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.
Description:
Papers presented to the 12th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics, Costa de Sol, Spain on 11-13 July 2016.
