Gas turbine engine architecture with low pressure compressor hub between high and low rotor thrust bearings
US9784181B2 · kind B2 · utility
1Cited by
15References
23Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 23, 2011 |
| Grant date | Oct 10, 2017 |
| Priority date | — |
| Expiry date | Aug 7, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method for servicing a gas turbine engine includes providing access from a forward section of the gas turbine engine to a gearbox contained within a bearing compartment.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.