Study of effects of axisymmetric endwall contouring on film cooling/heat transfer and secondary losses in a cascade of first stage nozzle guide vane
The film cooling and heat transfer on the endwall especially in the junction region of a vane/blade which encounters strong vortical flow is of great significance in turbomachinery. Achievement of excellent film cooling and aerodynamic performance by controlling the secondary flow in that region can lead to increased gas turbine efficiency. This study investigates axisymmetric endwall contouring p