Circumferential Distortion (Temperature) Reduction of a Small-Size Gas Turbine Engine Combustion Chamber by Numerical Experimentation

In this article the features of modeling the physicochemical processes in the small-size gas turbine engine combustion chamber are considered: liquid kerosene spray, evaporation, fuel-air mixture formation, ignition, incomplete combustion (with the combustion products) and coupled heat transfer (convection, thermal conductivity, radiation) in three-dimensional setting by the control volume method in Ansys CFX. As a result of simulation, the temperature field formation of the gas flow in front of the turbine is analyzed. The effect of the flame tube openings diameters on the penetration depth of the secondary air flow is studied. By shifting the areas of the flame tube openings, the best options have been obtained that ensure a maximum temperature decrease and its circumferential distortion in front of the turbine. The methods described in this article can be widely used in evaluating the impact of structural changes on temperature field distortion at the combustion chamber outlet of gas turbine engines