INFLUENCE OF COMBUSTION CHAMBER PRESSURE ON INJECTOR PERFORMANCE

This paper provides the design of an injector for a small thruster rocket engine based on the propellant properties like the combustion chamber pressure, temperature, mixture ratio of propellants and the mass flow rate of propellants. This paper includes selection of injector by comparing various optimal operation parameters such as droplet size- SMD, mixture ratio, Reynolds number, Weber number and the number of injector orifices. The trends wherein the injector performance parameters vary with changing combustion chamber pressures are studied