Nacelle for gas turbine engine
US11415048B2 · kind B2 · utility
0Cited by
7References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 15, 2021 |
| Grant date | Aug 16, 2022 |
| Priority date | — |
| Expiry date | Apr 15, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/324
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The diffuser further includes a diffuser angle (θdiff), indicating a degree of divergence of the diffuser relative to the longitudinal centre line. The diffuser angle (θdiff) is from about 0 degrees to about 12 degrees.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.