Study of an 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 and pressure field,were compared with the traditional air-cooled turbine blade.The result shows that this new blade locks up 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 along with the decreasing amount of injection.