Gas turbine for aeronautic engines
US9188008B2 · kind B2 · utility
4Cited by
5References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 21, 2011 |
| Grant date | Nov 17, 2015 |
| Priority date | — |
| Expiry date | Dec 17, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a turbine for aeronautic engines, a first and at least a second turbine disk rotating around a common axis respectively carrying a first and a second moving-blade crown, with which first and, respectively, second axial passages are defined through which a cooling air mass for the turbine disks can pass, a device for conveying cooling air being interposed between the first and the second axial passages to receive the mass of air passing through the first axial passages and send it through the second axial passages.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.