Features of the Combustion Chamber Development for a Small-Sized Turbojet Engine

Abstract

The paper presents approaches to the development of the small-sized gas turbine engines combustion chambers. Schemes of currently used combustion chambers are given. Particular attention is paid to determining the amount of air entering the combustion chamber primary zone. A forecast of the gas temperature changes in front of the turbine is given, taking into account the actual completeness of fuel combustion with an increase in fuel supply in excess of the calculated optimal values.