Results of study of dissolution intensity of non-condensable gas in liquid propellant components of propulsion systems

The importance of determining the dissolution intensity of non-condensable gas in the propellant components used in rocket propulsion systems due to the effect of the gas content in the propellant on the liquid rocket engine performance is shown. The necessity of experimental studies of the dissolution intensity of gaseous helium in liquid hydrogen on a large-scale experimental facility when creating an oxygen-hydrogen propulsion system of the Energia launch vehicle is substantiated. Features of making studies with substantiation of the process model and generalization of experimental data are presented. The dependence of the mass-transfer coefficient in dimensionless form for wide ranges of the similarity criteria changes characteristic of high-boiling and cryogenic liquids is obtained. The comparative analysis and advantages of the obtained results, as well as brief information about their practical use are given. The results of the study of helium solubility in liquid cryogenic propellant components - hydrogen and oxygen - can be used when developing rocket stages with cryogenic propellant components for a superheavy class launch vehicle.