Investigations on Fibre Reinforced Combustion Chamber Structures under Effusion Cooled LOX/LH2 Operation

Abstract

The development of effusion cooled ceramic rocket thrust chambers at the German Aerospace Center (DLR) since more than one decade leads currently to first designs of selfsustaining fibre reinforced chamber structures. Within the German Research Network ‘Propulsion 2010’, a closed co-operation between the DLR and the German Space Propulsion Industry (EADS Astrium Space Transportation), the technology demonstration for a ceramic thrust chamber assembly until the end of 2010 is foreseen. The combination of a porous metal injector, an inner C/C combustion chamber liner, covered by load carrying CFRP, and a fuel cooled CMC nozzle extension is planned to be demonstrated at the European Research and Technology Test Bench P8 at DLR Lampoldshausen, in LOX/LH2 operation within the KSK project (KSK – Keramische Schub-Kammer). The final tests in 2010 will be conducted at 80 mm sub-scale level of inner chamber diameter. First a series of preliminary tests on 50 mm level have been performed in 2008, with the purpose of investigating both functional and structural principles.