摘要
通过碳氢燃料亚燃冲压发动机直连式试验,对凹腔火焰稳定器的点火性能进行了初步研究。试验分别在高能火花塞及氢气引导火焰两种情况下成功实现了可靠点火。结果表明,基于凹腔火焰稳定技术的亚燃冲压发动机的点火性能与燃料喷注压降及喷注方式密切相关。在壁面喷注燃料的方式下,发动机容易实现可靠点火,而在中心喷注燃料的情况下,发动机很难被点燃。此外,试验还发现,发动机的喉部尺寸对采用这类结构的亚燃冲压发动机凹腔内的压力影响较小,因此,喉部尺寸的变化对其点火性能的影响也较小。
Experimental investigations on the ignition characteristics of liquid hydrocarbon fuel ramjet with cavity based flameholder were conducted using a ground direct-connect test combustor. Successful ignition was achieved using high energy spark igniter and hydrogen pilot flames respectively. The results suggest that the ignition technique is closely related to the injection pressure drop and injection mode. Based on the wall injection mode, successful ignition is easily achieved, while based on the center injection mode, ignition is hard to reach. Meantime it is found that the size of the throat can hardly influence the static pressure in the cavity based on the structure illustrated. In that ease, the effect of the size of the throat towards the ignition characteristics is small.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2009年第4期1600-1605,共6页
Journal of Astronautics
