Method of producing a gas turbine engine component
US10793943B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Mar 15, 2018 |
| Grant date | Oct 6, 2020 |
| Priority date | — |
| Expiry date | Jun 2, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldMachine tools
- WIPO sectorMechanical engineering
Abstract
A method of producing a gas turbine engine fan blade having a geometric configuration is provided. The method includes: plastically deforming an initial substrate comprised of a first metallic material into a formed substrate; depositing a second metallic material onto the formed substrate using an additive manufacturing process to produce a blade blank, which depositing includes: additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface, to form a root portion; additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate between the root portion and the second end surface to form an airfoil portion; and shaping the blade blank into the geometric configuration.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.