关键词: 涡轮叶片;薄膜冷却;流量系数;计算;实验

Abstract: The empirical means for prediction of discharge coefficients of film cooling holes on the turbine blade suggested by Rowbury D A et al was improved to adapt the computations in the cases of low pressure ratios and the holes in leading edge region especially. The effects of external cross flow, hole geometry and Reynold number in the hole were taken into account. An additive loss coefficient method is subsequently applied to the test data in order to show the effect of the external crossflow. To compare with great deal of experimental data, the result shows the improved method may be used as a generalized design methodology of film cooling for turbine blade.

Key words: Turbine blade;Film cooling;Flow coefficient;Computation;Experimentation