在来流马赫数2.5,总温为285K的条件下,对于带亚燃预燃和流向涡掺混的超声速双燃烧室的亚燃室,进行了计算流体力学正问题设计研究以及实验验证研究。结果表明,亚燃室通过采用内压式三波系进气道、前部集中式主燃孔的火焰筒、增大了的亚燃室体积和火炬流喷口截面积、增设的V型火焰稳定器,使亚燃室内流场组织合理,解决了进气道的热态失速问题,得到了稳定的亚燃室燃烧和达到设计状态的火炬流喷射。 

Under the testbed condition of combustor inlet Mach number 2.5, total temperature 285K, this paper presents the design improvement with the numerical simulation of the cold flowfield and the experimental validation of the pilot burner of a direct-connected combined supersonic combustor with a streamwise vortices generator. The results indicate that, the design improvements, such as the triple-shock inlet, the burner liner with concentrated frontal holes, the pilot burner with a rather larger volume, the larger discharge-passage cross-sectional-area of the lobed mixer and the V-belt flame holder, rearrange the air distribution in the rectangular pilot burner and resolve the problem of the inlet stall during pre-combustion. The experiment obtains a stable pre-combustion and a torch plume achieving the design goal.

国家自然科学基金 (50076003);国家自然科学基金重大研究计划子课题(90305010)。