Porous injectors in cryogenic liquid propellant rocket engines at sub- and supercritical pressures

Abstract

An alternative injection concept for the application in liquid propellant rocket engines has been successfully tested using two subscale rocket combustion chambers at pressures of up to 80 bar. With the new concept liquid oxygen (LOX) enters the chamber through numerous small diameter tubes in a classical parallel showerhead configuration. The fuel is completely fed through a porous faceplate made from sinter bronze. Two propellant combinations have been used, LOX/H2 and LOX/CH4. The near injector zone has been investigated using an optically accessible combustion chamber. In a second configuration an injector head covering the full faceplate has been used to acquire combustion efficiency as well as axial heat flux distribution data.