Development of Technologies for a CMC-based Combustion Chamber
Haidn, O. and Riccius, J. and Suslov, D. and Beyer, S. and Knab., O. (2008) Development of Technologies for a CMC-based Combustion Chamber. In: EUCASS Advances in Aerospace Sciences Progress in Propulsion Physics, Vol. 1. Torus Press. pp. 645-658. ISBN 978-2-7598-0411-5.
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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.
|Document Type:||Book Section|
|Title:||Development of Technologies for a CMC-based Combustion Chamber|
|Journal or Publication Title:||EUCASS Advances in Aerospace Sciences|
|In ISI Web of Science:||No|
|Page Range:||pp. 645-658|
|Series Name:||Progress in Propulsion Physics|
|Keywords:||Combustion chamber, propulsion|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Space|
|HGF - Program Themes:||W - no assignement|
|DLR - Research area:||Space|
|DLR - Program:||W - no assignement|
|DLR - Research theme (Project):||W -- no assignement (old)|
|Institutes and Institutions:||Institute of Space Propulsion > Technologie|
|Deposited By:||Michaela Hanke|
|Deposited On:||14 Jan 2009|
|Last Modified:||15 Jan 2010 00:55|
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