Development of Technologies for a CMC based Combustion Chamber

Kurzfassung

Within the MoU ‘Propulsion 2010’ which was signed in 2006, Astrium and DLR agreed to work jointly on Ceramic Matric 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 and nozzle extension will be developed and tested within the coming years. The paper reports the current status and focuses on propellant injection with porous face plates, heat and mass transfer within and along a porous combustion chamber liner and design and heat transfer issues of a cooled thrust nozzle.