高圧メタン酸素ロケット噴射器近傍の非定常燃焼流れ場構㐀：詳細反応機構を用 いた CFD 解析

抄録

Detailed structures of gaseous CH₄/O₂ combustion flow fields behind a GOX post of rocket engines have been numerically investigated by using the Navier-Stokes equations with a detailed chemical kinetic model. The results show that the two types of combustion flow structures are established in the region behind the GOX post according to CH₄ and O₂ jet injection conditions. A broad higher-temperature region appears with a single anticlockwise recirculation region for larger velocity ratios of CH₄ to O₂ jets, while a lower-temperature region is formed with the presence of non-premixed flame structures and additional generations of another clockwise recirculation region for smaller velocity ratios.