Gas turbine engine with bearing buffer air flow and method
US9617916B2 · kind B2 · utility
3Cited by
22References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 28, 2012 |
| Grant date | Apr 11, 2017 |
| Priority date | — |
| Expiry date | Sep 24, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C6/08
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The gas turbine engine has a bleed air aperture formed in the radially outer wall upstream from the combustor and a bearing cavity formed within the radially inner wall, at least two bearing seals enclosing at least one bearing in the bearing cavity and separating the bearing cavity from associated buffer air entry points, an oil supply system including oil paths leading to each of the bearings; a buffer air supply system including buffer air paths leading to each of the entry points and a baffle partitioning one of the entry points.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.