Gas turbine engine turbine vane platform core
US9021816B2 · kind B2 · utility
9Cited by
13References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 2, 2012 |
| Grant date | May 5, 2015 |
| Priority date | — |
| Expiry date | Jan 13, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.