用小支板及凹腔组合提高火箭冲压组合发动机的燃烧性能

为了研究RBCC亚燃模态的高效稳定燃烧,对小支板及凹腔结合的火焰稳定及燃烧组织方式进行多次试验研究,结果表明,凹腔与支板的火焰稳定及燃烧组织方式能有效地改善燃料的燃烧性能,提升燃烧室压强,凹腔与支板相对位置对燃烧的放热位置及燃烧性能也有影响。为了进一步研究燃烧流场内部参数变化,选取其中一种试验工况进行数值模拟,结果表明,在RBCC混合燃烧模式中,采用支板与凹腔组合的火焰组织及稳定方式,能够在较短距离实现煤油的高效燃烧,获得较好的燃烧性能,并且可以从中发现热力喉道的形成与凹腔的后斜壁收缩有关联,在实现稳定高效燃烧的条件下,获得直扩的双模态燃烧室内较为稳定的热力喉道。

Combustion Performance of RBCC Engine with Pylon and Cavity at Ramjet Mode

In order to investigate the effective combustion performance in ramjet mode of RBCC,the pylon with cavity was disposed in the chamber of RBCC,and some experiments were taken on the direct-connect experiment system.Through the study,it is showed that the pylon with cavity can improve the combustion performance of fuel and increase the chamber pressure.The results also exhibit that the positions of cavity and pylon in the combustor also affect the combustion performance.For studying more parameters in the combustion flow,one experiment was selected into numerical simulation.Based on the computation results,it shows that the pylon with cavity improves the combustion stabilization,and it provides robust combustion efficiency and wide operability liquid hydrocarbon.And the thermal throat is connected with the rear ramp.It is indicated that good combustion performance can bring thermal throat after cavity.