Volume 41 Issue 3
Mar.  2026
Turn off MathJax
Article Contents
FENG Guomiao, LI Guoqing, BAI Xiaohui, et al. Film cooling characteristics and loss mechanism of combined construct with expansive main hole and contractive secondary holes[J]. Journal of Aerospace Power, 2026, 41(3):20240770 doi: 10.13224/j.cnki.jasp.20240770
Citation: FENG Guomiao, LI Guoqing, BAI Xiaohui, et al. Film cooling characteristics and loss mechanism of combined construct with expansive main hole and contractive secondary holes[J]. Journal of Aerospace Power, 2026, 41(3):20240770 doi: 10.13224/j.cnki.jasp.20240770

Film cooling characteristics and loss mechanism of combined construct with expansive main hole and contractive secondary holes

doi: 10.13224/j.cnki.jasp.20240770
  • Received Date: 2024-11-14
    Available Online: 2025-10-24
  • Film cooling characteristics and aerodynamic loss mechanism were numerically simulated under a mainstream Mach number of 0.6. Three-cylindrical combination holes, variable cross-section cylin-drical combination holes and crescent combination holes were compared at the blowing ratio varying from 0.5 to 2.0. In a crescent combination holes with expansive main hole and contractive secondary holes, main-stream penetration was prevented in the mid-expansion hole. As for the side-contraction holes, the anti-kidney vortex was promoted due to acceleration. The mixing structure was changed due to different pre-ssure gradients of holes. When the blowing ratio was 1.5 and 2.0, compared with three-cylindrical combi-nation holes, the film cooling effectiveness increased by 17.8% and 29.7%, respectively, and the mixing pressure loss due to film cooling declined by 51% and 43%, respectively, in crescent combination holes.

     

  • loading
  • [1]
    FRIC T F, ROSHKO A. Vortical structure in the wake of a transverse jet[J]. Journal of Fluid Mechanics, 1994, 279: 1-47. doi: 10.1017/S0022112094003800
    [2]
    ZHANG Jingzhou, ZHANG Shengchang, WANG Chunhua, et al. Recent advances in film cooling enhancement: a review[J]. Chinese Journal of Aeronautics, 2020, 33(4): 1119-1136. doi: 10.1016/j.cja.2019.12.023
    [3]
    GRITSCH M, COLBAN W, SCHÄR H, et al. Effect of hole geometry on the thermal performance of fan-shaped film cooling holes[J]. Journal of Turbomachinery, 2005, 127(4): 718-725. doi: 10.1115/1.2019315
    [4]
    付仲议, 朱惠人, 刘聪, 等. 涡轮导叶压力面簸箕形气膜孔冷却特性实验研究[J]. 推进技术, 2016, 37(12): 2303-2311. FU Zhongyi, ZHU Huiren, LIU Cong, et al. Experimental study of film cooling characteristics for dust-pan shaped holes on pressure side in a turbine guide vane[J]. Journal of Propulsion Technology, 2016, 37(12): 2303-2311. (in Chinese

    FU Zhongyi, ZHU Huiren, LIU Cong, et al. Experimental study of film cooling characteristics for dust-pan shaped holes on pressure side in a turbine guide vane[J]. Journal of Propulsion Technology, 2016, 37(12): 2303-2311. (in Chinese)
    [5]
    韩昌. 燃气轮机高温透平气膜冷却的孔型机理及叶栅特性研究[D]. 北京: 清华大学, 2014. HAN Chang. Research on film-hole mechanism and cascade characteristics of gas turbine film cooling[D]. Beijing: Tsinghua University, 2014. (in Chinese

    HAN Chang. Research on film-hole mechanism and cascade characteristics of gas turbine film cooling[D]. Beijing: Tsinghua University, 2014. (in Chinese)
    [6]
    DAI Ping, LIN Feng. Numerical simulation on film cooling effectiveness for different shaped holes[J]. Proceedings of the Chinese Society of Electrical Engineering, 2010, 30(14): 102-108.
    [7]
    KUSTERER K, ELYAS A, BOHN D, et al. Film cooling effectiveness comparison between shaped- and double jet film cooling holes in a row arrangement[R]. ASME Paper GT2010-22604, 2010.
    [8]
    KUSTERER K, ELYAS A, BOHN D, et al. Double-jet film-cooling for highly efficient film-cooling with low blowing ratios[R]. ASME Paper GT2008-50073, 2008.
    [9]
    李润东, 李明春, 贺业光, 等. 射流角度对姊妹孔气膜冷却效果影响实验研究[J]. 推进技术, 2020, 41(8): 1765-1772. LI Rundong, LI Mingchun, HE Yeguang, et al. Experimental study on effects of injection angles on film cooling performance of sister holes[J]. Journal of Propulsion Technology, 2020, 41(8): 1765-1772. (in Chinese

