Effect of Radiation on Gas Turbine Combustor Liner Temperature With Conjugate Heat Transfer (cht) Methodology

Abstract

Design of a gas turbine combustor is a challenging process. It contains many stages including estimation of liner wall temperatures in order to determine the lifetime of the engine. Therefore, accurate prediction of the liner wall temperature is an essential part of the gas turbine combustor design. The liner is heated by convection and radiation of the combustion gases inside the flame tube and it is cooled by convection to the air in annulus and radiation to the outer casing. Many studies have been performed with Conjugate Heat Transfer (CHT) methodology neglecting the effect of radiation on the liner temperature due to its complexity and limited computational power sources. The Effect of radiative heat transfer on combustor liner temperature using CHT methodology is studied in the present work. Radiation from luminous flame which is caused by formation of soot particles in the flame is not accounted for and radiation from non-luminous flame due to combustion gases, CO2 and H2O, and surface radiation is investigated. Effect of turbulent Schmidt/Prandtl number is also investigated in this paper. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.