回流器叶片中型线对离心压缩机性能影响的研究Numerical Study on the Effect of Meanlines of Return Channel Blades on Performance of Centrifugal Compressor
宫武旗;李晶;张斌;邓俊杰;
GONG Wu-qi;LI Jing;ZHANG Bin;DENG Jun-jie;Xi'an Jiaotong University;
摘要(Abstract):
以某离心制冷压缩机首级模型为研究对象,通过数值计算对比了单圆弧中型线、CCR中型线(切向速度线性变化)和MMR中型线(角动量线性变化)3种回流器,研究了回流器中型线对压缩机级性能和流场的影响规律。数值计算结果表明,回流器中型线对压缩机级性能和流场影响显著。单圆弧中型线回流器压缩机级性能最优,CCR中型线回流器次之,MMR中型线回流器最低。其中,CCR和MMR中型线回流器压缩机级绝热效率峰值较单圆弧中型线回流器级分别降低1.2%和3%。在实际工程应用中,适当增加回流器前半段叶片载荷,能降低由于回流器尾缘载荷过大造成的流动分离损失。
With the first stage model of a centrifugal refrigerating compressor as the research object,the influence rules of the meanlines of return channel blades on the performance and flow field of compressor stages were studied by comparing the return channel blades using single arc meanline,CCR(Circumferential Component Reduction) and MMR(Moment of Momentum Reduction) meanlines,respectively.Numerical calculation results show that the blade meanlines have significant effects on the performance and flow field of the compressor stage. The performance of the return channel blades using single arc meanline was the best,followed by the CCR meanline,and the MMR meanline was the worst. Compared to the return channel blades using single arc meanline,the adiabatic efficiency of compressor stage in the blades with CCR and MMR meanlines at peak efficiency condition was 1.2% and 3%,respectively. In practical engineering applications,flow separation loss due to overload of the blade trailing edge can be reduced by increasing the load of blade leading edge properly.
关键词(KeyWords):
离心压缩机;制冷;回流器;中型线;数值分析
centrifugal compressor;refrigeration;return channel;blade meanline;numerical analysis
基金项目(Foundation): 国家自然科学基金资助项目(51236006)
作者(Authors):
宫武旗;李晶;张斌;邓俊杰;
GONG Wu-qi;LI Jing;ZHANG Bin;DENG Jun-jie;Xi'an Jiaotong University;
参考文献(References):
- [1]姚承范,朱营康,马林,等.回流器对离心压缩机级特性影响的试验研究[J].工程热物理学报,1994(15):46-49.
- [2]冀春俊,刘洋,武斌.回流器冲角对于压缩机模型级性能影响的研究[J].风机技术,2013(4):11-16.
- [3]赵锐,谢蓉,王晓放.离心压缩机小流量级回流器的优化分析[J].动力工程,2005(25):668-671.
- [4]Bera A,Singh DNK.Thickness and blade angle distribution for design of centrifugal compressor stage return channel vane[C].ASME 2015 Gas Turbine India Conference,Hyderabad,India,2015,GTINDIA 2015-1350:1-5.
- [5]Nishida Y,Kobayashi H,Nishida H,et al.Performance improvement of a return channel in a multistage c e n t r i f u g a l c o m p r e s s o r u s i n g m u l t i o b j e c t i v e optimization[J].Journal of Turbomachinery,2013,135(3):031026-1-8.
- [6]姚承范,朱营廉,马林,等.离心压缩机低喘回流器的设计[J].流体机械,1992(1):8-12.
- [7]Hildebrandt A.Aerodynamic optimisation of a centrifugal compressor return channel and U-turn with genetic algorithms[C].Proceeding of ASME Turbo Expo 2011,Vancouver,British Columbia,Canada,2011:1869-1880.
- [8]雷王兴.大转折角回流器流动特征和设计方法[D].南京:南京航空航天大学,2014.
- [9]何坤,袁新.离心压气机回流器三维气动优化设计[C].中国工程热物理学会热机气动热力学2009年学术会议,2009:403-406.
- [10]Bellis FD,Guidotti E,Rubino DT.Centrifugal compressors return channel optimization by means of advanced 3D CFD[C].ASME Turbo Expo 2015:Turbine Technical Conference and Exposition,Montreal,Canada,2015,GT2015-44143:1-9.
- [11]Japikse D.Centrifugal Compressor Design and Performance[M].Concepts ETI,1996.