A test bench for gas turbine combustor cooling investigations

Abstract

Design and installation of a test bench for combustion chamber cooling investigations of gas turbines are carried out. The test bench mainly consists of a radial fan, an electrical heater, an air tunnel, a test section, and cooling air supply system. The combustor liner is presented by a flat test plate which is a scaled-up model of a real combustor geometry. Main flow can be provided at a temperature in the range of 298-573 K, which enables a wide range of density and blowing ratio between the main flow and the coolant. The surface temperature distribution of the test plate is measured by infrared thermography technique to determine the adiabatic cooling effectiveness. The test bench enables to investigate the effects of different geometrical and flow parameters on effusion and film cooling effectiveness.