Abstract
Nowadays, in order to obtain a higher efficiency in aeroengines, the increase in the turbine inlet temperature of gas turbine engine is an urgent need. At present, the turbine inlet temperature is close to 2000K, which means the radiation and coupled radiationconduction heat transfer play more and more important roles in hot section of aeroengines. As we all konw, considering the cylindrical symmetry of the aeroengine. It is convenient to adopt the cylindrical coordinate to simplify the systems in aeroengines with cylindrical geometry, such as annular combustor and exhaust nozzle. In this paper, the Discontinuous Spectral Element Method (DSEM) is extended to solve the radiation and coupled radiationcoduction heat transfer in cylindrical coordinate systems. Both the spatial and angular computational domains of radiative transfer equation (RTE) are discretized and solved by DSEM. For coupled radiationconduction heat transfer problem, Discontinuous Spectral Element MethodSpectral Element Method (DSEMSEM) scheme is used to avoid using two sets of computational grids which would cause the increase of computational cost and the decrease of accuracy. Then, the effects of various geometric and thermal physical parameters are comprehensively investigated. Finally, these methods are further extended to 2D cylindrical system.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
