Development of Technologies for a CMC-based Combustion Chamber

Abstract

Within the "Propulsion 2010" Memorandum of Understanding (MoU) which was signed in 2006, Astrium and DLR agreed to work jointly on Ceramic Matrix Composite (CMC) materials and related technologies with the aim to have finally within the next three years all components and subsystems available for an entirely CMC-based thrust chamber assembly. Hence, propellant injection, combustion chamber liner, and appropriate cooling technologies as well as CMC nozzle parts will be developed and tested within the years to come. The paper reports the current status and focuses on propellant injection applying a porous face plate, heat and mass transfer within and along an effusion-cooled porous combustion chamber liner and design and heat transfer issues of a cooled thrust nozzle.