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TURBINE-09. Proceedings of International Symposium on Heat Transfer in Gas Turbine Systems
August, 9-14, 2009, Antalya, Turkey

DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst


ISBN Print: 978-1-56700-263-8

MODELING OF HEAT TRANSFER IN EXHAUST NOZZLE OF GAS TURBINES

page 9
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.240
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RESUMO

Thermal barrier coatings (TBCs) are widely used ceramic based coatings in different industries because of their advantages. They are used in aerospace, diesel engine and power plant technologies due to porous structures and especially low thermal conductivity. Because of high turbine temperatures thermal barrier coatings are applied hot part components to protect the metallic parts and increase performance at high temperatures. They are applied blades, vanes, combustion chambers and exhaust nozzles in gas turbines. In this present work, numerical steady-state exhaust nozzle heat transfer mechanisms were studied. Numerical analysis of heat transfer by conduction and radiation in a TBC was investigated. Radiation to the external surface of coating and conduction to the coating and superalloy nozzle were modeled. The effective thermal conductivity was simulated. This analysis includes the CFD model of gas, coating and metal parts. CFD studies were carried out using Fluent 6.1.22 code. The thermal barrier coatings provide thermal insulation of nozzle and can reduce the temperature by up to 350 °C.

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