Gas turbine engine
US11156118B2 · kind B2 · utility
1Cited by
5References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 21, 2020 |
| Grant date | Oct 26, 2021 |
| Priority date | — |
| Expiry date | Jul 21, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine is provided for an aircraft comprising an engine core and a core flow path, a fan, a front drum cavity arranged radially inward of the core flow path, and a front bearing chamber. The front drum cavity comprises a front drum inlet, for providing air to the front drum cavity from the core air flow, located downstream of a stage of the compressor, and a front drum outlet, for ejecting air from the front drum cavity to the fan air flow, located axially between the fan and the compressor. The front drum inlet is through a seal, and the front drum outlet is through a spaced gap.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.