Heat Transfer Research on a Certain Gas Turbine Blade

Abstract

The internal cooling effects on a stator blade in a turbine was simulated. The results showed that the thermal barrier coating (TBC) not only lowered the temperature but also made the temperature distribution more uniform, which could decrease the thermal stress and prolong the blade using life to a great extent. The FORTRAN code was used to solve the internal heat transfer coefficient and the temperature of the blade wall and get the temperature in the 10%, 50% and 90% of the blade height. It was found the blade wall temperature was below 1100K, which meets the requirement of the gas turbine blade in the practical application. Keywords-conjugate heat transfer ； gas turbine nozzle ； , blade cooling； TBC I.978-1-4244-6255-1/11/$26.00