亚声速轴流压气机转子轴对称机匣造型优化的数值研究

高 翔; 楚武利

doi:10.13224/j.cnki.jasp.2014.04.026

亚声速轴流压气机转子轴对称机匣造型优化的数值研究

doi: 10.13224/j.cnki.jasp.2014.04.026

高翔¹,
楚武利^1,2

1. 西北工业大学动力与能源学院,西安 71007;
2. 先进航空发动机协同创新中心,北京 100191

详细信息

作者简介:
高翔：高翔(1990-),男,陕西铜川人,硕士生,主要从事叶轮机械气动热力学研究.

中图分类号: V231.3
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出版历程
- 收稿日期: 2013-09-03
- 刊出日期: 2014-04-28

Numerical investigation on subsonic axial-flow compressor rotor with implementation of axisymmetric casing contouring optimization

GAO Xiang¹,
CHU Wu-li^1,2

1. School of Power and Energy, Northwestern Polytechnical University,Xi'an 71007;
2. Co-Innovation Center for Advanced Aero-Engine,Beijing 100191,China

摘要

摘要: 以西北工业大学某亚声速轴流压气机孤立转子为研究对象,提出了较为可靠的数值模拟方法,进而采用NUMECA软件包中DESIGN/3D软件块,在峰值效率工况下对该转子机匣进行了轴对称造型优化,最终得到优化转子.优化转子在叶片前缘将叶顶间隙泄漏涡推离叶片吸力面,虽然该结果导致前30%轴向弦长间隙泄漏涡涡量及流动损失有一定程度增大,但是在后70%轴向弦长,优化转子间隙泄漏涡的涡量与流动损失比原始转子有了很大程度降低,从而使得全局损失降低,峰值点效率提高,出口绝对总压增加.优化转子的峰值点效率提升约为0.36%,大流量点效率增加更多,但是近失速点会更早地形成叶顶低速区从而诱发失速,使得优化转子比原始转子稳定裕度略有降低.
- 亚声速轴流压气机转子 /
- 轴对称造型优化 /
- 泄漏涡 /
- 流动损失 /
- 稳定裕度
Abstract: For the study object of a subsonic axial-flow compressor rotor of Northwestern Polytechnical University, a reliable numerical simulation method was presented, and then axisymmetric contouring optimization for the casing under the condition of peak efficiency was conducted with the module DESIGN/3D in software package NUMECA, and the optimal rotor was obtained finally. The optimal rotor pushed the tip clearance leakage vortex away from the suction side at the leading edge of the blade. Although this led to an increase of the magnitude of leakage vortex and flow loss at the first 30% axial chord, the magnitude of leakage vortex and flow loss were greatly reduced at the last 70% axial chord of the blade, thus reducing the total loss, and increasing the peak efficiency and absolute total pressure at the outlet. The efficiency of the optimal rotor increases about 0.36% under the peak efficiency condition, which increases more under large mass flow rate condition, but under the near stall condition, the optimal rotor forms low velocity zone earlier at the blade tip area, leading to an earlier stall and making the stability margin of the optimal rotor smaller.
- subsonic axial-flow compressor rotor /
- axisymmetric contouring optimization /
- leakage vortex /
- flow loss /
- stability margin

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参考文献(18)

[1]	Lakshminarayana B.Methods of predicting the tip clearance effects in axial flow turbomachinery[J].Journal of Basic Engineering,1970,92(3):467-482.
[2]	Inoue M,Kuroumaru M,Fukuhara M.Behavior of tip leakage flow behind an axial flow compressor rotor[J].Journal of Engineering for Gas Turbines and Power,1986,108(1):7-13.
[3]	Inoue M,Kuroumaru M.Structure of tip clearance flow in an isolated axial compressor rotor[J].Journal of Turbomachinery,1989,111(3):250-256.
[4]	Furukawa M,Saiki K,Nagayoshi K.Effects of stream surface inclination on tip leakage flow fields in compressor rotor[J].Journal of Turbomachinery,1998,120(4):683- 694.
[5]	Furukawa M,Inoue M,Saiki K.The role of tip leakage vortex breakdown in compressor rotor aerodynamics[J].Journal of Turbomachinery,1999,121(3):469-480.
[6]	Bergner J,Kinzel M,Schiffer H.Short length-scale rotating stall inception in a transonic axial compressor criteria and mechanisms .ASME Paper GT-2006-90209,2006.
[7]	聂超群,桂幸民,于清,等.跨音速压气机近失速状态的非定常特征[J].工程热物理学报,1999,20(2):171-175. NIE Chaoqun,GUI Xingmin,YU Qing,et al.Unsteady flow behavior of near-stall states in a transonic axial compressor[J].Journal of Engineering Thermophysics,1999,20(2):171-175.(in Chinese)
[8]	贾希诚,王正明.叶轮机械中间隙流与通道二次流相互作用的数值研究[J].航空动力学报,2002,17(4):399-403. JIA Xicheng,WANG Zhengming.Numerical study of interaction between clearance flow and passage secondary flow in turbomachinery[J].Journal of Aerospace Power,2002,17(4):399-403.(in Chinese)
[9]	Chen G T,Greitzer E M,Tan C S,et al.Similarity analysis of compressor tip clearance flow structures .ASME Paper GT-1990-153,1990.
[10]	Kang S,Hirsch C.Experimental study on the three dimensional flow within a compressor cascade with tip clearance:Part Ⅱ the tip leakage vortex[J].Journal of Turbomachinery,1993,115(3):444-452.
[11]	Denton J D.Loss mechanisms in turbomachines[J].Journal of Turbomachinery,1993,115(4):621-655.
[12]	SHAO Weiwei,JI Lucheng,CHENG Ronghui.Basic analysis of tip leakage mixing loss .ASME Paper GT-2007-27616,2007.
[13]	Chunill H,Douglas C D,Aspi R W.Role of tip-leakage vortices and passage shock in stall inception in a swept transonic compressor rotor .ASME Paper GT-2004-53867,2004.
[14]	卢新根.轴流压气机内部流动失稳及其被动控制策略研究 .西安:西北工业大学,2007. LU Xingen.Flow instability and its passive control strategies in axial-flow compressor .Xian:Northwestern Polytechnical University,2007.(in Chinese)
[15]	Shabbir A,Celestina M L,Adamczyk J J,et al.The effect of hub leakage on 2 high speed axial flow compressor rotors .ASME Paper GT-1997-346,1997.
[16]	Khalid S A,Khalsa A S,Waitz I A,et al.Endwall blockage in axial compressors[J].Journal of Turbomachinery, 1999,121(3):499-509.
[17]	Georg K,Christian C,Eberhard N.Rotor casing contouring in high pressure stages of heavy duty gas turbine compressors with large tip clearance heights .ASME Paper GT-2009-59626,2009.
[18]	Georg K,Christian V,Eberhard N.Theory and application of axisymmetric endwall contouring for compressors .ASME Paper GT-2011-45624,2011.