Gas turbine engine
US11248533B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | May 5, 2020 |
| Grant date | Feb 15, 2022 |
| Priority date | — |
| Expiry date | Jun 5, 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 for an aircraft. The gas turbine engine for an aircraft comprising: an engine core comprising an annular gas passage, a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and a power gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft. The engine further has a recirculatory lubricant system which feeds lubricant to and scavenges lubricant from the power gearbox. The engine further has a circumferential row of inlet guide vanes, located downstream of the fan at an air inlet of the annular gas passage. The recirculatory lubricant system includes one or more return passages for lubricant scavenged from the power gearbox, the return passages crossing the annular gas passage through one or more of the inlet guide vanes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.