Super-Mixing High-Speed Combustion Enhanced by Unsteady Fuel Injection with Timescale of Micro Shear Layer

在人体超高速扩散燃烧的情况下，微剪切层形成接近行星喷嘴0.5的微剪切层。在1 mm的宽度被声学共振所刺激。对于非反应式喷气式飞机实验、Schlieren可视化和流量测量，通过一个热线动画仪显示，以湍流为标记的放大被诱导为频率的声学刺激，使nozzle-exit velocity。类似地，用于反应喷气式飞机演示的视觉观测、温度和浓度测量在共振条件下具有很大的增强性。由于飞机喷气机从0.5的喷嘴中射入。宽度为1毫米，声学刺激已被应用。在所有非反应和反应的喷气机中，共振的现象都是清楚地确认的。对于共振条件来说，中风的数目几乎是每个情况下的常数，但在很大程度上取决于反应或非反应条件。在目前的实验中观察到的戏剧性变化被归类为声学刺激和微剪切层的组合。

In order to embody extremely high-speed diffusion combustion, micro shear layers formed near the planar nozzle of 0.5。ォ1 mm in width were excited by acoustic resonance. For nonreacting jet experiments, Schlieren visualization and flow measurement by a hot-wire anemometer show that the marked amplification of turbulence is induced by the acoustic excitation with the frequencies proportional to the nozzle-exit velocity. Analogously, visual observation, temperature and concentration measurements for the reacting jet demonstrate that combustion is much enhanced under the resonant condition. For the planar jets injected from the nozzles of 0.5。ォ1 mm in width, acoustic excitation was applied. In both the nonreacting and reacting jets, resonant phenomena were clearly confirmed. The Strouhal number for the resonant condition was almost constant for each case, but varies largely depending on reacting or nonreacting conditions. The dramatic changes observed in the present experiments are ascribed to the combination of acoustic excitation and micro shear layers.