Geared turbofan engine with integral gear and bearing supports
US8845277B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | May 24, 2010 |
| Grant date | Sep 30, 2014 |
| Priority date | — |
| Expiry date | Apr 17, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49229
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a bearing and a bearing support having a first wall extending between first and second ends and operatively supported by the bearing at a first end. An engine case is secured to the second end radially outward of the first end. A second wall integral with and extending transversely from the first wall provides a flexible support. The second wall has a flange, and a gear train component is secured to the flange. A gas turbine engine includes a support structure which supports the main rotatable structure via bearings and gear train components. The support provides both the necessary structural support for the rotor structure as well as desired flexibility for a fan drive gear system.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.