Gas turbine engine with fan outlet guide vanes
US10584632B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 9, 2019 |
| Grant date | Mar 10, 2020 |
| Priority date | — |
| Expiry date | Jul 9, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/36
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes an engine core; a fan located upstream of engine core and having a fan diameter; a nacelle surrounding engine core and defining a bypass duct between engine core and nacelle; and a fan OGV extending radially across bypass duct, fan OGV having a radially inner and outer edge, wherein the radially inner edge's axial midpoint is the fan OGV root centrepoint. The engine core includes a compressor system encompassing a first, lower pressure, compressor, and second, higher pressure, compressor; and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of outer core casing at an axial position of first flange connection, the first flange connection having a first flange radius, wherein the first flange connection is downstream of an axial position. A fan OGV root position ratio of: is equal to or less than 2.6.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.