Cooling system for a gas turbine engine
US7625171B2 · kind B2 · utility
6Cited by
11References
21Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 22, 2006 |
| Grant date | Dec 1, 2009 |
| Priority date | — |
| Expiry date | Oct 16, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/601
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling system for a gas turbine engine (FIG. 1) comprises a pre-swirl arrangement, preferably including a pre-swirl chamber, for providing cooling air to a turbine blade disc, and a ventilation arrangement for providing ventilation air to a rotating component of the gas turbine engine. The cooling system includes an air bypass arrangement, which preferably includes first, second and third air bypass duct portions, for conveying ventilation air away from the pre-swirl arrangement.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.