具有前缘凹陷特征的新型气冷涡轮叶型研究

本文提出了一种具有前缘自锁涡的新型气冷涡轮叶型。对新叶型流场进行了跨音速情况下的详细数值研究。观察了由前缘冷气喷射所形成的冷气旋涡沿叶型表面的变化。将新叶型的冷却效率、能量损失、压力场等与传统气冷涡轮叶型进行了对比。结果表明，新气冷叶型能够把由前缘冷气喷射形成的冷气旋涡锁定在其凹陷部位。冷气与主流的掺混损失减小。因此，前缘冷气喷射孔的列数可以减少。相应地，冷气喷射量可以减少。

A New Air-Cooled Turbine Blade Profile with Depression Feature at Leading Edge

A new air-cooled turbine blade profile with depression feature at leading edge was presented in this paper. The flow field of this blade profile at the transonic condition was simulated in detail. The change of vortex position induced by the leading edge cooling air injection along the blade profile was observed. The aerodynamic characteristics of the new blade such as film effectiveness, energy loss, pressure field etc. were compared with the traditional air-cooled turbine blade. The result shows that this new blade locks the vortex induced by the leading edge cooling air injection in its depression part. The mixing of cooling air and mainstream becomes weak. Thus, the number of the leading edge cooling air injection holes can be reduced. Correspondingly, the amount of injection can also be reduced.