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对某小型燃气轮机设计工况下的涡轮动叶,采用标准k-ε湍流模型,数值模拟了复合角气膜孔对冷却效果的影响.主流雷诺数为670 000,比较了吹风比分别为0.5,1.0,1.5和2.0时,采用60°,30,°0°,-30°和-60°复合角气膜孔的气膜流动情况和冷却效果.结果表明:在旋转状态下,压力面上复合角可以有效地提高气膜冷却效果,受哥氏力的影响,朝向低半径的复合角的气膜冷却效果要好于朝向高半径;吸力面上复合角对气膜冷却效果的影响不大.
For a small gas turbine design turbine turbomachinery, the standard k-ε turbulence model was used to simulate the effect of the composite angle film pore on the cooling effect.The main Reynolds number was 670 000, the blow ratio was 0.5, 1.0, 1.5 and 2.0, the gas film flow and cooling effect of the composite angular gas film pores of 60 °, 30 °, ° 0 °, -30 ° and -60 ° were used.The results show that under the rotating condition, Angle can effectively improve the cooling effect of the gas film. Under the influence of Coriolis force, the cooling effect of the gas film toward the compound corner with the lower radius is better than that toward the high radius; the composite angle on the suction surface has little effect on the film cooling effect.