Investigation of ignition and flame stability in RBCC ramjet mode

The experimental investigation of mechanical-chocking-aided ignition and flame stability in RBCC ramjet mode was carried out on a direct-connect combustor experimental bench. The simulated flight Mach number is 2.5. The combustor is a dual-mode expansion combustor with multi-stage JP-10 injection. A reliable ignition was implemented with mechanical chocking at the engine exit when the primary rocket is working. Flame stability has no relation with the ethylene guide flame, and the exit chocking ratio is an important factor for the combustor pressure rising. The investigation lays a fine foundation for realizing stable high efficient combustion based on the thermal throat RBCC ramjet mode.