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Experimental Study on Heat Transfer of Leading Edge Film- Cooling With Counter-Inclined Cylindrical and Laid-Back Holes

机译:用反倾斜圆柱形和铺设孔的前缘薄膜冷热传热的试验研究

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摘要

The heat transfer coefficient of counterinclined film holes fed by different intake structures on the turbine vane leading edge (LE) model is experimentally investigated in this paper. A semicylinder model is adopted to model the vane leading edge, which is arranged with one single row of film holes per side, which are located from the stagnation at a 15-deg angle. The four leading edge models, which are the combinations of the hole-shapes (cylindrical hole and laid-back hole) and intake structures (plenum and impingement), are tested at four blowing ratios M. The contours of the heat transfer coefficient, which are characterized by the Frossling number Fr, since it includes the Reynold number effect, are acquired by the transient measurement technique based on double thermochromic liquid-crystals (LCs). The lateral-averaged Fr of the nonfilm-cooled model is provided by using the same experimental platform with an identical main-flow condition. It is then compared with the published data, which indicates the reliability of the present transient measurement techniques. The results illustrate that a core region with a higher heat transfer appears in the hole-exit downstream, and its distribution is slightly skewed to the inclination direction of the film holes. The shape of the high heat transfer region gradually inclines in the spanwise direction as M increases. The heat transfer in the region where the jet core flows through is relatively low, while the jet edge region is relatively high. The effect of impingement leads to the outflow of each hole becoming increasingly uniform, which can reduce the difference in the heat transfer between the region where the jet core flows through and the jet edge. The heat transfer strength may increase due to the intense turbulence caused by the introduction of the impingement. Compared with the cylindrical hole, the laid-back hole has a spanwise expansion feature, which makes the shape of the high heat transfer region wider in the spanwise direction and increases the heat transfer level. Additionally, the magnitude of the enhancement increases with an increasing M.
机译:在本文实验研究了通过不同进气结构供给的涡轮叶片前缘(LE)模型中的不同进气结构供给的抗衡线膜孔的传热系数。采用半圆形模型来建模叶片前缘,该叶片前缘布置有一排每侧的一排薄膜孔,其位于15°角的停滞处。四个前缘模型,即孔 - 形状(圆柱形孔和铺设孔)和进气结构(增压器和冲击)的组合,以四个吹率M进行测试。传热系数的轮廓,哪个由凹陷号FR的特征在于,由于它包括雷诺数效应,通过基于双热致变色液晶 - 晶体(LCS)的瞬态测量技术来获取。通过使用相同的主流条件的相同的实验平台提供非晶体冷却模型的横向平均FR。然后将其与已发布的数据进行比较,这表示当前瞬态测量技术的可靠性。结果示出了具有较高传热的芯区域出现在下游的孔出口中,并且其分布略微偏向于膜孔的倾斜方向上。随着M的增加,高传热区域的形状逐渐倾斜地倾斜。喷射芯流过的区域中的传热相对较低,而喷射边缘区域相对较高。冲击的效果导致每个孔的流出变得越来越均匀,这可以降低喷射芯流过的区域和喷射边缘之间的传热差。由于引入冲击引起的强烈湍流,传热强度可能增加。与圆柱孔相比,铺砌孔具有翼展膨胀特征,其使高传热区域的形状沿翼展方向宽并增加传热水平。另外,增强的幅度随着M的增加而增加。

著录项

  • 来源
    《Journal of Heat Transfer》 |2020年第6期|061801.1-061801.12|共12页
  • 作者单位

    School of Power and Energy Northwestern Polytechnical University Xi'an Shaanxi 710072 China;

    School of Power and Energy Northwestern Polytechnical University Xi'an Shaanxi 710072 China Shaanxi Key Laboratory of Thermal Sciences in Aero-Engine System Xi'an Shaanxi 710129 China;

    School of Power and Energy Northwestern Polytechnical University Xi'an Shaanxi 710072 China;

    School of Power and Energy Northwestern Polytechnical University Xi'an Shaanxi 710072 China;

    School of Power and Energy Northwestern Polytechnical University Xi'an Shaanxi 710072 China Shaanxi Key Laboratory of Thermal Sciences in Aero-Engine System Xi'an Shaanxi 710129 China;

  • 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

    heat transfer coefficient; transient measurement; leading edge; counter- inclined film holes; impingement;

    机译:传热系数;瞬态测量;前沿;反倾斜薄膜孔;冲击;

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