Cold Flow 2D Axis-Symmetric Numerical Analysis and Modification of Combustion Chamber of Small Turbojet Engine
Nowadays, ITB Aeronautics and Astronautics propulsion laboratory is developing a 500 N turbojet engine. This engine will be used to generate thrust for high speed UAV. The first generation of this engine has been successfully manufactured, but a problem occurs during the testing. The problem is that the flame occurs outside the nozzle. A 2D axis-symmetric simulation of the combustion chamber was carried out using CFD software to find out the causes. Modifications have been made to the combustion chamber geometry after the causes were found. From these modified models, the parameters data such as liner length, liner cross-sectional area, curvature of the front liner, front holes position, and the number of front holes which influenced the flow behavior were obtained. A modified model that shows the best flow behavior would be the initial design for the next generation 500 N turbojet engine combustion chamber.
Numerical analysis 2D axis-symmetric Cold flow Combustion chamber
S. Rahardianto F. Hartono
Aeronautics and Astronautics Study Program Institut Teknologi Bandung, Bandung, INDONESIA
国际会议
The 7th International Conference on Fluid and Thermal Energy Conversion(第七届流动技术与热能转化国际会议 FTEC 2011)
郑州
英文
365-372
2011-09-24（万方平台首次上网日期，不代表论文的发表时间）