Selecting cooling techniques for liquid rockets for spacecraft

Visualization of Coolant Liquid Film Dynamics in Hypergolic Bipropellant Thruster

“…As schematically depicted in Fig. 1, the chamber wall must tolerate heat transfer from the hot combustion gas, exceeding 3000K; thus, a filmcooling technique is widely employed by extending a thin liquid film on the chamber inner surface by directly impinging fuel jets and spreading along as a liquid film [15]. The liquid film produced on the chamber wall elongates downstream with evaporation, developing to a certain length at the balancing point between the heat input and the latent heat, reaching a steady state at last.…”

Computational Investigation of Impingement Cooling for Regeneratively Cooled Rocket Nozzles

“…The main advantages for using regenerative cooling are its long, continuous run time, negligible heat loss, and light weight structure. Therefore, it is found to be best used for high thrust propulsion engines, such as the SSME (Coulbert, 1964). particularly at the nozzle throat where the heat load is highest, more innovative techniques must be also studied.…”

Thermal protection of rocket nozzle by using film cooling technology - effect of lateral curvature

“…Efficient cooling methods are necessary in order to reduce thermal loads and insure reliability of rocket engines. Cooling techniques such as regenerative cooling, radiation cooling, film cooling, transpiration cooling and ablation have led to improvements in nozzles thermal protection [1]. Film cooling technology is one of the favorable cooling methods.…”