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...

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Bibliographic Details
Main Authors Vijay, Pujar V, Hayes, Rusty, Brown, Keith T, Rose, David L
Format Patent
LanguageEnglish
French
German
Published 16.12.2020
Subjects
CLADDING OR PLATING BY SOLDERING OR WELDING
CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING
MACHINE TOOLS
METAL-WORKING NOT OTHERWISE PROVIDED FOR
PERFORMING OPERATIONS
SOLDERING OR UNSOLDERING
TRANSPORTING
WELDING
WORKING BY LASER BEAM
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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: EP20200182220