抄録
In a compressor and a turbine blade passages, there exist a number of vorticies such as horseshoe vortex and passage vortex. They lead to large loss. Tip leakage vortex is one of such vorticies, and accounts for about 30% of all loss in a turbine stage. In the present study, we perform numerical simulations for the flow field around a turbine blade with/without jet injection from the tip platform. The effects of injection on the blade performance are clarified..
