Based on a 3D N-S solver

a computational method was adopted to simulate the flow field in film-cooling turbine

which included a finite difference scheme with 3rd order precision and TVD property

domain decomposition method and arbitrarily curved mesh technique.Air was ejected from 8 locations on the turbine blade surface and the upper and lower endwalls.Both the flow fields in the turbine cascade with straight and bowed blade were simulated.The results show that bowed blade apparently reduces the endwall losses whether with and without cooling.The aerodynamic performance of bowed blade becomes worse when the ejection flux is getting larger in the mid-span.