Research Unit III, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Research Unit III, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Research Unit III, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Research Unit III, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
48th Fluid Dynamics Conference /the 34th Aerospace Numerical Simulation Symposium (July 6-8, 2016. The Kanazawa Theatre), Kanazawa, Ishikawa, Japan
抄録（英）
A feasibility study of the interface tracking simulations of liquid oxygen (LOX) and gaseous hydrogen(GH2) coaxial combustion at a subcritical pressure was conducted. To simulate the breakup and atomization of LOX core, CIP-LSM (Constrained Interpolation Profile based Level Set and MARS) that combined CIP-CUP (CIP-Combined Unified Procedure) method with the hybrid Level-set and MARS (Multi-interface Advection and Reconstruction Solver) method for volume tracking, was employed as a solver of the governing equations of fluids. The phase change rate on the surfaces between the multi-species gas and single-species liquid was calculated. To investigate the ignition process and flame holding mechanism, chemical reaction equations were solved with the detailed chemical mechanism of oxygen and hydrogen. Results suggested that this numerical approach can be a powerful method that provides the information on ignition, breakup and atomization of LOX core, and flame holding at the steady state of LOX/GH2 coaxial combustion at subcritical pressures.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
界面捕獲法を用いた液体ロケットエンジン亜臨界圧燃焼流解析
AA1630031027.pdf
(8.67MB)
