摘要
建立了采用连续式电阻加热器的超声速燃烧室直连式试验平台,介绍了该试验平台的调试结果,可以满足飞行马赫数约3.0~4.5时进行超声速燃烧的试验要求.自行设计了采用凹槽火焰稳定器的超声速燃烧室试验模型,在超声速燃烧室直连式试验平台上,进行了来流总温约1 000 K,马赫数约2.0条件下氢气燃料的燃烧试验,研究了氢气与来流空气的当量油气比对超声速燃烧室内燃烧情况的影响.并在此基础上开展了氢气引燃煤油的点火试验研究,研究了氢气和煤油的喷射位置、喷孔直径等对煤油点火性能的影响.
A unique supersonic wind tunnel facility using resistance heaters has been built to simulate the operation of a scramjet over a range of Mach numbers of 3.0 to 4.5. A number of preliminary experiments results from calibration of both the facility and the vari- ous components were introduced. Based on the previous experience and the experimental results published worldwide, a new eombustor configuration using cavity flame holder to create recirculation and promote the fuel/air mixing has been developed. And the combustion characteristics of the hydrogen have been investigated in the supersonic clean airstreams experimental facility. The effect of the hydrogen fuel equivalence ratio on the flame holding mechanism and combustion was studied. Furthermore, the ignition characteristics of kerosene using hydrogen pilot have been investigated. The effect of the injection locations and diameters on the kerosene combustion was also presented.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第12期2268-2273,共6页
Journal of Aerospace Power
