摘要
针对超燃冲压发动机在较低飞行M数(M0≤4)下的起动点火问题,利用氢氧燃烧加热脉冲风洞,在超声速燃烧室进口M数M=2、总温T0=960K条件下,分别采用等离子体点火器+先锋氢燃料和大功率等离子体点火器,探索了在超声速燃烧室中,实现煤油点火和稳定燃烧的方法。采用等离子体点火、凹槽火焰稳定器和从壁面喷射燃料方式,实现了煤油的可靠点火和稳定燃烧。研究表明,在燃烧室进口M=2、总温T0=960K时,采用大功率等离子体点火器,不需要先锋燃料,可以直接点燃煤油。
The start ignition problem for scramjet operating in lower flight Mach number （M0 ≤4） is concemod in the paper. The method for kerosene ignition and flame stabilization in supersonic combustor is explored in hydrogen-oxygen combustion impulse wind tunnel. The entrance of supersonic combustor is at Mach number 2, total temperature about 960K. The plasma igniter with pilot-hydrogen and high-power plasma igniter are adopted in the direct-connected experiment of supersonic combustor. The successful kerosene ignition and flame stabilization is obtained by using plasma ignition, cavity flameholder and wall injection fuel. The experimental results indicate that kerosene can be ignited directly with high-power plasma igniter and without pilotfuel at entrance stagnation temperature 960K, Mach number 2.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2006年第4期20-24,共5页
Journal of Experiments in Fluid Mechanics
基金
航天科技创新基金(N4CH0007)
