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This paper deals with the modelling and simulation of the combustion in a turbojet engine in order to find the velocity distribution in the secondary zone of the flame tube. The Arrhenius relationship, which describes the basic dependencies of the reaction rate on pressure, temperature and concentration, has been used. Also, combustion efficiency has been defined and related to both the exhaust temperature and species concentration. Premixed laminar flames and the dependence of propagation rate on temperature and the fuel-air ratio have been highlighted. The main focus of this paper consists in a new configuration of the aircraft engine combustion chamber with an optimal distribution of gas velocity in front of the turbine. This constructive solution could allow a lower engine rotational speed, a lower temperature in front of the first stage of the turbine and the possibility to increase the turbine pressure ratio. Also, a higher thermodynamic cycle efficiency and thrust in comparison to traditional constant-pressure combustion gas turbine engines could be obtained.

ASPECTS REGARDING VELOCITY DISTRIBUTION IN THE SECONDARY ZONE OF A GAS TURBINE COMBUSTOR