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据《ASME Journal of Engineering for Gas Turbines and Power》2009年5月号报道,加拿大Concordia大学的学者利用计算流体力学方法,在跨音速叶片上进行气膜冷却的性能计算研究(或气膜冷却方案的可行性)。气膜冷却孔位于叶栅通路喉部附近。对于圆孔,气膜冷却效果可通过数值估算
According to the May 2009 issue of ASME Journal of Engineering for Gas Turbines and Power, researchers at Concordia University in Canada used computational fluid dynamics (CFD) methods to calculate the performance of gas-cooled films on transonic blades feasibility). The film cooling hole is located near the throat of the cascade. For round holes, the film cooling effect can be estimated by numerical