D. Smitha, M. R. S. Satyanarayana, Sachin Srivastava
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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.
期刊介绍：
Aerospace Systems provides an international, peer-reviewed forum which focuses on system-level research and development regarding aeronautics and astronautics. The journal emphasizes the unique role and increasing importance of informatics on aerospace. It fills a gap in current publishing coverage from outer space vehicles to atmospheric vehicles by highlighting interdisciplinary science, technology and engineering.
Potential topics include, but are not limited to:
Trans-space vehicle systems design and integration
Air vehicle systems
Space vehicle systems
Near-space vehicle systems
Aerospace robotics and unmanned system
Communication, navigation and surveillance
Aerodynamics and aircraft design
Dynamics and control
Aerospace propulsion
Avionics system
Opto-electronic system
Air traffic management
Earth observation
Deep space exploration
Bionic micro-aircraft/spacecraft
Intelligent sensing and Information fusion
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