THE NUMERICAL STUDY OF A NEW AIR-COOLED TURBINE BLADE WITH DEPRESSION FEATURE AT LEADING EDGE

摘要

A new air-cooled turbine blade with depression feature at leading edge was presented in this paper. The flow field of this blade 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.