Three domain thermal and mechanical fluid-structrure interaction analysis applied to cooled rocket thrust chambers

Document typeConference report
Defense date2011
PublisherCIMNE
Rights accessOpen Access
Abstract
Regeneratively cooled combustion chamber and nozzle structures are exposed
to extreme temperature gradients in space and time. One sided wall heating during the
hot run generates thermomechanical loads that induce high heat fluxes on the surface
and consequently high stresses inside the thin cooling channel structures. In order to
address the strong interaction between the structure and the different flow fields a coupled
simulation considering the thermal and mechanical interactions is desirable. The present
study covers both physical couplings in a partitioned approach applied to the steady state
case of a subscale thrust chamber.
Furthermore, this study will present a novel full parametric 3D modelling approach
for cooled rocket thrust chambers, which is specifically designed to reduce computational
expense in FSI analyses by applying non conforming symmetry conditions across coupling
interfaces. The parametrization ranges from thrust chamber contour design through CAD
modelling up to grid generation of the individual domains. Further extension of the
parametric approach allows the analysis of thermal protection systems applied inside the
combustion chamber.
CitationKowollick, D.S.; Haupt, M.C.; Horst, P. Three domain thermal and mechanical fluid-structrure interaction analysis applied to cooled rocket thrust chambers. A: COUPLED IV. "COUPLED IV : proceedings of the IV International Conference on Computational Methods for Coupled Problems in Science and Engineering". CIMNE, 2011, p. 1388-1399. ISBN 978-84-89925-78-6.
ISBN978-84-89925-78-6
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