Blade for a turbomachine turbine, comprising internal passages for circulating cooling air
US11286788B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 18, 2018 |
| Grant date | Mar 29, 2022 |
| Priority date | — |
| Expiry date | Nov 4, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In order to limit the air flow required to cool its blade member, a blade for an aircraft turbomachine turbine includes, in its blade member, a main passage configured to collect a main air flow from an air inlet and to circulate it in the blade member, and a side passage located between the main passage and the pressure-side wall, while being separated from the main passage, wherein the side passage is configured to collect a side air flow from the air inlet and to circulate it in the blade member, the main passage having at least three portions connected together end-to-end to form a coil, the side passage being located between each of these portions and the pressure-side wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.