Numerical Analysis of Film Cooling Characteristic on a Turbine Non-axisymmetric Contoured Endwall

The contoured endwall has been investigated widely as an effective way to increase turbine efficiency by mitigating the strength of vortices. But the film cooling effectiveness may be greatly changed as the surface curvature is an important factor affecting the film cooling performance. So far, the round hole film cooling effectiveness on contoured endwall has been researched, but investigations of the influence of different hole shapes at various inclination angles on film cooling effectiveness and aerodynamic loss have been less found in publications. For the current study, the endwall film cooling effectiveness on contoured endwall and flat endwall are analyzed separately by numerical simulation. Injection angles and film hole shapes are adjusted at three blowing ratios. The film cooling effectiveness and the aerodynamic loss are analyzed.