Model for Fuel Droplet Evaporation in Combustion Chamber of Liquid Propellant Rocket Engines
Complete burning of liquid propellants droplets is very important to get higher specific impulse from liquid rocket engines. Required time must be provided to propellants droplets in combustion chamber for complete combustion. If required time is not provided then there will incomplete combustion of fuel which will reduce characteristic velocity and specific impulse. Combustion in liquid propellant rocket engine is non-premixed diffusion combustion. Combustion takes place in gaseous phase and reaction is very fast. So, the time consumed by a droplet for complete burning is the time taken by a droplet to get evaporate. Through modeling of droplets evaporation in combustion chamber of liquid propellant rocket engine, we can calculate time required for complete evaporation/ burning of propellants droplets and we can provide the required time in combustion chamber at design phase. An analytical mono component model is developed for the droplet evaporation in liquid rocket engine based on heat and mass transfer. The results of the model shows effects of the combustion chamber pressure, temperature, turbulence intensity, fuel droplet initial temperature, chamber diameter, droplet diameter and droplet relative velocity with hot gas on the life of droplet.
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