Turbine nozzle trailing edge cooling configuration
US7121787B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 29, 2004 |
| Grant date | Oct 17, 2006 |
| Priority date | — |
| Expiry date | Sep 5, 2024 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/22141
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The trailing edge region of a nozzle airfoil is provided with a cooling configuration wherein post-impingement cooling air flows between radially spaced ribs defining convective cooling channels into a generally radially extending plenum. Cooling air in the plenum is split between film cooling holes for film cooling the pressure side of the trailing edge region and for flow about downstream pins for pin cooling the downstream regions of the opposite sides of the airfoil. The cooling air exiting the pins is directed through convective channels defined by a second set of radially spaced ribs and through exit apertures on the pressure side of the trailing edge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.