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为研究燃气轮机叶片表面曲率对气膜冷却性能的影响,对二维斜缝曲面模型(凹面、凸面和平板)进行了数值模拟,选取冷却流体射流入射角35°、主射流密度比1.5,采用RNGk-ε湍流模型计算得到不同吹风比(0.5、1.2和2.0)下斜缝气膜冷却曲面模型壁面的传热系数.结果表明:低吹风比(M=0.5)时,壁面压力梯度越大,传热系数越小;中吹风比(M=1.2)时,射流对主流扰动加剧,传热加强,凹面总体传热系数比凸面小;高吹风比(M=2.0)时,曲率对传热系数的影响减弱,传热系数差异不大.
In order to study the influence of gas turbine blade surface curvature on the film cooling performance, two-dimensional inclined-curved surface models (concave, convex and flat) were numerically simulated. The incidence angle of cooling fluid jet was 35 ° and the main jet density was 1.5. -ε turbulent model was used to calculate the heat transfer coefficient of the wall surface of the film with oblique airfoil cooling curves under different blowing ratios (0.5, 1.2 and 2.0). The results show that the wall pressure gradient increases with the low blowing ratio (M = 0.5) (M = 1.2), the jets aggravate the disturbance of the mainstream and the heat transfer is strengthened, and the overall heat transfer coefficient of the concave surface is smaller than that of the convex surface. When the high blowing ratio (M = 2.0), the influence of curvature on the heat transfer coefficient The influence is weakened, and the difference of heat transfer coefficient is not big.