An assembly is provided for an aircraft propulsion system (20). This assembly includes a nacelle inner structure (42) that extends axially along and circumferentially about an axial centerline (30). The nacelle inner structure (42) includes an internal compartment (68) and a cowl (76). The internal compartment (68) is configured to house a core of a gas turbine engine (22). The cowl (76) is configured to form an outer radial periphery of the internal compartment (68). An aft end portion (80) of the cowl (76) is also configured to form an outer radial periphery of a compartment exhaust (70) to the internal compartment (68). The aft end portion (80) of the cowl (76) includes a plurality of axial fingers (84) arranged circumferentially about the axial centerline (30) in an array.
PASSIVE INTERNAL COMPARTMENT EXHAUST FOR AN AIRCRAFT PROPULSION SYSTEM
PASSIVE INNENRAUMABSAUGUNG FÜR EIN FLUGZEUGANTRIEBSSYSTEM
ÉCHAPPEMENT DE COMPARTIMENT INTERNE PASSIF POUR SYSTÈME DE PROPULSION D'AÉRONEF
2022-11-02
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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