Nozzle for an aircraft turboprop engine with an unducted fan
US10113506B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 13, 2015 |
| Grant date | Oct 30, 2018 |
| Priority date | — |
| Expiry date | Aug 26, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.