Gas turbine engine having front mount position ratio
US11008870B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 31, 2020 |
| Grant date | May 18, 2021 |
| Priority date | — |
| Expiry date | Jan 31, 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 including: a compressor system including first, lower pressure compressor, and second, higher pressure compressor; and an outer core casing. The engine includes a front mount arranged for connection to a pylon; and a fan located upstream of the engine core. The outer core casing includes a first flange connection that: is arranged to allow separation of the outer core casing at an axial position thereof, and is the first flange connection downstream of an axial position defined by the axial midpoint between the mid-span axial location on trailing edge of the most downstream aerofoil of first compressor and mid-span axial location on leading edge of the most upstream aerofoil of the second compressor. A front mount position ratio of: is equal to or less than 1.18.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.