Nacelle for gas turbine engine and aircraft comprising the same
US11408306B2 · kind B2 · utility
1Cited by
4References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 19, 2021 |
| Grant date | Aug 9, 2022 |
| Priority date | — |
| Expiry date | Feb 14, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/38
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A nacelle for housing a fan within a gas turbine engine having a longitudinal centre line includes a leading edge and a trailing edge. A nacelle length (Lnac) is defined as an axial distance between the leading edge and the trailing edge. An azimuthal angle (θ) is defined about the longitudinal centre line. The nacelle length (Lnac) varies azimuthally. The nacelle length (Lnac) decreases azimuthally from an inboard end of the nacelle to an outboard end of the nacelle.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.