ISSN Online: 2377-424X
ISBN Print: 0-89116-909-1
International Heat Transfer Conference 9
RADIAL COOLING OF GAS TURBINE BLADE TRAILING EDGE WITH COMBINED HEAT CONDUCTION-CONVECTION
Resumo
Enhanced cooling of blade trailing edge is needed for the conversion of aircraft gas turbines to ship propulsion units in order to extend their lifetime. In this paper heat transfer experimental data are presented in the enlarged cooling passages with or without pin-fin rows and a simplified analysis model is proposed to calculate the tip temperature of the blade trailing edge through the combined heat conduction-convection system. The calculated results for the smooth cooling passage of certain blades are in agreement with their published data and the decrease of the tip temperature in the blade trailing edge region is 33°C when two pin-fin rows are used in the cooling passage.