Sealing arrangement with pressure-loaded feather seals to seal gap between components of gas turbine engine
US11371368B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 27, 2018 |
| Grant date | Jun 28, 2022 |
| Priority date | — |
| Expiry date | Mar 27, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/57
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A sealing arrangement in a gas turbine engine to seal a gap between first and second turbine components is provided. The sealing arrangement includes a first arcuate feather seal connected to an anchoring assembly of the sealing arrangement affixed to the first turbine component. A second arcuate feather seal is affixed to the second turbine component. The first arcuate feather seal and the second arcuate feather seal are responsive to a pressure differential that develops across the gap to form a pressure-loaded sealing joint between respective sealing surfaces of the first arcuate feather seal and the second arcuate feather seal. The sealing arrangement provides substantial design flexibility since it can reliably provide appropriate sealing functionality while enabling multiple degrees of freedom, such as to accommodate radial and/or axial displacements that can develop between the first turbine component and the second turbine component.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.