Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : October 22, 2016 - October 23, 2016
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.
