A PROPOSED METHOD FOR CALCULATING FILM-COOLED WALL TEMPERATURES IN GAS TURBINE COMBUSTION CHAMBERS

摘要

The growing awareness of pollutant emissions from gas turbine engines is highlighting the need to minimise the amount of air employed in liner film cooling and thereby reduce the output of carbon monoxide and unburned hydrocarbons. To this end an analysis has been made of experimental data obtained on a specially designed film-cooling rig which has led to the development of a calculation procedure for liner wall temperatures in the presence of film cooling.nThe purpose of this paper is to describe the procedure and show the level of agreement between predicted values of wall temperature and the results of thermal paint tests carried out an an aircraft combustor at pressures up to 30 atmospheres. The implication of the results to the design of cooling slots for optimum performance is also discussed.