Integrated thermal system for a gas turbine engine
US9797311B2 · kind B2 · utility
5Cited by
9References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 3, 2015 |
| Grant date | Oct 24, 2017 |
| Priority date | — |
| Expiry date | May 4, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.