Numerical study and performance analysis of an annular combustion chamber using methane and oxygen as propellant

A highly efficient combustion chamber is always desired for high performance from jet engines/rocket engines. This paper presents the novel numerical analysis method for optimizing the combustion characteristics of methane (CH₄) in an annular combustion chamber, achieving a maximum exit velocity nearly Mach 5. The velocity achieved is 1650 m/s, which is approximately 5 times of Mach number. The dimension of combustion chamber, length is 100 mm, diameter is 60 mm. Pre-combustion and post-combustion chamber length is 30 mm and 45 mm respectively. The port diameter is 16.5 mm and 4 injectors are used in this case. The main purpose of this paper is to investigate the optimize the combustion of solid fuel and air and justify the numerical model by using a 3D RANS simulation.