Fabian Breede
Current Organizations / Institutes
The organizations/institutes from the scholar's latest article
Research Subjects
Fabian Breede has a total of 3 co-authors. Here are the top co-authors by number of shared publications:
- Neraj Jain
DLR German Aerospace Center, Institute of Structures and Design, Pfaffenwaldring 38-40, 70569 Stuttgart, Germany
1 shared publication Raouf Jemmali
Institute of Structures and Design German Aerospace Center (DLR) Pfaffenwaldring 38–40 Stuttgart 70569 Germany
1 shared publicationSeverin Hofmann
Institute of Structures and Design German Aerospace Center (DLR) Pfaffenwaldring 38–40 Stuttgart 70569 Germany
1 shared publication
Latest Publications
- 18 October 2015
- Published by Wiley in International Journal of Applied Ceramic Technology
- Vol. 13 (1) , 3-16
Design, Manufacture, and Characterization of a Carbon Fiber‐Reinforced Silicon Carbide Nozzle Extension
Nozzle extensions made of ceramic matrix composites ( CMC s) have shown the potential to replace heavy superalloy nozzles and improve the performance of future upper‐stage and orbital rocket engines. Gas permeability has been reported to be a critical issue during the manufacture for CMC nozzles. This work shows the manufacture of a dense radiation‐cooled C / C ‐ S i C nozzle demonstrator. A multi‐angle fiber architecture was applied using filament winding technique to reduce the incidence of delaminations during the manufacturing process under high temperatures. Additional efforts were made to improve the final gas tightness and reduce the amount of residual silicon by means of an adapted liquid silicon infiltration process. The manufacture, the material, and structural characterization as well as a finite element analysis of a performed internal pressure test are presented.
- 18 October 2015
- Published by Wiley in International Journal of Applied Ceramic Technology
- Vol. 13 (1) , 3-16
Design, Manufacture, and Characterization of a Carbon Fiber‐Reinforced Silicon Carbide Nozzle Extension
Nozzle extensions made of ceramic matrix composites ( CMC s) have shown the potential to replace heavy superalloy nozzles and improve the performance of future upper‐stage and orbital rocket engines. Gas permeability has been reported to be a critical issue during the manufacture for CMC nozzles. This work shows the manufacture of a dense radiation‐cooled C / C ‐ S i C nozzle demonstrator. A multi‐angle fiber architecture was applied using filament winding technique to reduce the incidence of delaminations during the manufacturing process under high temperatures. Additional efforts were made to improve the final gas tightness and reduce the amount of residual silicon by means of an adapted liquid silicon infiltration process. The manufacture, the material, and structural characterization as well as a finite element analysis of a performed internal pressure test are presented.