The measurement of oxidant/fuel ratio in injector plate of liquid propellant rocket engine before combustion, with an experimental method and its comparison with a theoretical method

Abstract

Mixture ratio (oxidant/ fuel) in combustion chamber has influence on combustion and thermodynamic properties as thrust and impulse; therefore, calculation of this parameter in the injector plate of liquid propellant rockets is very important. We have proposed an experimental method in which water and oil (simulating oxidant and fuel) passed from injection plate enter in elemental vessels. A computer code based on existent theoretical methods is developed and its results are compared with experimental results.