Turbine shroud assembly with angled cooling holes
US12421862B2 · kind B2 · utility
0Cited by
162References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 4, 2023 |
| Grant date | Sep 23, 2025 |
| Priority date | — |
| Expiry date | Dec 4, 2043 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a retainer. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The retainer couples the blade track segment to the carrier segment. The carrier segment may include a plurality of impingement passageways to conduct cooling air to the blade track segment.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.