Turbine shroud assemblies with channels for buffer cavity seal thermal management
US12352176B1 · kind B1 · utility
0Cited by
161References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 31, 2024 |
| Grant date | Jul 8, 2025 |
| Priority date | — |
| Expiry date | May 31, 2044 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/55
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system includes seals arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.