Gas turbine engine sealing structure
US8821114B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 2, 2011 |
| Grant date | Sep 2, 2014 |
| Priority date | — |
| Expiry date | Apr 12, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/30
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine section having a plurality flow path components forming a plurality of guide vane rings and ring segments arranged in axial succession to define a boundary of a hot gas duct. A vane carrier located around the gas duct, and sealing elements extend radially between circumferentially extending grooves in the vane carrier and respective grooves in the flow path components. The sealing elements include radially inner and outer edges, and at least one axially facing side defining a chamfered portion extending to one of the edges to accommodate axial movement of the sealing element about the one edge within a respective groove.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.