Numerical Study of Swirl Cooling in a Turbine Blade Leading-Edge Model

Numerical Study of Swirl Cooling in a Turbine Blade Leading-Edge Model
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涡轮叶片前缘模型旋流冷却的数值研究

DOI:
10.2514/1.t4362
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发表时间:
2015-02
影响因子:
2.1
通讯作者:
Feng Zhenping
Feng Zhenping
中科院分区:
工程技术4区
文献类型:
--
作者:
Liu Zhao;Li Jun;Feng Zhenping

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对某燃气涡轮机叶片前缘内冷却通道模型的旋流冷却性能进行了数值模拟。研究了两个矩形截面进气道使气流切向冲击圆形冷却通道内表面时的旋流冷却性能及其有效性。在不同的雷诺数,以及旋流室半径的比例,射流槽高度的旋流室半径的喷嘴长度和恒定的喷嘴面积的比例不变,分别进行局部和平均流动和传热的参数分析。结果表明,旋流中心位置沿旋流室轴向沿着变化,且同一轴向截面上的旋流中心位置在不同旋流室半径与射流槽高度比下也不均匀。旋流室半径与射流槽高度的比值越大,雷诺数越大,旋流器的性能越好。
In this paper, a numerical simulation is conducted to predict the swirl cooling performance of an internal leading-edge cooling passage model for a gas turbine blade. The swirling cooling performance and its effectiveness are investigated in the case of two rectangular section inlets that cause flow to impinge tangentially on the internal surface of the circular cooling passage. Parametric analysis on the local and average flows and heat transfers are performed at various Reynolds numbers, as well as the ratio of swirl chamber radius to jet slot height for a constant ratio of swirl chamber radius to jet nozzle length and constant jet nozzle area, respectively. The results indicate that the position of the swirl flow center is changing along the axial of the swirl chamber, and the swirl flow center of one constant axial section is not uniform as well in different ratios of swirl chamber radius to jet slot height. The larger ratio of swirl chamber radius to jet slot height and the higher Reynolds number are...
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