Research On The Flame-stabilizing Technology Based On A Cavity In High Speed Flow

The flame-Stabilizing technology based on cavity in supersonic combustion was studied systematically and comprehensively.The main idea of this study with domestic and foreign research is the key point of difference:the latter is that the fuel injected into the Supersonic flow before it is in the cavity ,or ignition of fuel injected into the cavity. For two types of fuel injected into the way, the cavity recirculation zone only to return as a high-temperature flue gas heat to play on the flame stability of the Supersonic flow. Not only streaming the fuel into the Supersonic flow, but also injecting a small amount of fuel with the corresponding air into the cavity. It depend on the three inherent attributes of the recirculation zone which are high temperature, low-speed and high turbulence, so that the introduction of small amount of fuel and air which is in the cavity immediately become duty flame ignition and then it can ignite hypersonic mainstream. A small amount of fuel which it has burned is cited access to the cavity by the deflector in the experimental. Then it has a higher temperature to ignite the mainstream of the fuel and air mixture. Therefore, combustion stabilizes in a better position.Aerodynamic wind tunnel experiments are carried out one of the basic equipment. So far most of the aerodynamic experiments were completed in the wind tunnel. The characteristics of supersonic wind tunnel is that it must have a Laval nozzle which can generate a supersonic flow by uniform and one shape of the nozzle must correspond to one mach number. And the streamline-shaped of the nozzle have played the role of uncertainty to mach number of the supersonic flow. In this paper, we design the flow line of a temporary wind-tunnel nozzle to get the supersonic flow which the mach number is two for the stability of combustion experiments in the cavity.