支板火箭RBCC亚燃模态性能的影响因素（英文）

Influencing factors of strut-based RBCC performance in ramjet mode

针对2种扩张流道的RBCC燃烧室构型,通过三维数值模拟和地面直连试验,研究了燃烧室结构参数以及火焰稳定装置等对亚燃模态性能的影响。结果表明,第二级燃烧室采用较小的扩张角,有利于燃料的进一步燃烧,减小总压损失,燃料支板和凹腔火焰稳定器的共同使用,能有效提升燃烧室内的燃烧组织效果,扩展火焰的传播范围;直连试验验证了通过构型的改进,燃烧室性能得到大幅提高,压力积分推力增大了682 N。当凹腔距离燃料支板较近时,火箭关闭之后,燃料能够实现自持燃烧,比冲性能可提高50%。通过减小主支板宽度,在来流Ma=4时,能够更容易在隔离段中建立预燃激波系,保证亚燃燃烧反应更好地进行,燃烧室内推力提高了418 N。

Aiming at two expansion configurations of RBCC combustor,three-dimensional numerical simulation and ground tests were carried out to study the effects of structural parameters and flame stabilization devices on engine performance in ramjet mode. The results show that better combustion reaction and less total pressure loss can be achieved with a smaller expansion angle of the second combustor. Pylons for injection with cavities flame holder in each combustor can effectively enhance combustion of fuel and extend the range of flame propagation. The better performance of thrust increased by 682 N through configuration improvement has been verified with direct-connect test. Moreover,the sustained combustion of fuel after shutting down the rocket could be achieved when the cavities location is close to the pylons,in such a case the specific impulse has a nearly 50% increase with rocket off. Pre-combustion shock train can be more easily established in isolator by reducing the width of central strut at Ma = 4 and better reaction of subsonic combustion can be ensured,in this case the engine performance has improved by 418 N.