轴流压气机插板式进气畸变数值仿真
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摘要
以航空发动机稳定性评价体系中常用的插板实验为背景,分别进行低速、高亚声速、跨声速轴流压气机与插板畸变发生器的耦合数值仿真,研究插板畸变条件下压气机的流场特性以及不同类型压气机在插板畸变影响下的失速起始机制。研究发现:转子进口截面的周向流动是影响低速压气机稳定边界的主要因素;插板角涡对转子叶顶泄漏涡的扰动是影响高亚声速压气机稳定边界的重要原因;畸变气流影响下的叶片通道内激波强度和位置的变化是影响跨声速压气机稳定边界的关键因素。
The coupling numerical simulation of the low-speed,high-subsonic,transonic axial compressor with the flat-baffle-type distortion generator was carried out respectively.The flow field characteristics of compressor under the flat-baffle-type distortion condition and the stall boundary of the different types of compressors were analyzed.It was found that the circumferential flow in the inlet plane of the low-speed compressor,the influence of the flat baffle angular vortex on the high subsonic compressor tip leakage's flow path,and the change of passage shock wave's intensity and location in the transonic compressor rotor passage were important factors of distortion flow to the stability boundary of different types of compressor respectively.
The coupling numerical simulation of the low-speed,high-subsonic,transonic axial compressor with the flat-baffle-type distortion generator was carried out respectively.The flow field characteristics of compressor under the flat-baffle-type distortion condition and the stall boundary of the different types of compressors were analyzed.It was found that the circumferential flow in the inlet plane of the low-speed compressor,the influence of the flat baffle angular vortex on the high subsonic compressor tip leakage's flow path,and the change of passage shock wave's intensity and location in the transonic compressor rotor passage were important factors of distortion flow to the stability boundary of different types of compressor respectively.
引文
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[16]屠宝峰,胡骏.径向进气总压畸变对压气机气动稳性的影响[J].推进技术,2012,33(2):167-173.TU Baofeng,HU Jun.Effect of total pressure distortion on aerodynamic stability of compressor[J].Journal of Propulsion Technology,2012,33(2):167-173.(in Chinese)
[17]童志庭,张靖煊,李美林,等.不同进口畸变下低速压气机近失速状态非定常特征[J].工程热物理学报,2006,27(1):51-53.TONG Zhiting,ZHANG Jingxuan,LI Meilin,et al.Unsteady characteristics of low-speed compressor near stall under different inlet distortion[J].Journal of Engineering Thermophysics,2006,27(1):51-53.(in Chinese)
[18]李军,周游天.航空发动机气动稳定性畸变指数关联研究报告[R].西安:空军工程大学报告,2015.
[2]GRABER E Jr.,BRAITHWAITE W M.Summary of recent investigations of inlet flow distortion effect on engine stability[R].AIAA Paper 74-236,1974.
[3]Society of Automotive Engineers.Inlet total-pressure distortion considerations for gas turbine engines[R].Aerospace Information Report,AIR 1419,1998.
[4]REID C.The response of axial compressors to intake flow distortion[J].ASME Paper 69-GT-29,1969.
[5]DUNHAM J.CFD validation for propulsion system components[R].Advisory Group for Aeronau-tical Research and Development,AGARD-AR-355,1998.
[6]李军.进气压力畸变对涡喷、涡扇发动机稳定性影响的试验研究[R].西安:空军工程大学报告,1999.
[7]江勇,李军.发动机进气畸变流场的测量系统分析[J].燃气涡轮试验与研究,2000,13(1):9-13.JIANG Yong,LI Jun.Analysis of engine inter distortion flow field measurement[J].Gas Turbine Experiment and Research,2000,13(1):9-13.(in Chinese)
[8]程邦勤,陶增元,李军.某型涡扇发动机进气总压畸变的试验研究[J].推进技术,2003,24(1):21-23.CHENG Bangqin,TAO Zengyuan,LI Jun.Aerodynamic stability analysis of inlet total pressure distortion for turbofan[J].Journal of Propulsion Technology,2003,24(1):21-23.(in Chinese)
[9]程邦勤,陶增元,李军.某型涡扇发动机进气畸变压力脉动分析[J].航空动力学报,2003,18(1):65-69.CHENG Bangqin,TAO Zengyuan,LI Jun.Pulsatile analysis of inlet pressure distortion in turbofan engine[J].Journal of Aerospace Power,2003,18(1):65-69.(in Chinese)
[10]江勇,张百灵,陈世国,等.基于实验的发动机插板式进气畸变压力谐振分析[J].航空动力学报,2009,24(9):2057-2062.JIANG Yong,ZHANG Bailing,CHEN Shiguo,et al.Testbased syntonic analysis of the aero-engine inserted-board inlet dynamic distortion pressure[J].Journal of Aerospace Power,2009,24(9):2057-2062.(in Chinese)
[11]江勇,陶增元,张发启,等.某型飞机进气道与发动机地面匹配实验研究[J].航空动力学报,2003,18(4):554-557.JIANG Yong,TAO Zengyuan,ZHANG Faqi,et al.Matching test of an aircraft inlet and engine on the ground[J].Journal of Aerospace Power,2003,18(4):554-557.(in Chinese)
[12]李茂义,陆亚钧,弓志强,等.进口畸变条件下轴流压气机转子内流的PIV研究[J].航空动力学报,2006,21(3):461-466.LI Maoyi,LU Yajun,GONG Zhiqiang,et al.PIV investigation of the internal flow in an axial flow compressor rotor under inlet distortion[J].Journal of Aerospace Power,2006,21(3):461-466.(in Chinese)
[13]蒋华兵,陆亚钧,袁巍,等.进气畸变对低速轴流压气机失速特性的影响[J].航空动力学报,2008,23(2):355-360.JIANG Huabing,LU Yajun,YUAN Wei,et al.Influence of inlet distortion on the stall character of a low speed axial compressor[J].Journal of Aerospace Power,2008,23(2):355-360.(in Chinese)
[14]张环.旋转总压畸变对压气机稳定性影响的研究[D].南京:南京航空航天大学,2009.ZHANG Huan.Effect of rotational total pressure distortion on aerodynamic stability of compressor[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2009.(in Chinese)
[15]屠宝锋,胡骏,王志强,等.进气畸变下低速轴流压气机失速起始特性试验[J].推进技术,2010,31(4):428-437.TU Baofeng,HU Jun,WANG Zhiqiang,et al.Satll Inception of low-speed axial-flow compressor with inlet distortion[J].Journal of Propulsion Technology,2010,31(4):428-437.(in Chinese)
[16]屠宝峰,胡骏.径向进气总压畸变对压气机气动稳性的影响[J].推进技术,2012,33(2):167-173.TU Baofeng,HU Jun.Effect of total pressure distortion on aerodynamic stability of compressor[J].Journal of Propulsion Technology,2012,33(2):167-173.(in Chinese)
[17]童志庭,张靖煊,李美林,等.不同进口畸变下低速压气机近失速状态非定常特征[J].工程热物理学报,2006,27(1):51-53.TONG Zhiting,ZHANG Jingxuan,LI Meilin,et al.Unsteady characteristics of low-speed compressor near stall under different inlet distortion[J].Journal of Engineering Thermophysics,2006,27(1):51-53.(in Chinese)
[18]李军,周游天.航空发动机气动稳定性畸变指数关联研究报告[R].西安:空军工程大学报告,2015.