Airfoil trailing edge cooling construction
US6616406B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jun 11, 2001 |
| Grant date | Sep 9, 2003 |
| Priority date | — |
| Expiry date | Jun 29, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil in a gas turbine comprises an improved cooling construction at its trailing edge providing impingement as well as enhanced film cooling. The airfoil comprises cavities arranged between the suction and pressure side wall for a cooling fluid and exit passages leading from the cavities to exit ports positioned on the pressure side wall. According to the invention the suction side wall is shaped such that the tip portion of the trailing edge has a cross-section comprising a part of a circle that is equal or greater than a semi-circle extending from the suction side around the tip to the pressure side and beyond into the exit passage. The exit passages comprise a bend in the region of the tip where they form an exit plenum for the cooling fluid to diffuse further.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.