Gas turbine engine having fan outlet guide vane root position to fan diameter ratio
US11333021B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 21, 2021 |
| Grant date | May 17, 2022 |
| Priority date | — |
| Expiry date | Jul 21, 2041 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes an engine core, a fan located upstream of the engine core, a nacelle surrounding the engine core and defining a bypass duct, and a fan outlet guide vane (OGV) extending radially across the bypass duct between an outer surface of the engine core and an inner surface of the nacelle. The engine core includes a compressor system, and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection. An axial midpoint of a radially inner edge of the fan OGV is defined as the fan OGV root centrepoint. A fan OGV root position to fan diameter ratio of: is equal to or less than 0.33.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.