Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : October 09, 2021 - October 10, 2021
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.
