In this paper, a hexagonal prism inlet chamber is used to form a swirling flow for the film cooling, and three kinds of compound angle of film hole (γ = 10°, 20°, 30°) with clockwise swirling or counterclockwise swirling are used for numerical simulation studies. The influence of different compound angles of film hole and the swirling directions for the film cooling effectiveness are obtained. The results show that the film cooling effectiveness and spanwise cooling coverage range of the clockwise swirling or counterclockwise swirling flow both are low when the compound angle of film hole is 10°. With the increasing compound angle of film hole, the kidney shaped vortex of film hole exit gradually weakens until it disappears, which reduces the entrainment effect by the coolant jet. So that the spanwise coverage range of two swirling modes is obviously improved. When the compound angle of film hole is 30° compared to 10°, the average spanwise film cooling effectiveness of clockwise swirling and counterclockwise swirling are increased by about 133.75 and 212.6%, respectively. The average spanwise film cooling effectiveness on the downstream of film hole for counterclockwise swirling is increased by about 140% compared with clockwise swirling.

本文采用六边形棱柱进气室形成旋流，以进行薄膜冷却，并形成三种薄膜孔复合角（γ = 10°，20°，30°），顺时针旋转或逆时针旋转用于数值模拟研究。得到了不同的膜孔复合角度和旋流方向对膜冷却效率的影响。结果表明，当膜孔复角为10°时，顺时针旋流或逆时针旋流的膜冷却效率和跨度冷却覆盖范围均较低。随着膜孔复合角的增加，膜孔出口的肾形涡旋逐渐减弱直至消失，这降低了冷却剂射流的夹带作用。从而明显提高了两种回旋方式的翼展方向覆盖范围。当薄膜孔的复合角为30°而不是10°时，顺时针旋流和逆时针旋流的平均翼展方向膜冷却效率分别提高了约133.75和212.6％。与顺时针旋流相比，逆时针旋流在薄膜孔下游的平均翼展方向薄膜冷却效率提高了约140％。