As liquid propellants are atomized into droplets in a liquid rocket engine combustor, the evaporation and combustion of droplets plays an important role in the engine performance. In a practical rocket engine, the combustion of liquid propellants is carried out in the form of a spray or droplet cluster. However, it is very difficult to study the combustion process of the whole liquid spray theoretically as well as experimentally. Since the combustion of a single droplet is the fundamental of the spray combustion, some approximate estimates for the liquid spray combustion can be obtained from droplet combustion. The combustion process of a fuel droplet consists of several stages: fuel evaporation from the droplet surface, mixing with the surrounding medium, and reaction with the oxide gas in the medium.This chapter elaborates on the evaporation of a single droplet under various conditions: in a static or convection environment at atmospheric pressure, at a high pressure, and in an oscillation environment. The evaporation of a single droplet of a multicomponent fuel will also be described.
Theory for Quasi-Steady Evaporation and Combustion of a Single Droplet at Atmospheric PressureAs a classic case of droplet evaporation, the evaporation of an isolated spherical droplet in a static ambient at atmospheric pressure is widely studied. To derive an analytical solution in theoretical modeling, the droplet evaporation is commonly assumed to be a stationary process, though it is actually an unsteady process. It is also assumed that the droplets contain only one chemical component. Moreover, in most cases there is a velocity difference between the droplet Internal Combustion Processes of Liquid Rocket Engines: Modeling and Numerical Simulations, First Edition. Zhen-Guo Wang.