Methods are provided forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis. The nacelle inlet structure includes an inlet lip portion and an outer barrel portion. One of the method may include steps of: forming the inlet lip portion; forming the outer barrel portion; arranging the inlet lip portion axially adjacent the outer barrel portion; and friction stir welding the inlet lip portion to the outer barrel portion to provide a circumferentially extending weld joint between the inlet lip portion and the outer barrel portion.
FORMING A NACELLE INLET FOR A TURBINE ENGINE PROPULSION SYSTEM
HERSTELLUNG EINES TRIEBWERKSGONDELEINLAUFS FÜR EIN TURBINENTRIEBWERK
FORMATION D'UNE ENTRÉE D'AIR DE NACELLE POUR TURBORÉACTEUR
2020-08-12
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Forming a nacelle inlet for a turbine engine propulsion system
European Patent Office | 2017
|FORMING A NACELLE INLET FOR A TURBINE ENGINE PROPULSION SYSTEM
European Patent Office | 2017
|Air inlet channel of aero-engine nacelle and aero-engine nacelle
European Patent Office | 2022
|NACELLE WITH A TRANSLATABLE INLET FOR AN AIRCRAFT PROPULSION SYSTEM
European Patent Office | 2022
|NACELLE WITH A TRANSLATABLE INLET FOR AN AIRCRAFT PROPULSION SYSTEM
European Patent Office | 2020
|