The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle comprising: a propelling nozzle wall (20), a duct (15), which is radially outwardly bounded by the propelling nozzle wall (20), and a central body (5) arranged in the duct (15). According to the invention, the central body (5) is connected to the propelling nozzle wall (20) via at least one brace (31, 32).
PROPELLING NOZZLE FOR A TURBOFAN ENGINE ON A SUPERSONIC AIRCRAFT
18.03.2021
Patent
Elektronische Ressource
Englisch
Propelling nozzle for a turbofan engine on a supersonic aircraft
Europäisches Patentamt | 2022
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