Method of forming gas turbine engine components
US11806953B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 24, 2022 |
| Grant date | Nov 7, 2023 |
| Priority date | — |
| Expiry date | Aug 24, 2042 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
Abstract
An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.