Numerical Study of CH4/LOx Combustion of Shear-coaxial Injector in High Pressure Combustion Chamber of Liquid Rocket

액체로켓 동축인젝터(CH4/LOx)의 고압 연소실 내 연소 유동장에 대한 수치적 연구

High pressure combustion with multiphase--liquid, gas, and supercritical phase--mixtures are widely used technology in the high efficiency liquid propellent rocket engine. This is the typical characteristics differentiate from the combustor of conventional air-breathing engines. Therefore, successful research of high pressure combustion at supercritical condition is essential to develope a high efficiency liquid rocket engine. Numerical studies have been carried out to explore capabilities of numerical method for LOx-CH4 non-premixed flames at high pressure. In this paper, corresponding numerical results are presented and compared with experimental result of MASCOTTE facility.