压气机静子非轴对称端壁优化设计及实验

王佳宇; 胡骏; 姜超

doi:10.13224/j.cnki.jasp.20200389

压气机静子非轴对称端壁优化设计及实验

doi: 10.13224/j.cnki.jasp.20200389

1.
中国航空发动机集团有限公司沈阳发动机研究所，沈阳 110015
2.
南京航空航天大学能源与动力学院，南京 210016

基金项目: 国家科技重大专项（2017-Ⅱ-0004-0017）

详细信息

作者简介:
王佳宇（1992-），男，工程师，博士，主要从事叶轮机械气体动力学研究。

中图分类号: V231.3
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- 文章访问数: 337
- HTML浏览量: 71
- PDF量: 135
- 被引次数: 0
出版历程
- 收稿日期: 2020-09-14
- 刊出日期: 2021-10-28

Optimization design and test of the non-axisymmetric endwall of the compressor stator

1.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China
2.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要: 为了探索多级压气机环境下非轴对称端壁优化设计方法，通过数值仿真优化和实验测试方法对某中间级静子的机匣端壁和轮毂端壁进行了非轴对称端壁造型研究，提出了在优化时将目标函数选择为近端壁的局部叶高总压损失系数。结果表明：相较于传统的全叶高总压损失系数作为目标函数的优化方法，该优化方法可以在较少的优化步数（400步）内使得静子总压损失系数下降更多，这表明该方法可以有效降低优化耗时，为多级压气机中进行非轴对称端壁优化设计的工程应用奠定基础。
- 多级压气机 /
- 中间级静子 /
- 非轴对称端壁 /
- 优化设计 /
- 局部叶高 /
- 压气机实验
Abstract: In order to explore the optimization design method of non-axisymmetric endwall in multistage compressor environment，the non-axisymmetric endwall profiling of the casing endwall and the hub endwall of an embedded stator was studied by numerical simulation optimization and experimental test.The local total pressure loss coefficient of local blade height near the endwall was selected as the objective function.The result proved that compared with the traditional total pressure loss of whole blade height as the objective function，the total pressure loss coefficient of stator can be reduced more in less optimization steps （400 steps），showing that this method can effectively reduce the optimization time and lay a foundation for the engineering application of non-axisymmetric endwall optimization design in multistage compressors.
- multistage compressor /
- embedded stator /
- non-axisymmetric endwall /
- optimization design /
- local blade height /
- compressor test

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参考文献(27)

[1]	刘勤,周人治,王占学.军用航空发动机特征分析[J].燃气涡轮试验与研究,2014,27（2）:59-62.
[2]	孟令勇,高海红,郑天慧,等.航空发动机推重比技术指标研究[J].燃气涡轮试验与研究,2016,29（2）:57-62.
[3]	STARK U,SAATHOFF H.Passive and active methods to enhance axial-flow compressor aerodynamics[C]∥Hermann Schlichting-100 Years.Berlin，Heidelberg:Springer-Verlag 2009:145-167.
[4]	D'ANDREA R,BEHNKEN R L,MURRAY R M.Active control of rotating stall using pulsed-air injection:a parametric study on a low-speed axial flow compressor[J].Sensing,Actuation,and Control in Aeropropulsion,1995,2494:152-165.
[5]	MARTIN P,WILSON J,BERRY J,et al.Passive control of compressible dynamic stall[R].AIAA 2008-7506,2008.
[6]	REISING S,SCHIFFER H P.Non-axisymmetric end wall profiling in transonic compressors:Part Ⅰ improving the static pressure recovery at off-design conditions by sequential hub and shroud end wall profiling[R].ASME Paper GT2009-59133,2009.
[7]	REISING S,SCHIFFER H P.Non-axisymmetric end wall profiling in transonic compressors:Part Ⅱ design study of a transonic compressor rotor using non-axisymmetric end walls-optimization strategies and performance[R].ASME Paper GT2009-59134,2009.
[8]	HARVEY N W.Some effects of non-axisymmetric end wall profiling on axial flow compressor aerodynamics:Part Ⅰlinear cascade investigation[R].ASME Paper GT2008-50990,2008.
[9]	HARVEY N W,OFFORD T P.Some effects of non-axisymmetric end wall profiling on axial flow compressor aerodynamics:Part Ⅱ multi-stage HPC CFD study[R].ASME Paper GT2008-50991,2008.
[10]	LI X,CHU W,WU Y,et al.Effective end wall profiling rules for a highly loaded compressor cascade[J].Journal of Power and Energy,2016,230（6）:535-553.
[11]	REUTTER O,HEMMERT-POTTMANN S,HERGT A,et al.Endwall contouring and fillet design for reducing losses and homogenizing the outflow of a compressor cascade[R].ASME Paper GT2014-25277,2014.
[12]	LIU X,JIN D,GUI X.Investigation of non-axisymmetric endwall contouring in a compressor cascade[J].Journal of Thermal Science,2017,26（6）:490-504.
[13]	陈得胜,刘波,那振喆,等.针对轴流压气机的非轴对称端壁造型优化设计[J].燃气涡轮试验与研究,2013,26（1）:16-21，52.
[14]	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.
[15]	CHU W,LI X,WU Y,et al.Reduction of end wall loss in axial compressor by using non-axisymmetric profiled end wall:a new design approach based on end wall velocity modification[J].Aerospace Science and Technology,2016,55:76-91.
[16]	吴吉昌,卢新根,朱俊强.非轴对称端壁下高负荷压气机叶栅二次流动分析[J].航空动力学报,2011,26（6）:1362-1369.
[17]	崔可,宋彦萍,刘华坪,等.翘曲端壁对大折转角压气机叶栅流动的影响[J].航空动力学报,2015,30（5）:1236-1243.
[18]	VARPRE M K,PRADEEP A M.Non-axisymmetric endwall contouring in a compressor cascade with tip gap[R].ASME Paper GT2014-26725,2014.
[19]	卢家玲,楚武利,胡书珍,等.端壁造型技术在亚声轴流压气机级中的应用[J].航空动力学报,2009,24（5）:1101-1107.
[20]	LEPOT I,MENGISTU T,HIERNAUX S,et al.Highly loaded LPC blade and non axisymmetric hub profiling optimization for enhanced efficiency and stability[R].ASME Paper GT2001-46261,2001.
[21]	HOEGER M,CARDAMONE P,FOTTNER L.Influence of endwall contouring on the transonic flow in a compressor blade[R].ASME Paper GT-2002-30440,2002.
[22]	刘宝杰,张帅,于贤君.4级重复级低速模拟压气机的试验与计算[J].航空发动机,2018,44（5）:56-64.
[23]	WANG J,HU J,JIANG C,et al.Design of a sector cascade applied in the middle stage of a compressor test rig[J].Journal of Thermal Science[EB/OL].[2020-09-01].https:∥link.springer.com/article/10.1007/s11630-020-1337-8.
[24]	WANG J,HU J,JIANG C,et al.Non-axisymmetric shroud profiled endwall optimization of an embedded stator and experimental investigation[J].Energies,2020,13（3）:1-22.
[25]	ROSE M G.Non-axisymmetric endwall profiling in the HP NGV's of an axial flow gas turbine[R].ASME Paper 94-GT-249,1994.
[26]	李秋实,杨春,肖文富,等.端壁造型抑制角区失速的数值研究[J].自然科学进展,2009,19（5）:537-543.
[27]	DENTON J D.Loss mechanisms in turbomachines[J].Journal of Turbomachinary,1993,115（4）:621-656.