Radiation heat transfer in a gas slab with properties characteristics of a jet engine combustor

• Autor(a) principal: Maurente, André Jesus Soares
• Data de Publicação: 2019
• Outros Autores: Alves, Camilo G.
• Tipo de documento: Artigo
• Idioma: eng
• Título da fonte: Repositório Institucional da UFRN
• Texto Completo: https://repositorio.ufrn.br/handle/123456789/31906
• topic: Line-by-line radiation heat transfer; Jet engine combustor; Participating gases; H2O-CO2-CO gas mixture

Due to economic and environmental reasons, there is an important demand to improve durability and fuel efficiency of jet engines for commercial aviation. Computer simulations are largely employed with the goal of gaining knowledge for design and optimization of the engines. Simulations are increasingly realistic, tanking into account complex coupled phenomena. However, radiation is often either neglected or included using quite simple models for the spectral dependence of the radiative properties. In this paper, the radiative transfer is accurately solved line-by-line for a one-dimensional gas slab with temperature, pressure and H2O, CO2 and CO molar fractions encountered in a jet engine combustor. These gas properties were selected from results obtained by a CFD simulation of a jet engine combustor-turbine, which was accomplished by researchers of NASA John H. Glenn Research Center, considering a realistic geometry and high-fidelity models for combustion, fuel injection and turbulence. The line-by-line solution obtained for such realistic gas serves as benchmark to simpler spectral models which could be further applied in highly computational time consuming coupled simulations of jet engines. In addition, the obtained results allowed to estimate the radiative heat transfer to critical regions of the engine and verify the relative importance of emitting/absorbing species, showing that CO2 has minor importance, while the H2O dominates the radiative transfer