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Functional and thermomechanical analysis of heat exchanger structure
KTH, School of Industrial Engineering and Management (ITM), Energy Technology, Heat and Power Technology.
2014 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

To keep the combustion chamber of a rocket engine in a good mechanical state, the chamber is cooled by hydrogen flowing through channels alongside the chamber wall. Those channels are drilled into the chamber wall and then closed. Nevertheless, the process used to manufacture the cooling channels is long, difficult, and expensive.


This document analyses the feasibility of a new concept of combustion chamber whose channels are not closed by the usual process. The main issue concerns the behavior of the hot gas wall under the loading of the channel internal pressure and the hot gas thermal dilatation that counteract on the evolution of chamber radius and so on the radial gap between channels fins and structural external liner.

A logic has been built in order to analyze the coupling between hot gas wall behavior and hydrogen cooling efficiency, in different configuration (engine size, pressure level,…) and taking into account scattering of manufacturing processes.


In that way, the document contains a functional and thermomechanical analysis dealing with the effect of such a combustion chamber for different wall cases. The functional analysis was carried out with ANSYS FLUENT, a CFD solver. As for the thermomechanical analysis, it was carried out with ANSYS Workbench / SAMCEF FEM solver taking into account both the thermal and the mechanical effects. This document compares the heat flux in the case of a classical combustion chamber and a new combustion chamber (heat flux extracted, maximal wall temperature) and presents the mechanical consequences implied by this new type of chamber (pressure effects, thermal effects, strains, stresses).

This document also suggests a method predicting the behavior of such a chamber with different chamber radius, different kind of material, different pressure difference between the channels and the chamber. This method eases the conception of this new type of rocket engine.

Eventually, this document deals with non symmetrical problems due to manufacturing.

Place, publisher, year, edition, pages
National Category
Energy Engineering
URN: urn:nbn:se:kth:diva-140838OAI: diva2:692683
Available from: 2014-02-04 Created: 2014-01-31 Last updated: 2014-02-04Bibliographically approved

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