Abstract
Optimum characteristic length of the combustion chamber of liquid rocket engine is very important to get higher energy from the liquid propellants. Characteristic length is defined by the time required for complete burning of fuel. Combustion reactions are very fast and combustion is evaporation dependent. This paper proposes fuel droplet evaporation model for liquid propellant rocket engine and discusses the factors which can affect the required size of characteristic length of the combustion chamber based on proposed model. The analysis is performed for low temperature combustion chamber. A computer code based on proposed model is generated, which solve analytical equations to calculate combustion chamber characteristic length under various input conditions. The analysis shows that characteristic length is affected by combustion chamber temperature, pressure, fuel droplet diameter, chamber diameter, mass flow rate of propellants and relative velocity of the droplet in the combustion chamber.
Highlights
Optimum characteristic length of the combustion chamber of liquid rocket engine is very important to get higher energy from the liquid propellants
The developed model is applied on low temperature combustion chamber with different input conditions
The output results showing the effects of input condition on characteristic length are shown
Summary
Optimum characteristic length of the combustion chamber of liquid rocket engine is very important to get higher energy from the liquid propellants. This paper proposes fuel droplet evaporation model for liquid propellant rocket engine and discusses the factors which can affect the required size of characteristic length of the combustion chamber based on proposed model. The analysis shows that characteristic length is affected by combustion chamber temperature, pressure, fuel droplet diameter, chamber diameter, mass flow rate of propellants and relative velocity of the droplet in the combustion chamber. Characteristic length is one of the important parameters of the combustion chamber of liquid rocket engine. Characteristic cc length has normally value between 0.8 and 3 meter It can be higher in some conditions.
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