摘要
在双支板超燃燃烧室的直连试验中,以液体煤油为燃料,针对上游支板上的3个喷注位置对燃烧的影响进行了研究.在试验过程中获得了壁面压力数据,并通过一维冲量分析法处理.试验结果表明：煤油在两支板同时喷注时,热力喉道的位置受上游支板喷注位置显著影响.在上游支板的3个喷注位置中,第1,2位置分别喷注时超燃燃烧室压力分布基本相同,与第3位置喷注相比燃烧效率高6.3%-7.5%,内推力高16.7%-17.4%.试验的结果表明,在第1位置喷注时燃料能够在上游维持燃烧,但第3位置喷注时燃料无法在上游维持燃烧.结合数值仿真的结果分析,上游支板上的喷注位置到支板尾缘的距离L≥80mm时,燃料在支板尾缘处有较高的混合效率并形成稳定的燃烧.
Directly-connected test on dual-struts supersonic combustor fueled by liquid kerosene was made to test the influence of three different injection locations in upstream strut on combustion.The wall pressures were processed by one-dimensional impulse analysis method.Results showed that the position of thermal coking was influenced by the injection location in the upstream strut.Moreover,when fuel was injected respectively from the first and the second positions in upstream strut,the wall pressure distributions were nearly the same,but 6.3%-7.5%and 16.7%-17.4% higher than from the third injection location in conbustion efficiency and in thrust separately.Test results showed that fuel injected from the first injection position in the upstream strut could hold steady combustion but couldn＇t do from the third one.The results of simulation showed that the fuel had a high mixing efficiency with the air combusted steadily when the L≥80mm,where L was the distance between injection position and trail of strut.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2016年第11期2613-2620,共8页
Journal of Aerospace Power
