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Numerical Simulation of Heat Loads in a Cryogenic H 2 /O 2 Rocket Combustion Chamber
Author(s) -
Haarmann T. M.,
Koschel W. W.
Publication year - 2003
Publication title -
pamm
Language(s) - English
Resource type - Journals
ISSN - 1617-7061
DOI - 10.1002/pamm.200310164
Subject(s) - combustion chamber , rocket (weapon) , mechanics , heat transfer , boundary value problem , rocket engine , finite element method , combustion , flow (mathematics) , domain (mathematical analysis) , solver , rotational symmetry , computational fluid dynamics , combustor , physics , aerospace engineering , thermodynamics , mathematics , engineering , chemistry , mathematical analysis , mathematical optimization , organic chemistry
A Finite Element solver for a coupled simulation of fluid and structure in an axisymmetric domain is presented. The method employs an explicit solution of the flow and structure variables. The computational domain of the fluid is discretised by unstructured triangles and rectangles while the sturcture domain is discretised by unstructured triangles only. For the purpose of code validation the solution of in total three test cases are shown. One test case deals with the structure only while the other two simulate heat transfer problems with a defined temperature distribution along a boundary wall and coupled conditions. Finally the code is used to simulate the heat load in a cryogenic H 2 /O 2 rocket combustion chamber.