JONAS PEICHL; MARKUS SELZER; TATJANA CZIEP; PATRICK PFANNES; HANNAH BÖHRK; ANDREAS SCHWAB; JENS VON WOLFERSDORF; PATRICK PALMETSHOFER; DANIEL EIRINGHAUS

DOI Number: 10.13009/EUCASS2023-006

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.

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In Categories: 1. Aerospace Europe Conference 2023, 1.Events, 10. Propulsion Physics
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