Segmented ceramic matrix composite turbine airfoil component
US8251651B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 28, 2009 |
| Grant date | Aug 28, 2012 |
| Priority date | — |
| Expiry date | Jul 1, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A segmented component for use with a gas turbine engine comprises a radially extending gas path portion. The gas path portion is for interacting with gas flow from the gas turbine engine. The component is divided into axially aligned segments comprising a forward segment, an aft segment, and a plurality of middle segments disposed between the forward segment and the aft segment. The middle segments comprise radially elongate ceramic matrix composite material plates. In one embodiment, the gas path portion comprises an airfoil for a turbine blade. In another embodiment, the gas path portion comprises a removable platform for a turbine blade. In another embodiment, the gas path portion comprises an airfoil for a turbine vane.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.