Nacelle for a gas turbine engine
US11313241B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 30, 2020 |
| Grant date | Apr 26, 2022 |
| Priority date | — |
| Expiry date | Oct 30, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A nacelle for a gas turbine engine having a longitudinal centre line includes an intake lip disposed at an upstream end of the nacelle. The intake lip includes a crown and a keel. The crown includes a crown leading edge and the keel includes a keel leading edge. The crown leading edge and the keel leading edge define a scarf line therebetween. The scarf line forms a scarf angle (θscarf) relative to a reference line perpendicular to the longitudinal centre line. A fan casing is disposed downstream of the intake lip and includes a casing leading edge. The casing leading edge defines a droop line normal to the casing leading edge. The droop line forms a droop angle (θdroop) relative to the longitudinal centre line. A relationship between the droop angle (θdroop) and the scarf angle (θscarf) is given by: θdroop=θscarf/1.5±1 degree.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.