Aspects Regarding Aerodynamic Shape of Turbojet Combustion Chamber

This paper deals with the modelling and flow simulation in the combustion chamber of a turbojet engine in order to find the optimal velocity, pressure and temperature distributions in the flame tube and in front of the turbine. 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. The main focus of this paper consists in finding a new geometrical model of the aircraft engine combustion chamber with an optimal distribution of gas parameters in front of the turbine, that 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.