Gas turbine engine component, a turbojet engine provided therewith, and an aircraft provided therewith
US8459942B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 28, 2008 |
| Grant date | Jun 11, 2013 |
| Priority date | — |
| Expiry date | Oct 8, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component is provided including at least one ring element, and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. The load carrying vanes have an internal structure with an anisotropic load carrying property, and the internal structure is configured so that a main load carrying direction is in parallel with the extension direction of the load carrying vane. The component includes a stiffening structure bridging the distance between at least two adjacent load carrying vanes in the circumferential direction of the ring element, and the at least two adjacent load carrying vanes are attached to the stiffening structure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.