试验研究双旋流器头部燃烧室几何参数对燃烧性能影响

Experimental study of effects of geometric parameters on combustion performance of dual-stage swirler combustor

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要: 试验研究不同油气比下双级旋流器的几何参数以及主燃孔布局变化,对单头部试验燃烧室出口温度分布、燃烧效率、贫油熄火极限以及污染物排放等燃烧性能的影响规律.试验结果表明:双级旋流器的几何参数(如:叶片安装角、旋流器流通面积和喉道距文氏管出口距离等)与主燃孔布局变化对燃烧室性能都有较大的影响,但随着油气比的下降,影响程度相应地减弱.
- 航空、航天推进系统 /
- 燃烧 /
- 双旋流器 /
- 燃烧室 /
- 燃烧性能试验
Abstract: Under different fuel-air ratios, the effects of geometric parameters of dual-stage swirler and the arrangement of primary holes, on combustion performance(exit temperature distribution, combustion efficiency, lean blowout limit and pollutant emission) of single-head rectangle combustor are studied experimentally.The experimental results show that, the geometric parameters of dual-stage swirler and the arrangement of primary holes(swirler passage area, swirl vane angle of the primary and secondary swirler, the distance of the flare exit from throat, etc) have great influence upon the combustion performance of combustor, but the effects decrease with the reduction of fuel-air ratio.
- aerospace propulsion system /
- combustion /
- dual-stage swirler /
- combustor /
- combustion performance

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