Method for producing a metal bladed element for a turbomachine of an aircraft
US12084779B2 · kind B2 · utility
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2References
9Claims
0Family size
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Key dates
| Filing date | Apr 19, 2019 |
| Grant date | Sep 10, 2024 |
| Priority date | — |
| Expiry date | Oct 22, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/4932
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surface extending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X1, said method comprising the steps of: a) producing the bladed element by lost-wax casting, and b) finishing the bladed element, characterised in that step b) comprises the chemical milling at least of the trailing edge of the or each blade so as to obtain said thickness X1 which cannot be directly obtained by step a).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.