Swirling, impinging sheet injector

摘要

An injector for injecting a first liquid propellant and a second liquid propellant into a combustion chamber of a rocket engine. The injector includes a first injection element for injecting a first portion of the first liquid propellant into the combustion chamber such that the first portion of the first liquid propellant enters the combustion chamber in a first sheet or stream. A second injection element is spaced radially outward from the first injection element and injects a second portion of the first liquid propellant into the combustion chamber such that the second portion of the first liquid propellant enters the combustion chamber in a second stream. The first and second streams collide, causing the first and second portions of the first liquid propellant to at least partially atomize. A third injection element is spaced radially outward from the second injection element and injects at least a first portion of the second liquid propellant into the combustion chamber such that the first portion of the second liquid propellant enters the combustion chamber in a third stream. The third stream is collided with the at least partially atomized first propellant and produces a mixture of an atomized fuel and oxidizer. A method for injecting liquid oxidizer and liquid fuel into a combustion chamber is also provided.