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跨声速压气机动叶平面叶栅实验

高宇 钟兢军 李晓东 杨凌

高宇, 钟兢军, 李晓东, 杨凌. 跨声速压气机动叶平面叶栅实验[J]. 航空动力学报, 2016, 31(5): 1178-1185. doi: 10.13224/j.cnki.jasp.2016.05.020
引用本文: 高宇, 钟兢军, 李晓东, 杨凌. 跨声速压气机动叶平面叶栅实验[J]. 航空动力学报, 2016, 31(5): 1178-1185. doi: 10.13224/j.cnki.jasp.2016.05.020
GAO Yu, ZHONG Jing-jun, LI Xiao-dong, YANG Ling. Experiment on rotor plane cascade of transonic compressor[J]. Journal of Aerospace Power, 2016, 31(5): 1178-1185. doi: 10.13224/j.cnki.jasp.2016.05.020
Citation: GAO Yu, ZHONG Jing-jun, LI Xiao-dong, YANG Ling. Experiment on rotor plane cascade of transonic compressor[J]. Journal of Aerospace Power, 2016, 31(5): 1178-1185. doi: 10.13224/j.cnki.jasp.2016.05.020

跨声速压气机动叶平面叶栅实验

doi: 10.13224/j.cnki.jasp.2016.05.020
基金项目: 

辽宁省高等学校创新团队项目(LT2015004)

辽宁省自然科学基金(2015020636)

国家自然科学基金(51506020)

中央高校基本科研业务费专项资金(3132016205)

国家自然科学基金重点项目(51436002)

详细信息
    作者简介:

    高宇(1989-),女,辽宁盘锦人,博士生,主要从事发动机气动热力学研究.

  • 中图分类号: V235.1

Experiment on rotor plane cascade of transonic compressor

  • 摘要: 对某跨声速压气机动叶根部叶型平面叶栅流场在不同冲角和进口等熵马赫数下进行了详细的测量,得到了冲角特性曲线和叶片表面及端壁静压.结果表明:负冲角及零冲角时,叶栅出口总压损失系数随进口等熵马赫数增加变化不大,而在正冲角时变化较大.相同进口等熵马赫数下,负冲角和零冲角时,叶片负荷较高;正冲角时,由于气流分离严重,叶片负荷下降,叶栅出口总压损失系数升高.随冲角由负冲角向正冲角增加,气流落后角逐渐增大,叶栅出口总压损失系数先减小后增大,最小值为0.034.冲角相同时,随进口等熵马赫数增加,叶栅出口总压损失系数总体呈增加趋势.

     

  • [1] ZHANG Yanfeng,Mahallati A,Benner M.Experiment and numerical investigation of corner stall in a highly-loaded compressor cascade[R].ASME Paper GT2014-27204,2014.
    [2] Hilgenfeld L,Cardamone P,Fottner L.Boundary layer investigations on a highly loaded transonic compressor cascade with shock/laminar boundary layer interactions[J].Proceedings of the Institution of Mechanical Engineers:Part A Journal of Power and Energy,2003,217(4):349-356.
    [3] Iseler J,Hilgenfeld L,Pfitzner M.Investigations of the boundary layer on a highly loaded compressor cascade with wake-induced transition[R].ASME Paper GT2000-90665,2000.
    [4] 邓宝洋,桂幸民,袁巍,等.高负荷跨音压气机转子的间隙效应[J].北京航空航天大学学报,2002,28(4):387-390. DENG Baoyang,GUI Xingmin,YUAN Wei,et al.Experimental investigation on high-loading transonic compressor rotor[J].Journal of Beijing University of Aeronautics and Astronautics,2002,28(4):387-390.(in Chinese)
    [5] 李泯江,祁祎,邓宝洋,等.高负荷跨音压气机转子ATS-3气动设计[J].航空动力学报,2002,17(2):183-187. LI Minjiang,QI Wei,DENG Baoyang et al.Aerodynamic design of high load transonic compressor stage[J].Journal of Aerospace Power,2002,17(2):183-187.(in Chinese)
    [6] 桂幸民,王同庆,于清,等.跨音压气机转子叶尖流场试验与分析[J].工程热物理学报,1998,19(5):553-558. GUI Xingmin,WANG Tongqing,YU Qing,et al.Investigation on the tip clearance flow field in a transonic compressor rotor[J].Journal of Engineering Thermophysics,1998,19(5):553-558.(in Chinese)
    [7] Roehle I,Guevel A L,Fradin C.3D-shock visualisation in a transonic compressor rotor[J].Optics and Laser Technology,1999,31(1):67-73.
    [8] Biollo R,Benini E.Recent advances in transonic axial compressor aerodynamics[J].Progress in Aerospace Sciences,2013,56:1-18.
    [9] 于兰兰.高压压气机平面叶栅实验与数值计算[D].南京:南京航空航天大学,2008. YU Lanlan.Research on experiment and numerical simulation of cascades for one high-pressure compressor[D].Nanjing University of Aeronautics and Astromautics,2008.(in Chinese)
    [10] 赵鹏程,刘波,宣扬,等.基于遗传算法的压气机叶型优化设计[J].航空计算技术,2011,41(6):12-15. ZHAO Pengcheng,LIU Bo,XUAN Yang,et al.Optimization for compressor airfoil based on genetic algorithm[J].Aeronautical Computing Technique,2011,41(6):12-15.(in Chinese)
    [11] 陈忠良,姜斌,郑群,等.高亚声速轴流压气机的优化叶型研究[J].航空动力学报,2015,30(4):891-900. CHEN Zhongliang,JIANG Bin,ZHENG Qun,et al.Studies on blade profile optimization of high subsonic axial flow compressor[J].Journal of Aerospace Power,2015,30(4):891-900.(in Chinese)
    [12] 刘波,李俊.吸附式压气机叶型优化设计[J].航空发动机,2012,38(6):1-4,19. LIU Bo,LI Jun.Optimization for aspirated compressor airfoil[J].Aeroengine,2012,38(6):1-4,19.(in Chinese)
    [13] 凌代军,王晖,马昌友.低雷诺数亚声速扩压平面叶栅实验[J].航空动力学报,2013,28(1):171-179. LING Daijun,WANG Hui,MA Changyou.Subsonic compressor plane cascade experiment at low Reynolds number[J].Journal of Aerospace Power,2013,28(1):171-179.(in Chinese)
    [14] Zachos P K,Grech N,Charnley B,et al.Experimental and numerical investigation of a compressor cascade at highly negtive incidence[J].Engineering Applications of Computational Fluid Mechanics,2011,5(1):26-36.
    [15] Lian Y,Liou M S.Multi-objective optimization of transonic compressor blade using evolutionary algorithm[J].Journal of Propulsion and Power,2005,21(6):979-987.
    [16] Lotfl O,Teixeira J A,Ivey P C,et al.Aerodynamic optimization of industrial fan blade cascades[R].ASME Paper GT2005-68385,2005.
    [17] Carstens V,Schmitt S.Comparison of theoretical and experimental data for an oscillating transonic compressor cascade[R].ASME Paper GT 99-408,1999.
    [18] Drela M,Youngren H.A user's guide to MISES 2.63[M].Cambridge,Massachusetts:Massachusetts Institute of Technology Press,2008.
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出版历程
  • 收稿日期:  2015-10-26
  • 刊出日期:  2016-05-28

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