摘要
在双级旋流多点喷射直接混合(TAMDIM)高温升燃烧室单头部试验件上进行了燃烧效率试验,对比了两种不同主副级喉道间距尺寸下的慢车主、副分级供油方案及副油路单独供油方案的燃烧效率,分析了不同主、副级当量比(副油路供油比例分别为40%,56%,65%,100%)及喉道间距对燃烧效率的影响.试验表明:主副级采用分级供油策略时,喉道间距对燃烧效率有显著影响,喉道间距设计为19.3mm,副油路供油比例控制在40%~56%,可以获得比单独副油路供油更好的燃烧效率.在扇形试验件上进行了试验验证,进一步验证了慢车分级供油策略在TAMDIM高温升燃烧室上的可行性.
The combustion efficiency test was done on the single dome test piece of twin annular multi-point direct injection mixing （TAMDIM） high-temperature rise combustor, the idle combustion efficiency of two stages-fueled together mode and the pilot-fueled only mode with two different throat spacing sizes were compared, and the influence of different main and pilot equivalents （the pilot fuel ratio of 40%, 56%, 65%, 100%） and throat spacing size on the combustion efficiency were analyzed. Test results show that, the throat spacing size has a great influence on the combustion efficiency when taking the two stages-fueled together mode, compared with the pilot-fueled only mode, better combustion efficiency has been obtained when the spacing of throat is 19.3 mm and the pilot fuel ratio is within the range of 40%-56%. Validated test has been done on the sector test piece finally, ulteriorly verifying the feasibility of fuel stage under idle condition in the TAMDIM high-temperature rise combustor.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2017年第3期577-583,共7页
Journal of Aerospace Power
关键词
燃烧室
高温升
燃油分级
慢车
燃烧效率
combustor
high-temperature rise
fuel stage
idle condition
combustion efficiency
