Volume 40 Issue 3
Mar.  2025
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2025  >  40(3): 20230266
HE Yeguang, ZHANG Ming, ZHANG Deheng, et al. Experimental study on film cooling characteristics of U-shaped crater holes[J]. Journal of Aerospace Power, 2025, 40（3）：20230266 doi: 10.13224/j.cnki.jasp.20230266
Citation: HE Yeguang, ZHANG Ming, ZHANG Deheng, et al. Experimental study on film cooling characteristics of U-shaped crater holes[J]. Journal of Aerospace Power, 2025, 40（3）：20230266 doi: 10.13224/j.cnki.jasp.20230266
shu

Experimental study on film cooling characteristics of U-shaped crater holes

doi: 10.13224/j.cnki.jasp.20230266

  • College of Energy and Environment，Shenyang Aerospace University，Shenyang 110136，China

  • Received Date: 2023-04-21
    Available Online: 2024-10-12
    Abstract

  • Experimental study of U-shaped crater holes with depth and expansion angle on a flat plate using pressure sensitive paint technique was conducted to measure and compare the adiabatic film cooling efficiency of cylindrical holes and crater holes. The results showed that the cooling performance of the cratered hole structure was better than that of the cylindrical hole structure, while the cooling performance of the cratered hole structure with expansion angle was better than that of the depth crater hole structure. The average film cooling efficiency of the optimal depth crater hole (crater depth d=0.5D, blowing ratio M=2.0, D meant diameter of cylindrical hole) compared with the cylindrical was improved by nearly 800% in the region of X/D<5 (X meant the position in mainstream direction) and nearly 700% in the region of 5<X/D<14; the average film cooling efficiency of the optimal expansion angle crater hole (expansion angles α=30°, M=2.0) compared with the non-expansion crater hole was improved by nearly 180% in the region of X/D<5 and nearly 170% in the region of 5<X/D<14. The increased depth of the crater hole facilitated the expansion of the coolant on the wall surface; the expansion angle crater hole structure facilitated the expansion of the cooling jet coverage in the spreading and flow direction. The magnitude of the enhancement of the crater depth and expansion angle on the film cooling performance of the crater hole structure increased with the increasing blowing ratio.

     

    • FullText(HTML)
  • loading
    • References(23)
  • [1]
    谭艳青,姜东坡. 燃气轮机叶片冷却技术的发展[J]. 装备制造技术,2014(7): 208-210. TAN Yanqing,JIANG Dongpo. The development of cooling technology for gas turbine blade[J]. Equipment Manufacturing Technology,2014(7): 208-210. (in Chinese doi: 10.3969/j.issn.1672-545X.2014.07.075

    TAN Yanqing, JIANG Dongpo. The development of cooling technology for gas turbine blade[J]. Equipment Manufacturing Technology, 2014(7): 208-210. (in Chinese) doi: 10.3969/j.issn.1672-545X.2014.07.075
    [2]
    HAVEN B A,YAMAGATA D K,KUROSAKA M,et al. Anti-kidney pair of vortices in shaped holes and their influence on film cooling effectiveness[R]. ASME 97-GT-45,1997.
    [3]
    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
    [4]
    ZHANG Guohua,ZHU Rui,XIE Gongnan,et al. Optimization of cooling structures in gas turbines: a review[J]. Chinese Journal of Aeronautics,2022,35(6): 18-46. doi: 10.1016/j.cja.2021.08.029
    [5]
    GOLDSTEIN R J,ECKERT E R G,BURGGRAF F. Effects of hole geometry and density on three-dimensional film cooling[J]. International Journal of Heat and Mass Transfer,1974,17(5): 595-607. doi: 10.1016/0017-9310(74)90007-6
    [6]
    朱惠人,许都纯,刘松龄,等. 簸箕形排孔气膜冷却实验研究[J]. 航空学报,1997(5): 25-28. ZHU Huiren,XU Duchun,LIU Songlin,et al. Film cooling experimental investigation of a row of dust-pan shaped holes[J]. Acta Aeronautica et Astronautica Sinica,1997(5): 25-28. (in Chinese

    ZHU Huiren, XU Duchun, LIU Songlin, et al. Film cooling experimental investigation of a row of dust-pan shaped holes[J]. Acta Aeronautica et Astronautica Sinica, 1997(5): 25-28. (in Chinese)
    [7]
    戴萍,林枫. 气膜孔形状对冷却效率影响的数值研究[J]. 动力工程,2009,29(2): 117-122. Dai Ping,LIN Feng. Numerical investigation on the influence of transverse slot configurations on film cooling effect[J]. Journal of Propulsion Technology,2009,29(2): 117-122. (in Chinese

    Dai Ping, LIN Feng. Numerical investigation on the influence of transverse slot configurations on film cooling effect[J]. Journal of Propulsion Technology, 2009, 29(2): 117-122. (in Chinese)
    [8]
    朱惠人,许都纯,刘松龄. 气膜孔形状对排孔下游冷却效率的影响[J]. 航空学报,2002,23(1): 75-78. ZHU Huiren,XU Duchun,LIU Songling. Effects of hole shape on film cooling effectiveness[J]. Acta Aeronautica et Astronautica Sinica,2002,23(1): 75-78. (in Chinese doi: 10.3321/j.issn:1000-6893.2002.01.015

