Forming a nacelle inlet for a turbine engine propulsion system
US9845728B2 · kind B2 · utility
6Cited by
13References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 15, 2015 |
| Grant date | Dec 19, 2017 |
| Priority date | — |
| Expiry date | Jun 5, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/10
- WIPO fieldMachine tools
- WIPO sectorMechanical engineering
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.