Experimental analysis of the spreading of a liquid film on a bipropellant thruster chamber wall

In film cooling approaches, a of liquid fuel is formed on the chamber wall bipropellant thrusters to protect from high-temperature combustion gases. To optimize amount required sufficiently cool in this manner without degrading performance thrusters, formation process needs be understood. end, study, factors affecting spread were experimentally investigated. particular, experimental apparatus that could reproduce state jet being injected onto form was developed. Water used as test because hydrazine-derivative fuels, which are generally toxic, and density surface tension water similar those hydrazine. The processes visualized analyzed by using still camera. Results indicated velocity, nozzle diameter, impingement angle key width, maximum width exhibited linear relation velocity component perpendicular wall. Considering these results, general relationship between identified, it noted dimensionless defined product Weber number sine value angle. manner, can predicted when deciding injection conditions, assist thruster designers during design process.