微型涡喷发动机燃烧室优化与试验研究

Optimization of Micro Turbojet Engine Combustor

关键词:  微型涡喷发动机  燃烧室  优化设计  试验

Key words:  Micro turbojet engine  Combustor  Design optimization  Experiment

摘要:

在微型涡喷发动机甩油盘式折流燃烧室自主设计的过程中，遇到由高转速向设计转速过渡时发动机骤熄的问题。通过对骤熄原因逐个排查并结合Fluent软件对不同转速下燃烧室流场的数值计算结果进行研究，最终查明问题缘由并开展针对性的优化。试验显示优化后的火焰筒成功解决燃烧室骤熄的问题，发动机各项性能达标。结果显示解决发动机骤熄的关键因素在于:维持头部多涡流场结构不变，主燃区进气量约32%，头部多采用密集并且直径小于2mm的小射流孔以及沿火焰筒轴向渐进式小气量供气。

Abstract:

During the independent designing process of the micro annular combustor with a slinger injector，sudden flameout was encountered when the rotation speed moved up from high speed to designing speed. The possible causes of this problem have been discussed and the combustor flow field under different rotation speed has been simulated using Fluent. Finally，the reason has been found out and the optimization has been carried out. This problem has been solved perfectly and the engine equipped with the optimized liner performs well and meets the all targets during the experiment. The results indicate that the key to solve sudden flameout lies in the multi-vortexes in the head of liner，about 32% of air flow in the primary zone，dense injecting holes with small diameter of less than 2mm and appropriate air flow distribution along the liner axis.