液噴流の繰り返しパルス噴射が形成する液膜による加熱壁面の冷却

抄録

In a bipropellant thruster, a part of the liquid fuel is injected onto the combustion chamber wall to form a liquid film, which protect the wall from combustion gases. Particularly in the pulse operation, the fuel is injected onto a heated wall with temperature gradient formed by heat soak back from the nozzle throat. In this study, the transient processes of film formation and wall temperature distribution were visualized using a high-speed camera and an infrared camera, respectively, for a liquid film formed by a pulsed injection of liquid jet on a heated wall surface with temperature gradient. As a result of the analysis, knowledge about the liquid film behavior during the cooling and no-cooling periods was obtained.