STUDY OF THE FEATURES OF GAS FLOW BEHIND THE VORTEX BURNER OF THE COMBUSTION CHAMBER OF AN AIRCRAFT GAS TURBINE ENGINE

Currently, gas turbine engines are increasingly used as power units in the power industry, oil and gas industries, i.e., the process of converting aircraft gas turbine engines that have exhausted their flying resource into gas turbine installations for surface applications is underway. Therefore, the study of processes in the combustion chamber of aircraft gas turbine engines becomes particularly urgent. An analytical method for calculating the geometric and ejection characteristics of the gas-dynamic flow in the wake of the vortex burners is developed, which ensures the preparation of a homogeneous fuel-air mixture in the combustion chambers of air-jet engines and in other burner devices. The calculated model of the flow of coaxial, opposite swirling jets directly behind the cut of the burner in the zone of intensive circulation flow, where the combustion process stabilizes. The conditions under which it is possible to estimate the stability of combustion of a homogeneous mixture at the stage of design of vortex devices are shown.