Method of forming gas turbine engine components
US10808542B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 11, 2019 |
| Grant date | Oct 20, 2020 |
| Priority date | — |
| Expiry date | Jun 12, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/30
- WIPO fieldMachine tools
- WIPO sectorMechanical engineering
Abstract
A method of forming a gas turbine engine component according to an example of the present disclosure includes, among other things, attaching a cover skin to an airfoil body, the airfoil body and the cover skin cooperating to define pressure and suction sides of an airfoil, and moving the airfoil in a forming line including a plurality of stations. The plurality of stations include a set of heating stations, a deforming station and a set of cool down stations. The moving step includes positioning the airfoil in the set of heating stations to progressively increase a temperature of the airfoil, then positioning the airfoil in the deforming station including causing the airfoil to deform between first and second dies, and then positioning the airfoil in the set of cool down stations to progressively decrease the temperature of the airfoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.