    ZHU Huiren, XU Duchun, LIU Songling. Effects of hole shape on film cooling effectiveness[J]. Acta Aeronautica et Astronautica Sinica, 2002, 23(1): 75-78. (in Chinese) doi: 10.3321/j.issn:1000-6893.2002.01.015
    [9]
    张盛昌,张靖周,谭晓茗. 利用上游沙丘形斜坡增强气膜冷却[J]. 航空动力学报,2020,35(5): 973-982. ZHANG Shengchang,ZHANG Jingzhou,TAN Xiaoming. Film cooling enhancement by using upstream sand-dune-shaped ramp[J]. Journal of Aerospace Power,2020,35(5): 973-982. (in Chinese

    ZHANG Shengchang, ZHANG Jingzhou, TAN Xiaoming. Film cooling enhancement by using upstream sand-dune-shaped ramp[J]. Journal of Aerospace Power, 2020, 35(5): 973-982. (in Chinese)
    [10]
    KALGHATGI P,ACHARYA S. Improved film cooling effectiveness with a round film cooling hole embedded in a contoured crater[J]. Journal of Turbomachinery,2015,137(10): 101006. doi: 10.1115/1.4030395
    [11]
    王海,范芳苏,浦健,等. 带凹坑圆孔气膜冷却流动传热特性[J]. 航空动力学报,2022,37(3): 492-501. WANG Hai,FAN Fangsu,PU Jian,et al. Flow and heat transfer characteristics of round-hole film cooling with crater[J]. Journal of Aerospace Power,2022,37(3): 492-501. (in Chinese

    WANG Hai, FAN Fangsu, PU Jian, et al. Flow and heat transfer characteristics of round-hole film cooling with crater[J]. Journal of Aerospace Power, 2022, 37(3): 492-501. (in Chinese)
    [12]
    AN Baitao,LIU Jianjun,ZHANG Xiaodong,et al. Film cooling effectiveness measurements of a near surface streamwise diffusion hole[J]. International Journal of Heat and Mass Transfer,2016,103: 1-13. doi: 10.1016/j.ijheatmasstransfer.2016.07.028
    [13]
    KIM J H,KIM K Y. Surrogate-based optimization of a cratered cylindrical hole to enhance film-cooling effectiveness[J]. Journal of Thermal Science and Technology,2016,11(2): JTST0025. doi: 10.1299/jtst.2016jtst0025
    [14]
    BAI Linchao,ZHANG Chao. Flow mechanism of cooling effectiveness improvement for the cylindrical film cooling hole with contoured craters[J]. IOP Conference Series: Materials Science and Engineering,2019,473: 012033. doi: 10.1088/1757-899X/473/1/012033
    [15]
    ZHANG Zong,QIAN Wei,HU Jing. A numerical research on diverse cratered film cooling hole geometries[J]. Key Engineering Materials,2016,693: 491-497. doi: 10.4028/www.scientific.net/KEM.693.491
    [16]
    WU Xiaojun,DU Xin,WANG Chunhua. Study on film cooling performance of round hole embedded in different shaped craters and trenches[J]. Aerospace,2021,8(6): 147. doi: 10.3390/aerospace8060147
    [17]
    KHALATOV A,SHI-JU E,WANG Dongyun,et al. Film cooling evaluation of a single array of triangular craters[J]. International Journal of Heat and Mass Transfer,2020,159: 120055. doi: 10.1016/j.ijheatmasstransfer.2020.120055
    [18]
    LU Yiping,DHUNGEL A,EKKAD S V,et al. Effect of trench width and depth on film cooling from cylindrical holes embedded in trenches[J]. Journal of Turbomachinery,2009,131(1): 011003. doi: 10.1115/1.2950057
    [19]
    LU Yiping,DHUNGEL A,EKKAD S V,et al. Film cooling measurements for cratered cylindrical inclined holes[J]. Journal of Turbomachinery,2009,131(1): 011005. doi: 10.1115/1.2950055
    [20]
    RALLABANDI A P,LI S J,HAN J C. Unsteady wake and coolant density effects on turbine blade film cooling using pressure sensitive paint technique[J]. Journal of Heat Transfer,2012,134(8): 081701. doi: 10.1115/1.4006748
    [21]
    李佳. 燃气轮机透平气膜冷却机理的实验与理论研究[D]. 北京: 清华大学,2011. LI Jia. Experimental and theoretical study on gas turbine film cooling mechanism[D]. Beijing: Tsinghua University,2011. (in Chinese

    LI Jia. Experimental and theoretical study on gas turbine film cooling mechanism[D]. Beijing: Tsinghua University, 2011. (in Chinese)
    [22]
    LI Guangchao,YANG Peng,ZHANG Wei,et al. Enhanced film cooling performance of a row of cylindrical holes embedded in the saw tooth slot[J]. International Journal of Heat and Mass Transfer,2019,132: 1137-1151. doi: 10.1016/j.ijheatmasstransfer.2018.12.080
    [23]
    LIU Cunliang,ZHU Huiren,BAI Jiangtao,et al. Film cooling performance of converging-slot holes with different exit-entry area ratios[J]. Journal of Turbomachinery,2011,133(1): 011020. doi: 10.1115/1.4000543
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 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
    Get Citation
    PDF(2884.0KB)
    XML

    Article Metrics

    Article views (1017) PDF downloads(79) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return