考虑静叶封严泄漏对压气机端区影响的三维叶片优化

何柳; 蒋洪德

doi:10.13224/j.cnki.jasp.2014.06.030

考虑静叶封严泄漏对压气机端区影响的三维叶片优化

doi: 10.13224/j.cnki.jasp.2014.06.030

何柳,
蒋洪德

清华大学热能工程系, 北京 100084

详细信息

作者简介:
何柳（1982- ），男，山东莱州人，博士，主要从事叶轮机械气动设计和数值优化研究.

中图分类号: V232.4
计量
- 文章访问数: 1383
- HTML浏览量: 4
- PDF量: 862
- 被引次数: 0
出版历程
- 收稿日期: 2013-03-18
- 刊出日期: 2014-06-28

Three-dimensional blade optimization considering effect of stator seal leakage on end-wall in compressor

Department of Thermal Engineering, Tsinghua University, Beijing 100084, China

摘要

摘要: 鉴于静叶叶根封严蓖齿间隙的泄漏对压气机端区所产生的不利影响，取某带静叶封严结构的双级轴流压气机为研究对象，采用遗传算法对其进行了气动数值优化.优化自变量为所选双级轴流压气机的后面级静叶近轮毂区叶型的安装角和前缘角，优化目标为极大化该双级轴流压气机的等熵效率.优化后，双级轴流压气机设计点的等熵效率提高了约0.2个百分点.所优化的静叶近轮毂处呈现出了明显的端弯效果.双级轴流压气机性能改善的主要原因是，通过对后面级静叶根部叶型的调整，使其端区来流的攻角值落在了该叶型的最优设计攻角的附近.
- 重型燃气轮机 /
- 轴流压气机 /
- 封严蓖齿 /
- 气动数值优化 /
- 端弯叶片
Abstract: Considering the negative effect of the leakage of the labyrinth seal gap close to the stator root on the end-wall in the compressor, a two-stage axial compressor of the stator seal structure was chosen as the research subject. Genetic algorithm (GA) was applied to conduct numerical aerodynamic optimization of this two-stage axial compressor. The optimization variables included the stagger angles and the leading-edge angles of the airfoils close to the hub of the rear-stage stator, and the optimization object was to achieve the maximum isentropic efficiency of the two-stage axial compressor. After the optimization, the isentropic efficiency of the two-stage axial compressor in the design point increased by 0.2 percentage points, and the rear-stage stator obviously showed the end-bend blading close to the hub. The main reason for the improvement of the two-stage axial compressor performance is that after the root airfoils of the rear-stage stator have been modified by the optimization, the incidences of the upstream flow close to the end-wall are located close to the optimal design incidences of these airfoils.
- heavy-duty gas turbine /
- axial compressor /
- labyrinth seal /
- numerical aerodynamic optimization /
- end-bend blade

HTML

参考文献(15)

[1]	Wasserbauer C A,Weaver H F,Senyitko R G.NASA low-speed axial compressor for fundamental research.NASA TM 4635,1995.
[2]	Heidegger N J,Hall E J,Delaney R A.Parameterized study of high-speed compressor seal cavity flow.AIAA 96-2807,1996.
[3]	Shabbir A,Celestina M L,Adamczyk J J,et al.The effect of hub leakage flow on two high speed axial flow compressor rotors.ASME Paper 97-GT-346,1997.
[4]	Rosic B,Denton J D,Curtis E M.The influence of shroud and cavity geometry on turbine performance:an experimental and computational study:Part 1 shroud geometry.ASME Paper GT2007-27769,2007.
[5]	Naylor E,Montomoli F,Hodson H,et al.Numerical modeling of cavity in multistage axial compressors.ISABE-2009-1186,2009.
[6]	纪国剑.航空发动机典型蓖齿封严泄漏特性的数值和实验研究.南京:南京航空航天大学,2008. JI Guojian.Numerical and experiment investigation of sealing characteristics on typical labyrinth seals in aeroengine.Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[7]	Wellborn S R,Tolchinsky I,Okiishi T H.Modeling shrouded stator cavity flows in axial-flow compressors[J].Journal of Turbomachinery,2000,122(1):55-61.
[8]	Wellborn S R,Okiishi T H.The influence of shrouded stator cavity flows on multistage compressor performance[J].Journal of Turbomachinery,1999,121(2):486-498.
[9]	Lejambre C R,Zacharias R M,Biederman B P,et al.Development and application of a multistage Navier-Stokes flow solver:Part Ⅱ application to a high pressure compressor design[J].Journal of Turbomachinery,1998,120(2):215-223.(in Chinese)
[10]	马文生,禄堃,顾春伟.压气机静叶气封几何优化与流动分析[J].工程热物理学报,2009,30(8):1288-1290. MA Wensheng,LU Kun,GU Chunwei.Compressor stator seal cavity geometry optimization and flow analysis[J].Journal of Engineering Thermophysics,2009,30(8):1288-1290.(in Chinese)
[11]	Denton J D.The calculation of three-dimensional viscous flow through multistage turbomachines[J].Journal of Turbomachinery,1992,114(1):18-26.
[12]	Deb K.An efficient constraint handling method for genetic algorithms[J].Computer Methods in Applied Mechanics and Engineering,2000,186(2):311-338.
[13]	何柳.基于气动变量参数化的轴流压气机三维气动数值优化.北京:北京航空航天大学,2011. HE Liu.Three-dimensional aerodynamic optimization for axial-flow compressors based upon the aerodynamic parameters.Beijing:Beijing University of Aeronautics and Astronautics,2011.(in Chinese)
[14]	彭泽琰,刘刚.航空燃气轮机原理:上册[M].北京:国防工业出版社,2001.
[15]	NASA.轴流压气机气动设计[M].秦鹏,译.北京:国防工业出版社,1975.