Gas turbine cooled shroud assembly with hot gas ingestion suppression
US6942445B2 · kind B2 · utility
37Cited by
19References
28Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 4, 2003 |
| Grant date | Sep 13, 2005 |
| Priority date | — |
| Expiry date | Apr 30, 2024 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooled shroud assembly includes an angled slot and a plurality of dilution jet openings. The shroud forward cavity is modified such that at least one recirculation zone is produced. The angled slot forces an axial change in momentum of the hot gas flow and increases radial and axial pressure variation attenuation. The cooled shroud assembly isolates the shroud structure and seals from the hot flow path and a cooling flow from the dilution jet openings dilutes the hot gas flow. A series of recirculation zones shields the shroud carrier and high pressure seals from the hot gas flow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.