Gas turbine engine airfoil with vane platform cooling passage
US9080452B2 · kind B2 · utility
1Cited by
2References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 28, 2012 |
| Grant date | Jul 14, 2015 |
| Priority date | — |
| Expiry date | Jan 17, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.