涡轮叶片型面气膜孔流量系数的计算方法

A method for discharge coefficients computation of film cooling holes on blade surface of turbine cascade

在RowburyDA等提出的算法基础上进行了改进, 使该算法更适合用来计算压比较小情况下尤其是叶片前缘区域的气膜孔流量系数。该算法主要考虑了气膜孔出口主流流动状况、气膜孔几何参数和孔内流动雷诺数对气膜孔流量系数的影响。经过实验数据对比验证, 表明该算法可能成为设计型面气膜冷却的一种通用方法。

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.