不同旋流器方案下旋流驻涡燃烧室性能  

Performance of swirling-flow single trapped vortex combustor under different swirler schemes

作　　者：张秋峰 何小民 龚诚 郭煜玺 于镇潭 ZHANG Qiufeng;HE Xiaomin;GONG Cheng;GUO Yuxi;YU Zhentan(Jiangsu Province Key Laboratory of Aerospace Power System,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Aerospace Technology Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016 [2]中国空气动力研究与发展中心空天技术研究所,四川绵阳621000

出　　处：《航空动力学报》2023年第7期1773-1783,共11页Journal of Aerospace Power

摘　　要：为研究旋流驻涡燃烧室的燃烧性能,设计了3种旋流器方案(基准型、小流通面积和外加套筒),在进口温度493 K、常压条件下,采用RP-3航空煤油作为燃料,凹腔当量比在0.8~1.8之间,开展了热态试验。结果表明:基准型和小流通面积的主燃区火焰为脱体火焰,而外加套筒则为V型驻定火焰,且小流通面积和加套筒的主燃区火焰更加集中。燃烧效率方面,基准型最低,而小流通面积最高,试验中获得的最高燃烧效率为96.3%。随着凹腔当量比的增加,基准型的燃烧效率不断增加,而小流通面积的则先基本不变,随后略有增加,外加套筒的则先快速增加,然后缓慢增加。此外,小流通面积的冷态总压损失高于基准型,在进口马赫数为0.31时,两者的冷态总压损失分别为7.2%和4.5%。To investigate the combustion performance of swirling-flow single trapped vortex combustor,three swirler schemes(baseline type,small flow area and additional flare)were designed and thermal tests were carried out at an inlet temperature of 493 K and at atmospheric pressure,using RP-3 aviation kerosene as fuel and a cavity equivalent ratio between 0.8 and 1.8.Results showed that the flame in the main combustion zone of the baseline and small flow area schemes was a deconfined flame,while that of the plus flare scheme was a V-shaped standing flame,and the flame in the main combustion zone of the small flow area and plus flare schemes was more concentrated.In terms of combustion efficiency,the base type scheme was the lowest while the small flow area scheme was the highest,and the highest combustion efficiency obtained in the test was 96.3%.The combustion efficiency of the baseline model increased with the increase of the cavity equivalent ratio,while that of the small flow area solution remained basically the same at first and then increased slightly,and that of the plus flare solution increased rapidly and then slowly.The total pressure loss of the small circulation area scheme was higher than that of the baseline type,which was 7.2%and 4.5%respectively,at an inlet Mach number of 0.31.

关 键 词：旋流驻涡燃烧室 旋流器结构方案 火焰形态 燃烧效率 温度分布 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]