Patent ID: 8720184
Filing Date: 2014-05-13
Classification: F02K,F05D,Y10T

Abstract:
1. A method for supplying a combustion chamber of a space propulsion engine with cryogenic liquid fuel and oxidizer propellants, the method comprising: pressurizing a fuel propellant tank and an oxidizer tank at a constant pressure; mixing the fuel propellant from the fuel propellant tank and the oxidizer propellant from the oxidizer tank to form a propellant mixture; feeding said propellant mixture through via an orifice of an enclosure of a propellant injector, wherein the fuel propellant and oxidizer propellant are mixed at constant pressure upstream of the propellant injector enclosure; and injecting said propellant mixture from said propellant injector enclosure into said combustion chamber, wherein flow rate of the propellant mixture into the combustion chamber is varied by varying geometry of the propellant injector, and the injection of the propellant mixture from the propellant injector enclosure into the combustion chamber is at constant pressure.