Propelling nozzle for a turbofan engine on a supersonic aircraft
US11448162B2 · kind B2 · utility
0Cited by
10References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 5, 2018 |
| Grant date | Sep 20, 2022 |
| Priority date | — |
| Expiry date | May 10, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/80
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle including: a propelling nozzle wall, a duct, which is radially outwardly bounded by the propelling nozzle wall, and a central body arranged in the duct. According to the invention, the central body is connected to the propelling nozzle wall via at least one brace.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.