RBCC亚燃模态点火及火焰稳定研究(英文)

Investigation of ignition and flame stability in RBCC ramjet mode

在直联式燃烧试验台上进行了基于机械壅塞的RBCC亚燃模态点火及火焰稳定研究,试验模拟飞行马赫数为2.5,采用扩张型双模态燃烧室和多级JP-10喷注方式。在主火箭工作的情况下,借助发动机出口机械壅塞的方式实现了点火和火焰稳定。同时发现火焰稳定与乙烯引导火焰无关,出口堵塞比是燃烧室压力提升的一个重要影响因素。研究工作为实现基于热力喉道的RBCC亚燃模态稳定高效燃烧提供了良好的基础。

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.