An Extended Combustion Model for the Aircraft Turbojet Engine

Abstract

The paper consists in modelling and simulation of the combustion in a turbojet engine in order to find optimal characteristics of the burning process and the optimal shape of combustion chambers. The main focus of this paper is to find a new configuration of the aircraft engine combustion chambers, namely an engine with two main combustion chambers, one on the same position like in classical configuration, between compressor and turbine and the other, placed behind the turbine but not performing the role of the afterburning. 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 by extracting the flow stream after turbine in the inner nozzle. Also, a higher thermodynamic cycle efficiency and thrust in comparison to traditional constant-pressure combustion gas turbine engines could be obtained.

Mathematical Model and CFD Analysis of Partially Premixed Combustion in a Turbojet

“…If the external flow can be assumed irrotational, a single scalar potential equation may be used and the correction perturbation to this inviscid outer flow may be obtained from linearized theory (in transonic flow some perturbation potential must be solved throughout the flow). The conventional boundary layer approach leads to a parabolic system of equations but the interacted boundary layer is not well posed as an initial value condition [4].…”

Numerical Investigation of Turbojet Engine Thrust Correlated With the Combustion Chamber's Parameters

“…Performance Analysis of Turbojet Engine, also referred as Thermodynamic Analysis supposes the completion of three phases; thorough details are given in literature, Mattingly [1], as well as authors other researches, Andrei [8][9][10][11][12][13][14][15][17][18], Rotaru [21][22][23] and Prisacariu [16].…”

Analysis of turbojet combustion chamber performances based on flow field simplified mathematical model

“…Excepting the case of incompressible flow with small temperature differences, it becomes necessary to determine the variation of the density across the boundary layer. Since the static pressure is constant across the boundary layer, the gas law gives the product of local density and local temperature as constant, thus the problem becomes one of specifying the local temperature [3].…”