CMC component and method of fabrication
US7258530B2 · kind B2 · utility
29Cited by
12References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 21, 2005 |
| Grant date | Aug 21, 2007 |
| Priority date | — |
| Expiry date | Aug 20, 2025 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49339
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil (44) formed of a plurality of pre-fired structural CMC panels (46, 48, 50, 52). Each panel is formed to have an open shape having opposed ends (54) that are free to move during the drying, curing and/or firing of the CMC material in order to minimize interlaminar stresses caused by anisotropic sintering shrinkage. The panels are at least partially pre-shrunk prior to being joined together to form the desired structure, such as an airfoil (42) for a gas turbine engine. The panels may be joined together using a backing member (30), using flanged ends (54) and a clamp (56), and/or with a bond material (36), for example.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.