... platform are addressed. An n-factorial study is used to quantify the importance of such effects on aerodynamic losses. endwall contouring nozzle secondary flows heat transfer turbine vane leakage film cooling Early efforts, including those in 1954 by Herzig et al. [ 1 ], identified...

...Scot K. Waye; David G. Bogard Film cooling adiabatic effectiveness for axial and compound angle holes on the suction side of a simulated turbine vane was investigated to determine the relative performance of these configurations. The effect of the surface curvature was also evaluated by comparing...