Gas turbine engine
US9677424B2 · kind B2 · utility
1Cited by
9References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 24, 2015 |
| Grant date | Jun 13, 2017 |
| Priority date | — |
| Expiry date | Nov 6, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/98
- WIPO fieldChemical engineering
- WIPO sectorChemistry
Abstract
A gas turbine engine is provided defining a radial direction. The gas turbine engine generally includes a compressor section and a turbine section, the compressor section and turbine section together defining a core air flowpath. The gas turbine engine also includes a sump positioned inward of the core air flowpath along the radial direction. An air pump is positioned inward of the core air flowpath along the radial direction for providing a flow of air from the sump to lower an internal pressure of the sump and reduce a likelihood of lubrication leaking from the sump.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.