of two stages transonic fan with two-portion axial slot casing treatment[J].Journal of Propulsion Technology,2010,31(2):181-186,192.(in Chinese)
[8]李玲,于清,陆亚钧.处理机匣在单级跨声速风扇上的实验研究[J].推进技术,2000,21(3):49-52.LI Ling,YU Qing,LU Yajun.Experimental research of casing treatment on a single stage transonic fan[J].Journal of Propulsion Technology,2000,21(3):49-52.(in Chinese)
[9]BAILEY E E.Effect of grooved casing treatment on the flow range capability of a single-stage axial-flow compressor[R].NASA TM X-2459,1972.
[10]MOORE R D,KOVICH G,BLADE R J.Effect of casing treatment on overwall and blade element performance of a compressor rotor[R].NASA TN-D-6538,1971.
[11]MULLER M W,SCHIFFER H P,HAH C.Effect of circumferential grooves on the aerodynamic performance of an axial single-stage transonic compressor[R].ASME Paper GT2007-27365,2007.
[12]RABE D C,HAH C.Application of casing circumferential grooves for improved stall margin in a transonic axial compressor[R].ASME Paper GT2002-30641,2002.
[13]WU Y H,CHU W L,ZHANG H G,et al.Parametric investigation of circumferential grooves on compressor rotor performance[J].Journal of Fluids Engineering,2010,132(12):121103.1-121103.10.
[14]BENNINGTON M A.Tip gap flow and casing treatments in an axial compressor[D].South Bend,US:University of Notre Dame,2009.
[15]ZHAO S F,LU X G,ZHU J Q,et al.Investigation for the effects of circumferential grooves on the unsteadiness of tip clearance flow to enhance compressor flow instability[R].ASME Paper GT2010-22652,2010.
[16]HAH C,MULLER M W,SCHIFFER H P.Study of convective flow effects in endwall casing treatments in transonic compressor rotors[R].ASME Paper GT2012-68411,2012.
[17]党春宁.周向槽机匣处理对跨声速轴流压气机影响分析[J].燃气涡轮试验与研究,2008,21(3):18-25.DANG Chunning.Analysis of the effects of circumferential groove casing treatment on a transonic axial flow compressor[J].Gas Turbine Experiment and Reserch,2008,21(3):18-25.(in Chinese)
[18]段真真,柳阳威,陆利蓬.周向槽机匣处理对某跨音转子性能的影响[J].航空学报,2014,35(8):2163-2173.DUAN Zhenzhen,LIU Yangwei,LU Lipeng.Influence of circumferential casing grooves on transonic compressor rotor performance[J].Acta Aeronautica et Astronautica Sinica,2014,35(8):2163-2173.(in Chinese)
[19]李相君,楚武利,张皓光.高负荷跨声速轴流压气机周向浅槽处理机匣扩稳机理[J].推进技术,2013,34(5):629-637.LI Xiangjun,CHU Wuli,ZHANG Haoguang.Stabilizing mechanism of shallow circumferential grooves on a high loaded transonic axial-flow compressor[J].Journal of Propulsion Technology,2013,34(5):629-637.(in Chinese)
[20]刘传乐,楚武利,张皓光.槽深对跨音速压气机稳定性影响的数值仿真[J].计算机仿真,2012(6):394-399.LIU Chuanle,CHU Wuli,ZHANG Haoguang.Numerical simulation of influence of groove's depth on stability of transonic compressor[J].Computer Simulation,2012(6):394-399.(in Chinese)
[21]KHALSA A S,WAITZ I A,TAN C S,et al.Endwall blockage in axial compressors[J].Journal of Turbomachinery,1999,121(3):499-509.
[22]SUDER K L.Blockage development in a transonic,axial compressor rotor[J].Journal of Turbomachinery,1998,120(3):465-476.
[23]刘宝杰,张志博,于贤君.轴流压气机转子叶尖泄漏堵塞特性的试验研究[J].航空学报,2013,34(12):2682-2691.LIU Baojie,ZHANG Zhibo,YU Xianjun.Experimental investigation on characteristics of tip leakage blockage in an axial compressor[J].Acta Aeronautica et Astronautica Sinica,2013,34(12):2682-2691.(in Chinese)
[2]VIARS P R.The impact of IHPTET on the engine/aircraft system[R].AIAA 89-2137,1989.
[3]MERCHANT A A.Aerodynamic design and performance of aspirated airfoil[R].ASME Paper 2002-GT-30369,2002.
[4]金海良,金东海,桂幸民.某高负荷跨声双级风扇气动设计与数值模拟[J].航空动力学报,2011,26(2):272-280.JIN Hailiang,JIN Donghai,GUI Xingmin.Aerodynamic design and numerical simulation of a highly loaded transonic two-stage fan[J].Journal of Aerospace power,2011,26(2):272-280.(in Chinese)
[5]陈葆实,胡国荣,魏玉冰,等.高马赫数、高负荷单级风扇设计和试验研究[J].航空发动机,2000(3):28-35.
