Investigation of a Small Hydrogen-Oxygen Rocket Engine,

AD investigation on a small water-cooled, liquid oxygen/liquid hydrogen rocket engine has established the design of an efficient combustion system using a low pressure-drop injector. Five different injector combinations were considered and their combustion efficiencies evaluated. Heat transfer measurements were made and the effects of injector design on heat transfer profiles studied. Preliminary investigations were also made on a regeneratively-cooled combustion chamber, using hydrogen flowing through a simple annular cooling passage.