MATEC Web Conf.
Volume 70, 20162016 The 3rd International Conference on Manufacturing and Industrial Technologies
|Number of page(s)||6|
|Section||Power Machinery and Equipment|
|Published online||11 August 2016|
Numerical Simulation of Combustion Chamber for Button Turbojet Engine
School of Aerospace Science and Engineering, Beijing Institute of Technology, Beijing, 100081, China
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.
© The Authors, published by EDP Sciences, 2016
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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