Hybridized airfoil for a gas turbine engine
US11781436B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 7, 2022 |
| Grant date | Oct 10, 2023 |
| Priority date | — |
| Expiry date | Jan 7, 2042 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldMachine tools
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine includes a first portion joined to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section. The airfoil section includes an airfoil body that extends between leading and trailing edges in a chordwise direction, between pressure and suction sides separated in a thickness direction, and from the root section to a tip portion in a spanwise direction. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib that bounds a respective pocket within a perimeter of the recessed region. The recessed region and the at least one rib are dimensioned to extend across the interface. A cover skin is coupled to the airfoil body along the at least one rib to enclose the recessed region.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.