摘要
研究了在燃烧室入口马赫数为２的超音速燃烧中，液体射流所产生的振荡激波对强化超音速燃烧的作用。经过一维分析，证明了在离燃料喷嘴适当位置上喷射液体，所产生的振荡激波能强化超音速燃烧，提高燃烧效率。并且还发现液体射流位置与燃料射流位置越近。
An experimental investigation on effects of oscillating shock generated by liquid jet on reinforcement of hydrogen-fueled supersonic combustion in Mach 2 airstream was completed.According to the one-dimensional calculation,it is found that supersonic combustion can be reinforced by the oscillating shock generated by liquid injection normal to supersonic flow at some distance from fuel injectors.And it is also discovered that the nearer the liquid injector is to the fuel injectors,the more combustion efficiency is enhanced by the oscillating shock.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1997年第1期56-60,共5页
Journal of Aerospace Power
基金
国家自然科学基金
