低雷诺数下离心压气机性能及流动影响的数值研究

霍磊; 刘火星

低雷诺数下离心压气机性能及流动影响的数值研究

霍磊,
刘火星

北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室, 北京 100191

基金项目: 国家自然科学基金(51106004)

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出版历程
- 收稿日期: 2012-10-15
- 刊出日期: 2013-04-28

Numerical analysis of centrifugal compressor performance and flow at low Reynolds number

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and astronautics, Beijing 100191, China

摘要

摘要: 对高空低雷诺数条件下低压离心压气机进行了全三维数值模拟,分析了雷诺数对其内部流场的影响.结果表明:随着雷诺数降低,离心压气机的效率、裕度和流通能力下降;影响叶片表面负荷分布,使得转子叶片的做功能力下降;叶片前缘分离区范围增大,二次流增强,分流叶片叶尖泄漏损失增大,主叶片吸力面通道的低速区明显增大,起始位置也向前移动,对展向的影响区域也随之增加.
- 雷诺数 /
- 离心压气机 /
- 裕度 /
- 负荷分布 /
- 二次流
Abstract: Three-dimensional numerical simulation was conducted for a low pressure centrifugal compressor at low Reynolds number.Influence of Reynolds number on the flow-field was analyzed.The results show that, the efficiency,rotating stall margin and flow capacity reduce with the decrease of Reynolds number.Change of the blade loading distribution reduces the working capability of the compressor.In the flow-field,the leading-edge separation is more obvious and the secondary flow is encouraged.Tip leakage losses of the splitter blade increases.The low velocity flow area near the suction surface of blade obviously increases and its beginning location also moves forward.These will also enhance the influence on the span-wise region.
- Reynolds number /
- centrifugal compressor /
- rotating stall marginr /
- load distribution /
- secondary flow

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参考文献(15)

[1]	王大勇,李悦霖.高空长航时无人侦察机关键技术[J].飞航导弹,2009(11):31-35. WANG Dayong,LI Yuelin.Key technology of high-altitude long-endurance UAV[J].Winged Missiles Journal,2009(11):31-35.(in Chinese)
[2]	曹秋生,张会军.高空长航时无人机的发展特点及技术难点探讨[J].中国电子科学研究院学报,2008,3(1):9-13. CAO Qiusheng,ZHANG Huijun.Characteristics of HALE UAVs in development and discussion of existing technical difficulties[J].Journal of China Academy of Elecronics and Information Technology,2008,3(1):9-13.(in Chinese)
[3]	屠秋野,陈玉春,苏三买,等.雷诺数对高空长航时无人机发动机调节计划和性能影响[J].推进技术,2005,26(2):125-128. TU Qiuye,CHEN Yuchun,SU Sanmai,et al.Effects of Reynolds number on control schedule and performance of HALE engine[J].Journal of Propulsion Technology,2005,26(2):125-128.(in Chinese)
[4]	Wassell A B.Reynolds number effects in axial compressors[J].ASME Journal of Engineering for Gas Turbines and Power,1968,90(2):149-156.
[5]	Balje O E.A study of Reynolds number effects in turbomachines[J].Journal of Engineering for Power,1964,86(3):227-235.
[6]	王英锋,胡骏.雷诺数对轴流压气机稳定性的影响[J].航空动力学报,2004,19(1):69-73. WANG Yingfeng,HU Jun.The effects of Reynolds number on the stability of axial compressors[J].Journal of Aerospace Power,2004,19(1):69-73.(in Chinese)
[7]	肖洪,吴虎,廉筱纯.雷诺数对涡扇发动机性能及稳定性影响[J].航空动力学报,2005,20(3):394-398. XIAO Hong,WU Hu,LIAN Xiaochun.Reynolds number effects on performance and aerodynamic stabilities of the turbofan engines[J].Journal of Aerospace Power,2005,20(3):394-398.(in Chinese)
[8]	刘太秋,黄洪波,杜辉.压气机低雷诺数叶型设计技术研究[J].航空发动机,2006,32(2):26-30. LIU Taiqiu,HUANG Hongbo,DU Hui.Compressor airfoil design for low Reynolds number[J].Aeroengine,2006,32(2):26-30.(in Chinese)
[9]	凌代军,姜正礼,于进涛,等.低雷诺数平面叶栅试验方法研究[J].燃气涡轮试验与研究,2011,24(2):1-6. LING Daijun,JIANG Zhengli,YU Jintao,et al.Experimental investigation methods on low Reynolds number plane cascade[J].Gas Turbine Experiment and Research,2011,24(2):1-6.(in Chinese)
[10]	Wiesner F J.A new appraisal of Reynolds number effects on centrifugal compressor performance[J].ASME Journal of Engineering for Power,1979,101(3):384-396.
[11]	Casey M V.The effects of Reynolds number on the efficiency of centrifugal compressor stages[J].ASME Journal of Engineering for Gas Turbines and Power,1985,107(2):541-548.
[12]	Strub R A,Bonciani L,Borer C L,et al.Influence of the Reynolds number on the performance of centrifugal compressors[J].ASME Journal of Turbomachinery,1987,109(4):541-544.
[13]	Gulich J F.Effect of reynolds number and surface roughness on the efficiency of centrifugal pumps[J].ASME Journal of Fluids Engineering,2003,125(4):671-679.
[14]	薄东.高空下低雷诺数对压气机特性的影响分析 [D].北京:北京航空航天大学,2010. BO Dong.The effects of low Reynolds number on the characteristics of compressor at high-altitude [D].Beijing:Beijing University of Aeronautics and Astronautics,2010.(in Chinese)
[15]	徐斌,尧辉,薄东,等.高空活塞发动机2级涡轮增压系统匹配分析[J].航空发动机,2010,36(1):8-13. XU Bin,YAO Hui,BO Dong,et al.Matching analysis of two stage turbocharging system of high altitude piston engine[J].Aeroengine,2010,36(1):8-13.(in Chinese)