关键词: 薄膜冷却;涡轮部件;温度分布;流动分布;试验

Abstract: xperimental results describe the effects of blowing ratio at M=1. 0 and 2. 0, injection angles on flow field and heat transefer in the downstream of single film cooling hole with compoundangle orientations. The hole with a fan-shaped angle of 0°or 30° was oriented so that its angles with respet to the test surface are 30°or 60°in a stream/normal plane projection, and 30°or 45°in a spanwise/normal plane projection. The measurements were carried out with a detailed directional fivehole probe and thermocouple surveys of the three-dimensional flow field and surface heat transfer distribution. For the first time, it is found in experiments that a pair of counterrotating vorticesone is strong and another is weak, was observed in the downstream region of jet exit. Contours of longitudinal velocity U/U∞ and non-dimensional temperature θ show asymmetric kidney shape. The flared hole effectively decreases the strength of longitudinal vortex and increases the spreading of jet so that the film cooling effectiveness would be much greater than that found in the downstream of circular hole.

Key words: Film cooling;Turbine part;Temperature distribution;Flow distribution;Test