Gas turbine engine including a low pressure sump seal buffer source and thermally isolated sump
US7093418B2 · kind B2 · utility
21Cited by
17References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 21, 2004 |
| Grant date | Aug 22, 2006 |
| Priority date | — |
| Expiry date | Aug 3, 2024 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine is configured to use relatively cool, low pressure air discharged from a low pressure compressor to supply buffer air to lubrication sump seals. The engine is further configured such that the lubrication sump is thermally layered by isolating relatively hot, high pressure compressor air from the sump by utilizing a warm vent mixing cavity, which is located radially between of the hot high pressure compressor air and the cool buffer air, which is located in a buffer cavity between the vent cavity and the sump.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.