氦氙离心压气机叶顶间隙形态对气动性能的影响

王国杰; 刘学峥; 高杰

doi:10.13224/j.cnki.jasp.2020.06.021

氦氙离心压气机叶顶间隙形态对气动性能的影响

doi: 10.13224/j.cnki.jasp.2020.06.021

基金项目: 国家自然科学基金（51979052,51779051）；航空动力基金（6141B09050392）；国家科技重大专项（2017-Ⅲ-0010-0036）

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出版历程
- 收稿日期: 2019-11-07
- 刊出日期: 2020-06-28

Influence of form of tip gap on aerodynamic performance of centrifugal compressor using mixture of helium and xenon

College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,China

摘要

摘要: 针对氦氙混合工质离心压气机,通过数值模拟研究了叶顶径向间隙与轴向间隙高度的独立变化和不同间隙形态分布对压气机内部流场流动状态和性能产生的影响,总结氦氙混合工质离心压气机叶顶间隙不同高度和形态分布对其性能的影响规律。结果表明:叶顶间隙高度的增大会降低氦氙离心压气机的近喘振工况和设计工况效率。单独增加径向间隙(01~04 mm)使堵塞流量范围拓宽了388%,堵塞工况性能有所改善;单独增大轴向间隙对堵塞工况性能则无影响。渐缩式叶顶间隙分布使离心压气机效率较均匀分布提高023%。
- 氦氙混合工质 /
- 离心压气机 /
- 叶顶间隙 /
- 流动特性 /
- 气动性能
Abstract: The tip leakage flow directly affects the performance of the centrifugal compressor. The influence of the independent change of the radial and axial tip gaps and the influence of the distribution of the tip gap on the centrifugal compressor internal flow field and performance were studied by numerical simulation. The influence law of different height and shape of the centrifugal compressor tip gap on its performance was summarized. Result showed that increasing the centrifugal compressor gap would reduce the efficiency at near surge condition and design condition; increasing the radial gap solely, from 01 mm to 04 mm, could broaden the choke mass flow range by 388% and improve the performance of the centrifugal compressor near blockage condition; increasing the axial gap solely had no effect on the performance at near choke condition. The shrinking distribution of tip gap increased the efficiency of the centrifugal compressor by 023%.
- mixture of helium and xenon /
- centrifugal compressor /
- tip gap /
- ,flow characteristics /
- aerodynamic performance

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参考文献(18)

[1]	田志涛,郑群,姜斌.氦氙混合离心压气机设计与分析［J］.风机技术,2018,60(3):14-19. TIAN Zhitao,ZHENG Qun,JIANG Bin.Design and analysis of helium and xenon binary mixture gas centrifugal compressor［J］.Chinese Journal of Turbomachinery,2018,60(3):14-19.(in Chinese)
[2]	SKOCH G.Experimental investigation of centrifugal compressor stabilization techniques［J］.Journal of Turbomachinery,2003,125(4):765-776.
[3]	HAH C,KRAIN H.Secondary flows and vortex motion in a high-efficiency backswept impeller at design and off-design conditions［J］.Journal of Turbomachinery,1990,112(1):7-13.
[4]	MOORE J,MOORE J G.Secondary flow,separation and losses in the NACA 48-inch centrifugal impeller at design and off-design conditions［R］.ASME Paper 88-GT-101,1988.
[5]	SENOO Y.Mechanics on the tip clearance loss of impeller blades［J］.Journal of Turbomachinery,1991,113(4):680-685.
[6]	SENOO Y,ISHIDA M.Deterioration of compressor performance due to tip clearance of centrifugal impellers［J］.Transactions of the Japan Society of Mechanical Engineers,1987,109(1):55-61.
[7]	ISHIDA M,UEKI H,SENOO Y.Effect of blade tip configuration on tip clearance loss of a centrifugal impeller［J］.Transactions of the Japan Society of Mechanical Engineers,1990,112(1):14-18.
[8]	SCHLEER M,SONG S J,ABHARI A R S.Clearance effects on the onset of instability in a centrifugal compressor［J］.Journal of Turbomachinery,2006,130(3):993-1003.
[9]	SCHLEER M,ABHAEI R S.Clearance effects on the evolution of the flow in the vaneless diffuser of a centrifugal compressor at part load condition［J］.Journal of Turbomachinery,2008,130(3):031009.1-031009.9.
[10]	YAMADA K,TAMAGAWA Y,FUKUSHHIMA H,et al.Comparative study on tip clearance flow fields in two types of transonic centrifugal compressor impeller with splitter blades［R］.ASME Paper GT2010-23345,2010.
[11]	张楚华,王宝潼,栾辉宝,等.叶顶间隙对离心叶轮气动性能影响研究［J］.流体机械,2006,34(12):13-16. ZHANG Chuhua,WANG Baotong,LUAN Huibao,et al.Study on influence of tip clearance on aerodynamic performance of centrifugal impeller［J］.Fluid Machinery,2006,34(12):13-16.(in Chinese)
[12]	MASHIMO T,WATANABE I,ARIGA I.Effects of fluid leakage on performance of a centrifugal compressor［J］.Journal of Engineering for Gas Turbines and Power,1979,101(3):337-342.
[13]	楚武利,刘志伟.半开式离心叶轮间隙流动的实验研究［J］.流体机械,1998(10):3-6. CHU Wuli,LIU Zhiwei.Experimental study on clearance flow of semi open centrifugal impeller［J］.Fluid Machinery,1998(10):3-6.(in Chinese)
[14]	JAATINEN A,TURUNEN-SAARESTI T,GRNMAN A,et al.Experimental study of the effect of the tip clearance to the diffuser flow field and stage performance of a centrifugal compressor［R］.ASME Paper GT2012-68445,2012.
[15]	贾希诚,王正明,蔡睿贤.叶轮机械中叶顶间隙形态对气动性能影响的数值研究［J］.工程热物理学报,2001,22(4):431-434. JIA Xicheng,WANG Zhengming,CAI Ruixian.Numerical investigation of the effects of the tip gap shapes on aerodynamic performance in turbomachinery［J］.Journal of Engineering Thermophysics,2001,22(4):431-434.(in Chinese)
[16]	WEI C,GRATES D R,THERMANN H,et al.Numerical investigation of the influence of the tip clearance on wake formation inside a radial impeller［R］.ASME Paper GT2003-38279,2003.
[17]	冀国锋,桂幸民.轴流/离心压气机叶片通用任意中弧造型设计方法［J］.航空动力学报,2009,24(1):150-156. JI Guofeng,GUI Xingmin.A blading design method for axial/centrifugal compressor airfoils using arbitrary camber lines［J］.Journal of Aerospace Power,2009,24(1):150-156.(in Chinese)
[18]	冀国锋,殷明霞,桂幸民.某小型离心压气机气动设计［J］.航空动力学报,2010,25(3):557-564. JI Guofeng,YIN Mingxia,GUI Xingmin.Aerodynamic design of a small centrifugal compressor［J］.Journal of Aerospace Power,2010,25(3):557-564.(in Chinese)