FORMING A NACELLE INLET FOR A TURBINE ENGINE PROPULSION SYSTEM

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 oute...

Full description

Saved in:
Bibliographic Details
Main Authors BROWN, Keith T, ROSE, David L, PUJAR, Vijay V, HAYES, Rusty
Format Patent
LanguageEnglish
French
German
Published 12.08.2020
Subjects
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
COSMONAUTICS
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
PARACHUTES
PERFORMING OPERATIONS
TRANSPORTING
Online AccessGet full text

Cover

More Information
Summary: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.
Bibliography:Application Number: EP20160194081