Numerical Simulation of Combustion Chamber for Button Turbojet Engine

School of Aerospace Science and Engineering, Beijing Institute of Technology, Beijing, 100081, China

Abstract

To provide reference data for ultra-micro combustor, a new type button turbojet engine was designed and simulated the combustion’s steady-state process. The boundary condition of inlet was calculated using isentropic numerical calculation, taken into turbulent chemical reaction, heat radiation, and so on, getting the combustion chamber’s steady-state of the velocity, temperature and component concentration distribution, analysis the fuel/air flow and backflow, combustion efficiency and total pressure recovery coefficient, and compared with the experimental data. The calculation results can accurately reflect the actual combustion. The results show that combustion chamber exit velocity is about 65m/s, outlet temperature is around 1000K, the simulation and experimental data are similar, combustion chamber structure design is reasonable, and this paper will provide a basis for the future improvement of the millimeter scale turbojet engine.