Turbine blade platform with U-channel cooling holes
US9243500B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 29, 2012 |
| Grant date | Jan 26, 2016 |
| Priority date | — |
| Expiry date | Sep 2, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.