Gas turbine airfoil with shaped trailing edge coolant ejection holes
US8770920B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 18, 2012 |
| Grant date | Jul 8, 2014 |
| Priority date | — |
| Expiry date | Sep 18, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/304
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine blade or vane includes at least one internal radial channel for the circulation of cooling medium bordered on a pressure side by a pressure side wall and on a suction side by a suction side wall joined at a upstream side at a leading edge and at and downstream side at the trailing edge. At least one exit hole extends through at least one of the pressure side wall or the suction side wall for blowing out of cooling medium from the internal radial channel to a medium surrounding the blade or vane. At least one trailing edge exit hole along the trailing edge has a surfacial exit opening disposed at the pressure side of the trailing edge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.