【作者】 叶超；

【导师】 何小民；

【作者基本信息】 南京航空航天大学 ， 热能工程， 2008， 硕士

【摘要】 为改善某型冲压发动机燃烧室的燃烧性能,本文对燃烧室火焰稳定器系统和供油系统的相关部件进行了方案设计,运用FLUENT软件对带火焰稳定器的燃烧室流场和油雾场进行了数值计算,最后进行了模型试验验证。火焰稳定器系统包括薄膜蒸发型值班稳定器、径向稳定器、V型稳定器以及传焰槽。值班稳定器设计一套油路独立供油,主流采用分区和分压相结合的供油方式,含主副两套油路,并对副油路进行分区设计,适合大范围工作。通过数值研究得到了燃烧室流场特性(包括流阻损失系数、燃烧室各区域的流量分配以及流场速度矢量图),得到了特定状态下的油雾场分布。初步验证了部件设计方案在流动和油雾特征上的可行性。试验研究表明:主要结构参数的设计值均处于最佳设计范围,可以保证燃烧的稳定和完全;常压下燃烧效率超过90%,燃烧效率随压力变化最为明显,压力降低,燃烧效率下降;典型的组合工况下,燃烧室点火油气比在0.008左右,贫油熄火油气比在0.006左右。点火、熄火性能随流动参数变化不大,主要取决于值班稳定器的结构参数。研究成果为冲压燃烧室的研制和定型提供了依据。更多还原

【Abstract】 In order to improve the performance of a ramjet combustor, flameholder and fuel system components were designed in this paper. Numerical and experiment investigation were also carried out to explore the performance of the combustor based on the components design.According to the design, flameholder system including film vapor flameholder、V-gutter flameholder and flame passage was given. A separate fuel system was designed for the film vapor flameholder. The main stream fuel was supplied by different zones and fuel pressures, and the system regulation range can reach 0.0860 to 3.2746kg/s.The complex flow filed of the combustor was numerically simulated by using the commercial CFD (Computational Fluid Dynamics) software named FLUENT in the paper. The flow pattern、mass flow distribution、flow drag performance and fuel spray characteristics were obtained and analyzed in detail. The results show that the components design was acceptable.Finally, the combustion performance including ignition、lean blow out performance and combustion efficiency were experimentally investigated at normal and low pressure. The experiment result show that the combustion efficiency can reach over 90% at normal pressure. In addition, the ignition and lean blow out performance were mainly depended on the structural parameters of film vapor flameholder at typical combined working conditions.The paper can provide basis for the development of ramjet combustor.更多还原