Numerical Framework for the Investigation of a Transpiration Cooled LOx/LH2 Rocket Engine Combustion Chamber

Kurzfassung

The aim of this study is to present a numerical framework for the development of transpiration cooled rocket combustion chambers based on the commercial CFD software ANSYS CFX. The framework couples the hot gas flow domain and the coolant reservoir domain with the porous domain. The numerical setup is applied to an exemplary virtual transpiration cooled LOx/LH2 main stage rocket engine. Two different approaches modeling the hot gas flow with non-reactive flow and reactive flow are introduced and evaluated. The described setup was used for a parametric study to identify desirable properties for the porous material.