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首页> 外文会议>ASME Turbo Expo: Turbomachinery Technical Conference and Exposition >NUMERICAL STUDY ON COOLING CHARACTERISTICS OF DOUBLE-ROW CYLINDRICAL HOLES ON UPSTREAM ENDWALL
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NUMERICAL STUDY ON COOLING CHARACTERISTICS OF DOUBLE-ROW CYLINDRICAL HOLES ON UPSTREAM ENDWALL

机译：上游端墙上双排圆柱孔冷却特性的数值研究

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摘要

In this paper film-cooling effectiveness of two rows of cylindrical holes located on the endwall upstream of a vane is investigated numerically. Five different cooling schemes, including three schemes of double rows cylindrical holes (β=-45°, 0°, 45°), and two schemes of Double-jet film cooling (DJFC) holes (β=-45°, 45° and β=45°, -45°), are arranged on the endwall at four blowing ratios (M = 0.5, 1.0, 1.5, 2.0). Both primary effect (on downstream endwall) and secondary effect (on pressure and suction surfaces) of the endwall film cooling are considered. 1CEM is used to mesh the computational domain, and simulation is carried out by ANSYS 14.0. The result shows that cooling jets with compound angles can effectively suppress lifting-off and increase film-cooling effectiveness. In addition, at low blowing ratios, it is difficult for jets no matter what directions to cool the neighborhood of the leading edge and the pressure side due to the effect of horseshoe vortices. However, passage vortices have different effects on the cooling jets with different compound angles which will result in different film coverage on both endwall and airfoil.
机译：在该纸张 - 冷却效果，在数值上研究了位于叶片上游的端部上的两排圆柱孔。五种不同的冷却方案，包括三个双行圆柱孔的方案（β= -45°，0°，45°）和双喷射膜冷却（DJFC）孔的两种方案（β= -45°，45° β= 45°，-45°），以四个发泡比（M = 0.5,1.0,1.5,2.0）布置在端壁上。考虑初级效应（上游端壁）和末端膜冷却的次穿膜冷却的次要效果（在压力和抽吸表面上）。 1CEM用于网格来对计算域网，并且通过ANSYS 14.0执行模拟。结果表明，具有复合角度的冷却射流可以有效地抑制升降和提高薄膜冷却效果。另外，在低吹效率下，由于马蹄涡流的效果，射流难以冷却前缘和压力侧的邻距。然而，通道涡流对具有不同复合角的冷却射流具有不同的效果，这将导致端壁和翼型上的不同膜覆盖。

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