Laser ignition for liquid propellant rocket engine injectors

Abstract

A laser ignition device is used for igniting propellants in a rocket engine. The laser ignition device has an injector housing with passages for flowing gaseous hydrogen and liquid oxygen to injector elements which mix the hydrogen and oxygen in a combustion chamber. A laser ignition system assembly is inserted through the housing. The propellants in the housing keep the housing and the laser ignition system assembly cool. A laser beam entering the laser ignition system assembly via a fiber optic cable passes though a lens for diverging the laser beam and a second lens for converging the beam. A portion of the laser ignition system assembly extends beyond the injector housing face plate into the combustion chamber of the rocket engine. A multi-faceted pyramid reflector at the tip of the laser ignition system assembly in the combustion chamber splits the converging laser beam into beamlets which emerge from the laser ignition system assembly parallel to the ignition face plate and ignite the propellant a plurality of points in the combustion chamber adjacent to the injector elements. A purging gas may be introduced inside of the laser ignition system assembly to help cool the laser optic therein and helps keep the laser optics clean. The purging gas exits the laser ignition system assembly into the combustion chamber.