Numerische Simulation des Wärmeübergangs in einer kryogenen Raketenbrennkammer

The goal of this thesis is to determine the influence of different phenomena on the heat load of a hydrogen/oxygen rocket combustion chamber into the adjacent regenerative cooled wall. The heat transfer in turbulent flow is a result of turbulent vortices and the heat conductivity of the fluid. The turbulent effects were represented by the q-omega Low-Reynolds turbulence model, while the gas mixture and real gas effects werde considered in the gas conductivity. With these models, the heat load was simulated by a fluid/structure interaction simulation in which only the energy equation was solved for the solid domain. In this investigation, the influence of three oxidizer/fuel-ratios (O/F) and three chamber pressures was analized with special focus on boundary layer effects in the resulting heat loads.

Grantor dc:publisher

Publikationsserver der RWTH Aachen University

Year dc:date

2006

Author dc:creator

• Haarmann, Thomas

Contributors dc:contributor

• Koschel, Wolfgang

• info:eu-repo/classification/ddc/620
• Ingenieurwissenschaften
• Computersimulation
• Wärmeübergang
• Brennkammer
• Reales Gas
• Raketentriebwerk
• Wärmeleitfähigkeit
• simulation
• heat transfer
• rocket combution chamber
• real gas effects
• transport coefficients of mixtures

Statement dc:rights

• info:eu-repo/semantics/openAccess

Language dc:language

ger

Identifier

https://publications.rwth-aachen.de/search?p=id:%22RWTH-CONV-123123%22

OAI identifier oai:identifier

oai:publications.rwth-aachen.de:61461