An exhaust nozzle for an aircraft propulsion system includes a nozzle wall and a nozzle ring. The nozzle wall extends axially along an axis from an upstream end of the nozzle wall to a downstream end of the nozzle wall. The nozzle wall includes an inner skin, an outer skin and a cellular core between the inner skin and the outer skin. The inner skin forms an outer peripheral boundary of a flowpath axially along the nozzle wall. The nozzle ring forms a downstream trailing edge of the exhaust nozzle. The nozzle ring projects axially out from the downstream end of the nozzle wall to the downstream trailing edge of the exhaust nozzle to form another outer peripheral boundary of the flowpath axially along the nozzle ring. The nozzle ring is axially abutted against the cellular core. The nozzle ring is bonded to the inner skin and the outer skin.
EXHAUST NOZZLE ASSEMBLY FOR AIRCRAFT PROPULSION SYSTEM
2025-03-13
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
European Patent Office | 2021
|European Patent Office | 2025
|European Patent Office | 2021
|European Patent Office | 2023
|