Film cooling modeling of a turbine vane with multiple configurations of holes

Film cooling flow is important for gas turbine thermal protection. But it is difficult to predict the film cooling flow performances. The aim of this paper is to modeling the film cooling flow of a turbine vane with endwall film cooling, showerhead film cooling, and pressure/suction side film cooling simultaneously. Developing a method by adding endwall film cooling domain, the endwall film cooling flow can be simulated by CFD. This method can include heat transfer between flow and solid and capture the coolant details in the entering tubes. The conjugate heat transfer (CHT) method was utilized for fluid-solid thermal transfer at interfaces. The results show that the highest film overall effectiveness occurred immediately downstream the holes. The distribution of overall effectiveness is relatively homogenous in the zones between holes row in the leading edge no matter considering solid conduction. Without solid thermal transfer, better lateral coverage downstream the holes can form due to higher density ratio. The overall effectiveness and temperature field are affected by solid conduction, but the aerodynamic performance keeps consistent. Single row of holes in endwall cannot form good coverage in the lateral direction, but the showerhead film cooling configuration can form a preferable coverage layer.