Turbine shroud gas path duct interface
US8157511B2 · kind B2 · utility
15Cited by
17References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 30, 2008 |
| Grant date | Apr 17, 2012 |
| Priority date | — |
| Expiry date | Jun 2, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/37
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An arrangement for sealing a turbine shroud gas path duct interface of a turbine engine comprises a static shroud surrounding a rotatable airfoil array and an annular duct downstream of the shroud with respect to a gas flow passing through the gas path. The shroud and the duct define a portion of the gas path for directing the gas flow, having an axially extending interface gap between the shroud and duct. An annular seal in use engages both the shroud and the duct, thereby sealing the annular gap.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.