Parallel Computational Fluid Dynamics 2006

Parallel Numerical Simulation of Shear Coaxial LOX/GH₂ Jet Flame in Rocket Engine Combustor

S. Matsuyama^a; J. Shinjo^a; Y. Mizobuchi^a; S. Ogawa^a    a Institute of Aerospace Technology, Japan Aerospace Exploration Agency, 7-44-1 Jindaiji-higashi, Chofu, Tokyo 182-8522 Japan

Keywords

Combustion

Liquid Rocket engine

1 INTRODUCTION

Liquid rocket engines are used in a number of launch vehicles worldwide. In these rocket engines, e.g. LE-7A engine of H-2A, Space Shuttle Main Engine (SSME) and Vulcain engine of ARIANE 5, liquid oxygen (LOX) and gaseous hydrogen (GH₂) are injected through coaxial injectors (a schematic is shown in Fig.1). Although the injector design is a critical component of the combustion device, the processes associated with LOX/GH₂ injection, ...