Experimental investigation of effusion and film cooling for gas turbine combustor

Abstract

Experimental study was conducted to understand the heat transfer characteristics of film or effusion cooled test plates that represent the gas turbine combustor liner. Two effusion cooling test plates having different hole angles (30 and 75° with horizontal) were used. Film cooling tests were conducted by six different slot geometries. Test geometries were the scaled-up model of real combustor liner. Three different blowing ratios were applied for each test plate geometry. Surface cooling effectiveness was determined for each test condition by measuring the surface temperature distribution by infrared thermography technique. Effects of geometrical and flow parameters on cooling effectiveness were investigated.