高翔,晁晓亮,贾一哲
GAO Xiang,CHAO Xiao-liang,JIA Yi-zhe

• 1:中国飞行试验研究院

摘要(Abstract)：

针对NASA跨音速转子67,建立了可靠的数值计算模型,对3种不同的目标函数开展了非轴对称端壁造型的优化工作。3种优化方案均使得转子性能得到了不同程度改善,效率提升最大为0.41%。优化结果表明,由于相同流量的约束,转子通道中流量分布沿径向发生了改变,对于近轮毂的端壁区域来说,造型后静压梯度的方向对流场具有重要影响。不同造型结果中叶片尾缘三维角区分离的位置与范围也有所不同,当三维角区分离后移且沿径向发生迁移时,会使得效率得到的增益明显降低。
Reliable numerical computation method was built on rotor67. Based on this numerical computation method,optimization of non-axisymmetric endwall contouring focusing on three different objective functions were conducted. The three optimal results all improved the performances of the rotor and the maximum improvement was 0. 41%. Because of the restriction of the mass flow rate during optimization,the flow fields in different span height changed to different extent. As for the regions near hub,validity of the gradient direction influences the flow field significantly. In different optimal results,the location and scope of the threedimensional corner separation near the trailing edge of the blade altered obviously,and the gain in efficiency drops when the separation region moves backward and migrates towards spanwise direction.

关键词(KeyWords)： 跨音速轴流压气机转子;非轴对称端壁造型;二次流;多目标优化
transonic axial-flow compressor rotor;non-axisymmetric endwall;secondary flow;multi-objective optimization

Abstract:

Keywords:

基金项目(Foundation):

作者(Author): 高翔,晁晓亮,贾一哲
GAO Xiang,CHAO Xiao-liang,JIA Yi-zhe

参考文献(References)：

• [1]Harvey N W,Rose M G.Non-axisymmetric turbine endwall design:three2dimensional linear design system[C].Proceedings of ASME Turbo Expo 1999 Power for Land,Sea&Air,New York,USA,1999.
• [2]Hartland J C,Gregory-Smith D.Non-axisymmetric turbine end wall design:experimental validation[C].Proceedings of ASME Turbo Expo 1999 Power for Land,Sea&Air,New York,USA,1999.
• [3]Brennan G,Harvey N W,Rose M G,et al.Improving the efficiency of the trent 500 HP turbine using nonaxisymmetric endwalls part I:turbine design[R].ASME Paper 2001GT-0444,2001.
• [4]黄洪雁,王仲奇,冯国泰.上端壁翘曲对涡轮叶栅流场的影响[J].推进技术,2002,23(1):36-39.
• [5]Hoeger M,Cardamone P,Fottner L.Influence of endwall contouring on the transonic flow in a compressor blade[R].ASME Paper GT2002-30440,2002.
• [6]卢家玲,楚武利,吴艳辉.利用静子非轴对称轮毂造型提高轴流压缩机效率[J].风机技术,2009(2):3-6.
• [7]Harvey N W.Some effects of non axisymmetric endwall profiling on axial flow compressor aero dynamics Part II:Multi-Stage HPC CFD Study[R].ASME Paper GT2008-50991,2008.
• [8]郑覃,卢少鹏,羌晓青,等.动叶局部弯曲对压气机流场和性能的影响[J].流体机械,2015,43(7):27-31.
• [9]刘力歌,冯文卓,高欢,等.一种新型网壳储罐的支座结构及其优化[J].压力容器,2016,33(2):30-34.
• [10]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.
• [11]王晋华,同利平,赵珊珊.离心压缩机组管道优化布置及应力分析计算[J].化工设备与管道,2014,51(4):50-53.
• [12]Strazisar A J.Laser Anemometer Measurement in a Transon Axial-Flow Fan Rotor[M].NASA-TP-2879,1989.