#TITLE_ALTERNATIVE#

• Main Author: CHAFID ASYARY (NIM : 13613047), ACHMAD
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/20691
• Institution: Institut Teknologi Bandung

The development of very light jet aircraft (VLJ) encourages engineer to develop small, high-performance engines. Combustion chamber is an important component in addition to compressor and turbine that have a major impact on aircraft engine performance. Thus, the development of aircraft engine is inseparable from the development of the combustion chamber. Reverse flow combustion chamber offers a short shaft usage between compressor and turbine with ease of access of the fuel injector. This final project report discusses a reverse flow combustion chamber design for small size turbojet engines. Design point parameters that required in the design process such as compressor and turbine performance and dimensions of compressor outlet and turbine inlet are obtained from previous research. Design method is based on aerodynamic phenomena that occur in the combustion chamber or usually called aerodynamic design of the combustion chamber. Dimension of combustion chamber such as length and diameter are obtained by processing the design point parameters with aerodynamic design method. Liner’s hole is designed base on cranfield method and trial and error method. 3 dimensional model of combustion chamber geometry is made with CATIA software and performed numerical simulations using ANSYS CFD software. The result of combustion chamber simulation shows that there is a 14.8% total pressure loss relative to the inlet total pressure. The total pressure loss relative to the inlet total pressure is greater than the straight flow combustion chamber and outlet temperature profile is not quite ideal yet. However, the uniformity of the overall temperature as well as in the radial direction shows good results with the pattern factor and profile factor values less than 0.1 and high combustion efficiency with the fuel entirely burned.