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首页> 外文期刊>Journal of Heat Transfer >Full-Coverage Film Cooling: Heat Transfer Coefficients and Film Effectiveness for a Sparse Hole Array at Different Blowing Ratios and Contraction Ratios
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Full-Coverage Film Cooling: Heat Transfer Coefficients and Film Effectiveness for a Sparse Hole Array at Different Blowing Ratios and Contraction Ratios

机译:全覆盖薄膜冷却:稀疏孔阵列在不同的吹塑比和收缩比下的传热系数和膜效率

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摘要

The present experimental investigation considers a full coverage film cooling arrangement with different streamwise static pressure gradients. The film cooling holes in adjacent streamwise rows are staggered with respect to each other, with sharp edges and streamwise inclination angles of 20 deg with respect to the liner surface. Data are provided for turbulent film cooling, contraction ratios of 1 and 4, blowing ratios (BRs) (at the test section entrance) of 2.0, 5.0, and 10.0, a coolant Reynolds number of 12,000, freestream temperatures from 75 ℃ to 115℃, a film hole diameter of 7 mm, and density ratios from 1.15 to 1.25. Nondimensional streamwise and spanwise film cooling hole spacings, X/D and Y/D, are 18 and 5, respectively. Data illustrating the effects of contraction ratio, BR, and streamwise location on local, line-averaged, and spatially averaged adiabatic film effectiveness data; and on local, line-averaged and spatially averaged heat transfer coefficient data are presented. Varying BR values are present along the length of the contraction passage, which contains the cooling hole arrangement, when contraction ratio is 4. Dependence on BR indicates important influences of coolant concentration and distribution. For example, line-averaged and spatially averaged adiabatic effectiveness data show vastly different changes with BR for the configurations with contraction ratios of 1 and 4. In addition, much larger effectiveness alterations are present as BR changes from 2.0 to 10.0, when significant acceleration is present and Cr = 4 (in comparison with the Cr = 1 data).
机译:本实验研究考虑了具有不同流向静压力梯度的全覆盖膜冷却装置。相邻的流向行中的薄膜冷却孔彼此交错,具有锐利的边缘,并且流向相对于衬套表面的倾斜角度为20度。提供了湍流薄膜冷却的数据,收缩比为1和4,吹塑比(BRs)(在测试段入口)为2.0、5.0和10.0,冷却剂雷诺数为12,000,自由流温度为75℃至115℃ ,膜孔直径为7 mm,密度比为1.15至1.25。沿流向和跨向的无尺寸薄膜冷却孔间距X / D和Y / D分别为18和5。说明收缩率,BR和流向位置对局部,线平均和空间平均绝热膜有效性数据的影响的数据;并给出了局部,线平均和空间平均的传热系数数据。当收缩比为4时,沿着包含冷却孔布置的收缩通道的长度会出现变化的BR值。依赖于BR表示冷却剂浓度和分布的重要影响。例如,线平均和空间平均绝热效果数据显示,对于压缩比为1和4的构型,BR的变化很大。此外,当BR从2.0变为10.0时,效率变化更大。存在且Cr = 4(与Cr = 1数据相比)。

著录项

  • 来源
    《Journal of Heat Transfer》 |2015年第3期|032201.1-032201.12|共12页
  • 作者单位

    Department of Engineering Science, University of Oxford, Oxford, UK,Eminent in Propulsion, Mechanical and Aerospace Engineering, College of Engineering, Department of Mechanical and Aerospace Engineering, Propulsion Research Center, Olin B. King Technology Hall S236, University of Alabama in Huntsville, Huntsville, AL 35899;

    Department of Engineering Science, University of Oxford, Oxford, UK,Hill Air Force Base, USAF, 6030 Gum Lane, Bldg. 1217, Hill AFB, UT 84056;

    Solar Turbines Inc., Heat Transfer Research, 2200 Pacific Highway, P. O. Box 85376, Mail Zone C-9, San Diego, CA 92186-5376;

    Solar Turbines Inc., Heat Transfer Research, 2200 Pacific Highway, P. O. Box 85376, Mail Zone C-9, San Diego, CA 92186-5376;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    film cooling; full-coverage film cooling; thermal protection; turbine; gas turbine engine; heat transfer;

    机译:薄膜冷却;全覆盖薄膜冷却;热保护;涡轮;燃气涡轮发动机传播热量;

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