内部冲击构型对气冷涡轮气热耦合计算影响的对比研究

To evaluate the effects of changes in the internal cooling structure of complex cooling turbines on the aerodynamic and heat transfer performance of turbines, three high-pressure guide vanes with different internal impact structures are studied using a conjugate heat transfer calculation. The effects of impingement structures on the aerodynamic and heat transfer performance of turbines are analyzed. The results show that: In terms of aerodynamic performance, the total flow rate of the structure without impingement is the largest, and the structure with impingement sleeve is the smallest. At the same time, the aerodynamic efficiency of the turbine also changes for different internal structure. In terms of heat transfer, it can be found that both impingement cases can reduce the maximum temperature on the blade surface, but the impingement sleeve structure case can also reduce the average temperature on the blade surface.