Gas turbine engine having fan diameter ratio
US11111791B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 28, 2020 |
| Grant date | Sep 7, 2021 |
| Priority date | — |
| Expiry date | Oct 28, 2040 |
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 and a fan located upstream of the engine core. The engine core includes: a compressor system including 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 the outer core casing at an axial position of the first flange connection. The first flange connection is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor. A fan diameter ratio of: is equal to or greater than 0.125.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.