Turbine shroud segment transpiration cooling with individual cast inlet and outlet cavities
US7520715B2 · kind B2 · utility
13Cited by
15References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 19, 2005 |
| Grant date | Apr 21, 2009 |
| Priority date | — |
| Expiry date | Oct 28, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/20
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A shroud segment of a turbine shroud of a gas turbine engine comprises a platform with front and rear legs. The platform defines a plurality of axially extending holes with individual inlets on an outer surface of the platform for transpiration cooling of the platform of the turbine shroud segment.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.