RT Journal Article ID 1b9265be167f4135 A1 Altun, Ozge T1 HEAT TRANSFER ANALYSIS IN THE TBC COATED EXHAUST NOZZLE OF GAS TURBINES JF Heat Transfer Research JO HTR YR 2015 FD 2014-10-08 VO 46 IS 1 SP 13 OP 29 K1 heat transfer K1 gas turbine nozzle K1 thermal barrier coatings K1 numerical modeling AB Estimation of temperature distribution in hot section components plays an important role in the development of new generation of gas turbines. In this study, temperature distribution in a thermal barrier coated exhaust nozzle has been investigated. The numerical simulations were carried out using commercial codes FLUENT and GAMBIT to calculate heat transfer distributions. The temperature distributions in the exhaust nozzle were calculated taking into consideration all three heat transfer mechanisms: conduction, convection, and radiation. The wall temperature is significantly decreased by thermal barrier coating. PB Begell House LK https://www.dl.begellhouse.com/journals/46784ef93dddff27,6a92787e7fdb78cc,1b9265be167f4135.html