Setting up the mathematical model of gas fuel combustion taking into account computational domain geometry refinement
DOI:
https://doi.org/10.7242/1999-6691/2020.13.1.5Keywords:
gas fuel combustion, gas-turbine engine, RANS, SST turbulence model, combined EDM/FRC model, computational experiments, computational domain geometry refinemenAbstract
The problem of gaseous fuel combustion in a land-used gas turbine engine combustion chamber was formulated, and the results of the numerical solution were described. The paper assumes that the gas-air mixture is a single-phase, multicomponent and reactive flow. The Reynolds averaging approach to the Navier-Stokes equations was used to describe the turbulent flow in the combustion chamber. The SST model of turbulence was used to close the averaged system .A combined EDM/FRC combustion model was used to determine the rate of formation of mixture components. A technique was proposed for setting up the mathematical model taking into account three parameters: the turbulent Prandtl and Schmidt numbers and the coefficient limiting the burning rate. Based on a comparison of the results of preliminary calculations and experiments, it was suggested that the difference in these data is due to technological deviations and the application of a heat-protective coating to the walls of the flame tube. The geometry of the computational domain was changed based on the airflow coefficient obtained in the aerodynamic tests. The setting up of the mathematical model was carried out both on the initial and on the refined geometry. The verification of the mathematical model was carried out using the results of experiments on three structural variants of the flame tube. The results of calculations carried out with the use of refined data showed that a change in geometry made it possible to more correctly describe combustion in a turbulent flow: the theoretical results on the average non-uniformity obtained on the refined geometry of the studied region practically coincide with the experimental data. Due to updating the geometry of the computational domain, it was possible to establish the location and magnitude of the maximum non-uniformity. Using the results obtained in this work, a mathematical model was developed to describe the combustion of gaseous fuel in the combustion chamber of a gas turbine engine. The proposed model can be used to further optimize the design of the combustion chamber.
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