[6]吴艳辉,张皓光,楚武利,等.双级跨音风扇轴向缝处理机匣结构优化的数值研究[J].西北工业大学学报,2010,28(2):228-233.WU Yanhui,ZHANG Haoguang,CHU Wuli,et al.Further numerical investigation of optimum structure of axial slot casing treatment on a two-stage transonic fan[J].Journal of Northwestern Polytechnical University,2010,28(2):228-233.(in Chinese)
[7]吴艳辉,张皓光,楚武利,等.双级跨声风扇双段轴向缝式机匣扩稳机理分析[J].推进技术,2010,31(2):181-186,192.WU Yanhui,ZHANG Haoguang,CHU Wuli,et al.Mechanism of stall margin improvement of two stages transonic fan with two-portion axial slot casing treatment[J].Journal of Propulsion Technology,2010,31(2):181-186,192.(in Chinese)
[8]李玲,于清,陆亚钧.处理机匣在单级跨声速风扇上的实验研究[J].推进技术,2000,21(3):49-52.LI Ling,YU Qing,LU Yajun.Experimental research of casing treatment on a single stage transonic fan[J].Journal of Propulsion Technology,2000,21(3):49-52.(in Chinese)
[9]BAILEY E E.Effect of grooved casing treatment on the flow range capability of a single-stage axial-flow compressor[R].NASA TM X-2459,1972.
[10]MOORE R D,KOVICH G,BLADE R J.Effect of casing treatment on overwall and blade element performance of a compressor rotor[R].NASA TN-D-6538,1971.
[11]MULLER M W,SCHIFFER H P,HAH C.Effect of circumferential grooves on the aerodynamic performance of an axial single-stage transonic compressor[R].ASME Paper GT2007-27365,2007.
[12]RABE D C,HAH C.Application of casing circumferential grooves for improved stall margin in a transonic axial compressor[R].ASME Paper GT2002-30641,2002.
[13]WU Y H,CHU W L,ZHANG H G,et al.Parametric investigation of circumferential grooves on compressor rotor performance[J].Journal of Fluids Engineering,2010,132(12):121103.1-121103.10.
[14]BENNINGTON M A.Tip gap flow and casing treatments in an axial compressor[D].South Bend,US:University of Notre Dame,2009.
[15]ZHAO S F,LU X G,ZHU J Q,et al.Investigation for the effects of circumferential grooves on the unsteadiness of tip clearance flow to enhance compressor flow instability[R].ASME Paper GT2010-22652,2010.
[16]HAH C,MULLER M W,SCHIFFER H P.Study of convective flow effects in endwall casing treatments in transonic compressor rotors[R].ASME Paper GT2012-68411,2012.
[17]党春宁.周向槽机匣处理对跨声速轴流压气机影响分析[J].燃气涡轮试验与研究,2008,21(3):18-25.DANG Chunning.Analysis of the effects of circumferential groove casing treatment on a transonic axial flow compressor[J].Gas Turbine Experiment and Reserch,2008,21(3):18-25.(in Chinese)
[18]段真真,柳阳威,陆利蓬.周向槽机匣处理对某跨音转子性能的影响[J].航空学报,2014,35(8):2163-2173.DUAN Zhenzhen,LIU Yangwei,LU Lipeng.Influence of circumferential casing grooves on transonic compressor rotor performance[J].Acta Aeronautica et Astronautica Sinica,2014,35(8):2163-2173.(in Chinese)
[19]李相君,楚武利,张皓光.高负荷跨声速轴流压气机周向浅槽处理机匣扩稳机理[J].推进技术,2013,34(5):629-637.LI Xiangjun,CHU Wuli,ZHANG Haoguang.Stabilizing mechanism of shallow circumferential grooves on a high loaded transonic axial-flow compressor[J].Journal of Propulsion Technology,2013,34(5):629-637.(in Chinese)
[20]刘传乐,楚武利,张皓光.槽深对跨音速压气机稳定性影响的数值仿真[J].计算机仿真,2012(6):394-399.LIU Chuanle,CHU Wuli,ZHANG Haoguang.Numerical simulation of influence of groove's depth on stability of transonic compressor[J].Computer Simulation,2012(6):394-399.(in Chinese)
[21]KHALSA A S,WAITZ I A,TAN C S,et al.Endwall blockage in axial compressors[J].Journal of Turbomachinery,1999,121(3):499-509.
[22]SUDER K L.Blockage development in a transonic,axial compressor rotor[J].Journal of Turbomachinery,1998,120(3):465-476.
[23]刘宝杰,张志博,于贤君.轴流压气机转子叶尖泄漏堵塞特性的试验研究[J].航空学报,2013,34(12):2682-2691.LIU Baojie,ZHANG Zhibo,YU Xianjun.Experimental investigation on characteristics of tip leakage blockage in an axial compressor[J].Acta Aeronautica et Astronautica Sinica,2013,34(12):2682-2691.(in Chinese)