Numerical Model for Predictions of Reverse Flow Combustor Aerothermal Characteristics
A mathematical model of three-dimensional two-phase reacting flows in gas turbine combustion chambers has been developed. The governing time-averaged partial differential equations and the physical modelling for the turbulence, combustion and thermal radiation have been solved by a numerical tecnique based on the finite volume approach. A reverse flow type combustor was used to validate the model. The results are found to be in close agreement with available experimental data. An assessment of the adequacy of the various submodels embodied has been made in view of future improvements.
KeywordsRoot Mean Square Mixture Fraction Exit Plane Primary Zone Finite Volume Approach
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