Abstract
The methodology and results of the numerical simulation of gas flow with sprayed fuel combustion in a helicopter gas turbine annular combustor are presented. The goal of the simulation is to predict the non-uniformity of the combustor exit gas temperature field. The calculations are performed in two settings: a) with the simplified model of a full-size combustor included in the computational domain; b) with the one-burner sector of the combustor included in the computational domain and setting periodic boundary conditions. The results of the numerical simulation confirmed the influence of periodic boundary conditions on the accuracy of prediction of the combustor exit gas temperature field. The full-size combustor calculation is shown to be more appropriate and universal but more costly than the calculation of its one-burner sector.
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Schedule a callMore From: Вестник Самарского государственного аэрокосмического университета им. академика С.П. Королёва (национального исследовательского университета)
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