关键词: 燃烧室宽度;液态燃料;旋转爆轰发动机;传播特性;推力性能

Abstract: In order to study the effects of the combustor width on the operating characteristic of the rotating detonation engine with liquid fuel， a gas-liquid two-phase rotating detonation experiment system was set up. The gasoline and oxygen enriched air were used as working substance， and the pre-detonation tube with hydrogen/oxygen was used as ignition device. A series of experiments were carried out under different combustor widths， the initiation process of detonation wave was analyzed， and the effects of combustor width on detonation wave propagation characteristic and thrust performance were studied. The experimental results show that the formation of self-propagating detonation wave requires a deflagration-to-detonation transition process after ignition. The detonation wave propagates in double wave collision mode under different combustion chamber widths， and the corresponding wave velocity is distributed in the range of 850~1025m/s. As a whole， the velocity increases with the increase of equivalent ratio. Meanwhile， when the combustion chamber width decreases， the wave velocity decreases. There are significant differences in thrust performance under different combustion chamber widths， in which the thrust and fuel specific impulse of the engine under 16.5mm are obviously lower than those of 11.5mm and 9mm. With the decrease of combustion chamber width， the inner and outer wall boundary layer plays a more prominent role in the flow field， which reduces the stability of engine thrust.

Key words: Chamber width;Liquid fuel;Rotating detonation engine;Propagation characteristic;Thrust performance