Zahra Ghahramani - Department of Mechanical Engineering, Science and Research Branch, Islamic Azad University, Tehran, Iran
Masoud Zareh - Department of Mechanical Engineering, Science and Research Branch, Islamic Azad University, Tehran, Iran
Hossein Pourfarzaneh - Designer head, Farzanegan Propulsion Systems Design Bureau, Iran Rasht
Farshad Pazooki - Department of Aerospace Engineering, Science and Research Branch, Islamic Azad University, Tehran, Iran

In this study, an annular combustion chamber of a turbojet engine with a net trust of ۱۶۵۰N is designed. Kerosene is considered as fuel in this study. The design consists of evaluation of the reference quantities, calculation of the required dimensions, estimation of air distribution and pressure drop, estimation of the number and diameter of air admission holes, as well as aerodynamic considerations. The design process is accompanied by Computational Fluid Dynamics (CFD) based on RANS simulation. Three-dimensional simulation of the reacting process within the combustion chamber is carried out based on the finite volume method. The RNG turbulent model and the finite rate/eddy dissipation combustion model are considered in the present study. Finally, the (atmospheric test) AT rig of the combustion chamber is explained. The Turbine Inlet Temperature (TIT) of combustion chamber is measured at different operating conditions. The TIT values in the numerical simulation and experimental measurement are ۱۱۹۱.۱K and ۱۲۲۷ K, respectively, in the design point. The SN and the angle of the RZ are equal to ۰.۹۹۵۵ and ۳۵.۲۶ degree, respectively. The temperature, velocity and pressure fields of RZ, air-fuel mixture, combustion turbulence are then presented in image outputs and graphs. The results indicate that the temperature distribution at the outlet of combustion chamber is relatively uniform.

Annular Combustion Chamber, Atmospheric Test (AT), ۳D Numerical Simulation, Swirler Number (SN)