Grid ceramic matrix composite structure for gas turbine shroud ring segment
US8118546B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Aug 20, 2008 |
| Grant date | Feb 21, 2012 |
| Priority date | — |
| Expiry date | Sep 18, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/24479
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A ceramic matrix composite (CMC) component such as a ring seal segment (50, 50A, 50B, 50C, 50D) for a gas turbine engine (10), the component formed with a base plate (52) and a frame portion (54) that extends substantially normally from the base plate around its perimeter. A grid of intersecting CMC ribs (73) is formed on the base plate within the frame portion. The ribs have a height (H) that may be within 3 times the total thickness (B) of the base plate, including any rib base (39) bonded to the base plate, along at least most of the rib length. The grid of ribs may be assembled from an array of CMC cups (40) bonded to the base plate, to adjacent cups, and to the frame portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.