An assembly is provided for an aircraft propulsion system. This assembly includes a nozzle extending axially along and circumferentially about an axial centerline. The nozzle includes a nozzle panel and a nozzle fairing fixedly connected to the nozzle panel at an axial end of the nozzle. The nozzle is configured with an internal flow passage radially between the nozzle panel and the nozzle fairing. The internal flow passage extends axially within the nozzle to an outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle.
AIRCRAFT PROPULSION SYSTEM NOZZLE WITH INTERNAL FLOW PASSAGE
2021-11-11
Patent
Electronic Resource
English
Aircraft propulsion system nozzle with internal flow passage
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