Gas turbine engine nozzle loft for thrust reverser
US12000358B1 · kind B1 · utility
0Cited by
6References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 14, 2023 |
| Grant date | Jun 4, 2024 |
| Priority date | — |
| Expiry date | Feb 14, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/323
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An engine nacelle assembly includes a nacelle that defines a flow path between an intake end and an exhaust end, and a nozzle that is disposed at the exhaust end of the nacelle about a central axis. The nozzle includes opposing thrust reverser openings and thrust reverser doors. A cross-sectional area transverse to the central axis proximate a forward side of each of the opposing thrust reverser openings is oval shaped with an offset radius within offset arc segments that are aligned with the opposing thrust reverser openings and a first radius outside of the offset arc segment. The first radius is less than the offset radius.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.