AbstractIn this paper, we present a combined experimental and numerical approach to assess the thermal loads and the cooling mechanism of an internally cooled strut injector for a supersonic combustion ramjet. Infrared measurements of the injector surface are conducted at a moderate external flow temperature. In addition, the main flow field is investigated with the LITA technique. Main features of the cooling mechanism are identified based on experimental data. However, a full evaluation can only be obtained using a complex, conjugate CFD simulation, which couples the external and internal flow fields to the heat conduction inside the injector body. Furthermore, numerical simulations are also presented for hot gas conditions corresponding to combustion experiments. Both hydrogen, which would be used as fuel for flight tests, and air are considered as coolants. While the main features of the cooling mechanism will be shown to remain unchanged, the combustor wall temperature is found to have a significant influence on the cooling. This emphasizes the importance and the usefulness of such complex conjugate numerical simulations.
HighlightsThermal investigation of an actively cooled strut injector for scramjet application.Comparison of experimental and numerical data for moderate temperatures.Coupled numerical approach to assess thermal loads and to identify critical regions.Numerical simulations for hot gas conditions, where experiments are not possible.Assessment of the influence of the combustor side wall temperature.
Thermal investigation of an internally cooled strut injector for scramjet application at moderate and hot gas conditions
Acta Astronautica ; 132 ; 177-191
2016-12-16
15 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
British Library Conference Proceedings | 2015
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