Gas turbine engine with geared architecture
US10082105B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 8, 2018 |
| Grant date | Sep 25, 2018 |
| Priority date | — |
| Expiry date | Feb 8, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF16H57/0486
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
In one exemplary embodiment, a gas turbine engine includes a bypass flow ratio greater than about ten. A fan supported on a fan shaft having a plurality of fan blades and a low fan pressure ratio of less than 1.45 measured across the fan blades alone. A gutter with an annular channel. A gear system connected to the fan shaft having a gear reduction ratio greater than 2.5, planetary gears, and a ring gear with an aperture that is axially aligned with the annular channel. A torque frame at least partially supports the gear system. A low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.