Aircraft turbomachine blade and method for manufacturing same using lost-wax casting
US12146420B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 11, 2020 |
| Grant date | Nov 19, 2024 |
| Priority date | — |
| Expiry date | Apr 20, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
An aircraft turbine engine blade includes at least one inner cavity for circulating a ventilation air flow and having a wall with first projecting elements oriented in a first direction and forming air flow disrupters, and at least a second projecting element oriented in a second direction different from the first direction. The second projecting element and at least one of the first projecting elements overlap each other in one area. At least one of the first projecting elements overlaps the second projecting element and has a height (H2, H4′) which is greater than that of the second projecting element in the area and greater than that of the other first projecting elements of the wall, in order to retain its disruptive function along the entire length thereof.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.