A Study on Development of Numerical Treatment of Atomization and Combustion in a Rocket Engine Injector Flow

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In a liquid rocket engine, mixing process affects on the stability of combustion, and the process is strongly depends on pressure in a combustion chamber. In this research, I have studied development of numerical method to investigate combustion phenomena in a rocket engine coaxial injector flow. The final target of this activity is to include vaporization of liquid oxygen in a numerical treatment. A detailed chemical kinetic model in hydrogen/oxygen system applicable to rocket engine combustion is proposed, and a stable time integration method of the detailed kinetic mechanism in a flow analysis is also proposed. The deformation of an oxygen droplet in a hydrogen stream and its mixing behavior is numerically studied. Numerical results showed that flow field and mixing process is divided into two patterns, depending on Reynolds number. When an ambient pressure becomes high, the deformation of the droplet becomes rapid and the separation behind the droplet developed significantly.