Gas turbine bladed rotor for aeronautic engines and method for cooling said bladed rotor
US9181805B2 · kind B2 · utility
4Cited by
15References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 20, 2011 |
| Grant date | Nov 10, 2015 |
| Priority date | — |
| Expiry date | Mar 26, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A bladed rotor of a gas turbine for aeronautic engines is cooled by making an air mass flow through a plurality of passages, each one defined by a turbine disk on one side and by a root of a corresponding blade coupled to this turbine disk on the other, the incoming air of each passage being subdivided into two or more airflows and each flow being directed towards the turbine disk in a predefined direction.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.