    LI Rundong, LI Mingchun, HE Yeguang, et al. Experimental study on effects of injection angles on film cooling performance of sister holes[J]. Journal of Propulsion Technology, 2020, 41(8): 1765-1772. (in Chinese)
    [10]
    TAEIBI R M, JAVADI A, JAVADI K, et al. A new approach to improve film cooling effectiveness, using combined jets[R]. ASME Paper GT2003TS-071, 2003.
    [11]
    HARTSEL J. Prediction of effects of mass-transfer cooling on the blade-row efficiency of turbine airfoils[R]. AIAA 1972-11, 1972.
    [12]
    姚玉, 张靖周, 何飞, 等. 涡轮叶片吸力面上收敛缝形孔气膜冷却对叶栅气动损失的影响[J]. 航空学报, 2010, 31(7): 1312-1317. YAO Yu, ZHANG Jingzhou, HE Fei, et al. Numerical investigation on aerodynamic loss of turbine cascade with converging slot hole film cooling at suction surface[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(7): 1312-1317. (in Chinese

    YAO Yu, ZHANG Jingzhou, HE Fei, et al. Numerical investigation on aerodynamic loss of turbine cascade with converging slot hole film cooling at suction surface[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(7): 1312-1317. (in Chinese)
    [13]
    LIM C H, PULLAN G, IRELAND P. Influence of film cooling hole angles and geometries on aerodynamic loss and net heat flux reduction[J]. Journal of Turbomachinery, 2013, 135(5): 051019. doi: 10.1115/1.4023088
    [14]
    SARGISON J E, GUO S M, OLDFIELD M L G, et al. A converging slot-hole film-cooling geometry: Part 1 low-speed flat-plate heat transfer and loss[J]. Journal of Turbomachinery, 2002, 124(3): 453-460. doi: 10.1115/1.1459735
    [15]
    刘存良, 朱惠人, 白江涛. 收缩-扩张形气膜孔提高气膜冷却效率的机理研究[J]. 航空动力学报, 2008, 23(4): 598-604. LIU Cunliang, ZHU Huiren, BAI Jiangtao. Study on the physics of film-cooling effectiveness enhancement by the converging-expanding hole[J]. Journal of Aerospace Power, 2008, 23(4): 598-604. (in Chinese

    LIU Cunliang, ZHU Huiren, BAI Jiangtao. Study on the physics of film-cooling effectiveness enhancement by the converging-expanding hole[J]. Journal of Aerospace Power, 2008, 23(4): 598-604. (in Chinese)
    [16]
    康忠, 李国庆, 张深, 等. 收缩型双射流孔气膜冷却特性与损失机理[J]. 航空动力学报, 2023, 38(2): 335-343. KANG Zhong, LI Guoqing, ZHANG Shen, et al. Film cooling characteristics and loss mechanism of contracted double-jet hole[J]. Journal of Aerospace Power, 2023, 38(2): 335-343. (in Chinese

    KANG Zhong, LI Guoqing, ZHANG Shen, et al. Film cooling characteristics and loss mechanism of contracted double-jet hole[J]. Journal of Aerospace Power, 2023, 38(2): 335-343. (in Chinese)
    [17]
    张振, 陈子聿, 苏欣荣, 等. 基于孔内流动机理的气膜冷却界面模型[J]. 工程热物理学报, 2021, 42(7): 1692-1699. ZHANG Zhen, CHEN Ziyu, SU Xinrong, et al. In-hole flow based interface model for film cooling[J]. Journal of Engineering Thermophysics, 2021, 42(7): 1692-1699. (in Chinese

    ZHANG Zhen, CHEN Ziyu, SU Xinrong, et al. In-hole flow based interface model for film cooling[J]. Journal of Engineering Thermophysics, 2021, 42(7): 1692-1699. (in Chinese)
    [18]
    高扬, 刘建军, 安柏涛. 主流马赫数对不同气膜孔结构冷却效果及气动损失影响研究[J]. 燃气轮机技术, 2015, 28(2): 15-20, 72. GAO Yang, LIU Jianjun, AN Baitao. Influence of mainstream Mach number on cooling effectiveness and aerodynamic losses of different film cooling configurations[J]. Gas Turbine Technology, 2015, 28(2): 15-20, 72. (in Chinese

    GAO Yang, LIU Jianjun, AN Baitao. Influence of mainstream Mach number on cooling effectiveness and aerodynamic losses of different film cooling configurations[J]. Gas Turbine Technology, 2015, 28(2): 15-20, 72. (in Chinese)
    [19]
    LIM C H, PULLAN G, NORTHALL J. Estimating the loss associated with film cooling for a turbine stage[R]. ASME Paper GT2010-22327, 2010.
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Article Metrics

    Article views (701) PDF downloads(53) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return