超燃冲压发动机燃烧流场及火焰稳定初步研究

Preliminary study on flame stabilization and combustion field of a scramjet combustor

采用壁面燃料喷射并结合凹槽设施作为火焰稳定器是超燃冲压发动机设计的理想方案,本文采用非定常数值模拟研究了带凹槽的超燃冲压发动机壁面横向喷射乙烯的火焰稳定过程。结果表明:在燃烧室入口马赫数2、静温530K、静压0.1MPa条件下,冷流流场达到稳定所需时间约为2ms;当凹槽内喷油当量比为0.1时,火焰稳定模式为燃料尾迹和凹槽共同形成的回流区稳定模式;当凹槽内喷油当量比为0.315时,火焰稳定模式完全处于凹槽回流区稳定模式;当凹槽前端壁面注油当量比为0.05时,火焰稳定模式为凹槽回流区稳焰模式;当凹槽前端壁面注油当量比为0.2时,火焰稳定模式为射流回流区和凹槽回流区稳焰模式。

Wall fuel jet injection with a cavity flameholder is a desirable configuration for a scramjet combustor. Process of flame stabilization of a scramjet combustor with ethene injection of cavity flameholder is studied by solving unsteady N-S equations and experiment. Results show that the cold flow field is in 2ms to achieve stability under the inflow air condition with Mach number 2.0, static temperature 530 K and static pressure 0.1MPa. The steady mode are jet-wake and cavity recirculation-zone stabilized combustion when the fuel/air ratio is 0.1 in the cavity, the steady mode is cavity recirculation-zone stabilized combustion when the fuel/air ratio is 0.315 in the cavity and the steady mode is cavity recirculation-zone stabilized combustion when the fuel/air ratio is 0.05 on the wall before the cavity. The steady mode is jet-wake and cavity recirculation-zone stabilized combustion when the fuel/air ratio is 0.2 on the wall before the cavity.