Abstract
A one-dimensional full transient droplet evaporation model was established under consideration of factors such as high pressure vapour-liquid equilibrium, high-pressure physical property corrections, gas phase dissolution, and shift of interface. The finite volume method was used for discretization to study the migration and evaporation characteristics of the surrogate fuel for kerosene, which was constituting of (mass fraction)80% n-decane and 20%1,2,4-trimethylbenzene, under supercritical conditions. The results show that, under supercritical conditions, the higher the temperature and the pressure, the easier and the sooner the supercritical migration occurs. Before the supercritical migration occurring, there was obvious boundary between the gas and liquid phases. The mass fraction of component was discontinuous, and the gradient of temperature near the interface was large. After the supercritical migration occurring, the surface of the droplet disappeared, there was no obvious boundary between the gas and liquid phases, and the distribution of the components mass fraction and temperature were continuously. With the increase of the initial temperature of the droplet, the time of the supercritical migration was greatly advanced, the rise rate of the droplet surface temperature increased, and the phenomenon of endothermic expansion no longer appeared.
Highlights
With the rapid development of the aerospace industry around the world, people need to send more and more things into space for various scientific experiments, planetary exploration, and the establishment of space stations
The evaporation characteristics, supercritical transport characteristics and effects of initial droplet temperature on evaporation and migration characteristics in supercritical environment were studied by simulation calculations
The results lay the foundation for the simulation research of kerosene droplet combustion in the supercritical environment, and provide some reference for explaining the mechanism of ignition and unstable combustion in liquid oxygen/kerosene rocket engines
Summary
With the rapid development of the aerospace industry around the world, people need to send more and more things into space for various scientific experiments, planetary exploration, and the establishment of space stations. In order to improve the performance of the liquid oxygen/kerosene rocket engine, people continuously increase the pressure of the engine combustion chamber to improve the combustion efficiency. Li Yunqing et al.[4] studied the process and conditions of the surface migration in the supercritical evaporation process, based on the actual gas state equation and high-pressure vapourliquid equilibrium. Li Pengfei et al.[5] studied the variation of gas solubility, evaporation rate and droplet life under subcritical and supercritical conditions, which was based on OpenFOAM and using real fluid model and state equation method to calculate the multi-component vapour-liquid equilibrium under high-pressure. A bicomponent surrogate fuel for kerosene was found, and the transcritical characteristics of the kerosene droplet and the effect of initial droplet temperature on the transcritical characteristics of the kerosene droplet under the supercritical environment was studied by simulation
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