Cooling assembly for a gas turbine system
US9670785B2 · kind B2 · utility
4Cited by
16References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 19, 2012 |
| Grant date | Jun 6, 2017 |
| Priority date | — |
| Expiry date | Jan 17, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling assembly for a gas turbine system includes a turbine nozzle having at least one channel comprising a channel inlet configured to receive a cooling flow from a cooling source, wherein the at least one channel directs the cooling flow through the turbine nozzle in a radial direction at a first pressure to a channel outlet. Also included is an exit cavity for fluidly connecting the channel outlet to a region of a turbine component, wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.