Trailing edge cooling configuration for a gas turbine engine airfoil
US10100645B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 13, 2012 |
| Grant date | Oct 16, 2018 |
| Priority date | — |
| Expiry date | Nov 30, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49341
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine includes pressure and suction surfaces provided by pressure and suction walls that extend in a radial direction and are joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extends to the trailing edge. Elongated pedestals are arranged in the cooling passage and interconnect the pressure and suction walls. The elongated pedestals are spaced apart from one another in the radial direction and extend from a plane to the trailing edge. A metering pedestal includes at least a portion that is arranged between the plane and the trailing edge. The portion is provided between adjacent elongated pedestals in the radial direction.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.