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Experimental and Numerical Study of Turbulent Flow and Heat Transfer in a Wedge-shaped Channel with Guiding Pin Fins for Turbine Blade Trailing Edge Cooling

机译:涡轮机叶片后边缘冷却引导销翅片在楔形通道中湍流流动和传热的实验和数值研究

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摘要

Gas turbine blades employ wedge-shaped channels for the trailing edge internal cooling. Detailed experimental and numerical analyses have been done on the heat transfer and turbulent flow structures in a wedge-shaped channel with arrays of streamlined pin fins for the Reynolds number range from 20,000 to 80,000. The study examines two different configurations of the streamlined guiding pin fins in the wedge-shaped channels, which show the potential of flow guiding and heat transfer improvement for the turbine blade trailing edge internal cooling. The experiments indicate that the streamlined shape of the guiding pin fins causes significantly reduced pressure losses compared to the baseline circular pin fin arrays. Depending on two different configurations the guiding pin fin arrays can achieve pressure loss reduction by up to about 37.3% and 8.7%, respectively, while obtaining appreciably higher average heat transfer on the bottom wall by up to about 8.8% and 12.0%, respectively, compared to the baseline circular pin fin arrays. Besides, the conjugate numerical simulations obtain the total Nusselt numbers of the different pin fin array configurations. Depending on two different configurations the guiding pin fin arrays increase the total Nusselt numbers by up to 11.5% and 13.8%, respectively, compared to the baseline circular pin fin arrays. Additionally, the heat transfer enhancement and pressure loss reduction present more significant promotions for the guiding pin fin arrays as the Reynolds number increases. Also, the numerical simulations reveal the detailed flow structures in the wedge-shaped channels with different pin fin configurations and demonstrate the flow guiding mechanism of the guiding pin fin arrays. Due to the flow optimizations by the guiding pin fin arrays in the wedge-shaped channels, the heat transfer and flow distribution uniformities are improved.
机译:燃气轮机叶片采用楔形通道,用于后缘内部冷却。已经在楔形通道中的传热和湍流结构上进行了详细的实验和数值分析,其中雷诺数为20,000至80,000的流线型销翅片阵列。该研究检查了楔形通道中的流线型引导销翅片的两种不同的配置,其示出了对涡轮叶片后缘内冷却的流动引导和传热改进的电位。实验表明,与基线圆形销翅片阵列相比,引导销翅片的流线状的形状引起显着减小的压力损失。根据两种不同的配置,引导销鳍片阵列分别可以减少高达约37.3%和8.7%的压力损失,同时在底壁上获得明显高达约8.8%和12.0%,与基线圆形别针翅片阵列相比。此外,共轭数值模拟可以获得不同引脚鳍阵列配置的总孤立数。与基线圆形销鳍阵列相比,根据两种不同的配置,引导销鳍片阵列分别将总露珠数量增加高达11.5%和13.8%。另外,随着雷诺数的增加,传热增强和压力损失减少对引导销翅片阵列的更大促销产生了更大的促销。而且,数值模拟揭示了具有不同销翅片配置的楔形通道中的详细流动结构,并演示引导销翅片阵列的流动引导机构。由于楔形通道中的引导销鳍片阵列的流动优化,改善了传热和流量分布均匀性。

著录项

  • 来源
    《International Journal of Heat and Mass Transfer》 |2021年第10期|121590.1-121590.15|共15页
  • 作者单位

    Institute of Turbomachinety School of Mechanical Engineering Shanghai Jiao Tong University Dongchuan Road 800 Shanghai 200240 China;

    Institute of Turbomachinety School of Mechanical Engineering Shanghai Jiao Tong University Dongchuan Road 800 Shanghai 200240 China;

    Institute of Turbomachinety School of Mechanical Engineering Shanghai Jiao Tong University Dongchuan Road 800 Shanghai 200240 China;

    Paris Tech Elite Institute of Technology Shanghai Jiao Tong University Dongchuan Road 800 Shanghai 200240 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

    Gas turbine; Trailing edge cooling; Heat transfer; Pin fin; Flow optimization;

    机译:燃气轮机;后缘冷却;传播热量;别针;流量优化;

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