双燃烧室冲压发动机亚燃室设计与实验研究  

Design Improvement and Validation of Subsonic Combustor Pilot Burner for Dual Combustor Ramjet

作　　者：杨占宇[1] 单鹏[1] 郭德三[1] 赵吕顺[1] 介克[1] 刘建[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《推进技术》2013年第1期69-75,共7页Journal of Propulsion Technology

基　　金：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)

摘　　要：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 this paper presents the design improvement with the numerical Mach number 2.5, total temperature 285K, 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 dis- charge-passage cross-sectional-area of the lobed mixer and the V-belt flame holder, rearrange the air distri- bution 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.

关 键 词：超声速流动 超声速燃烧 双燃室冲压发动机 预燃室 稳焰火炬 

分 类 号：V235.211[航空宇航科学与技术—航空宇航推进理论与工程]