Experimental verification of film-cooling concepts on a turbine vane

Abstract

Film cooling concepts applied to gas turbine vanes were investigated. The filming cooling air was ejected from a single row of holes on the convex surface and a double row of holes of the concave surface. Tests were conducted at a gas temperature of 1260 K, a gas pressure of 3 atmospheres, and a coolant temperature of 280 K. Mass velocity ratios were varied between 0 and 2.0. Data were taken without film cooling holes, with film cooling holes but without blowing, and with blowing. A small amount of blowing into a nonturbulent boundary layer caused an increase in vane temperatures. Film cooling when combined with convection cooling was verified to be more effective than either film or convection cooling alone