Airfoil with supplemental cooling channel adjacent leading edge
US7478994B2 · kind B2 · utility
59Cited by
14References
31Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 23, 2004 |
| Grant date | Jan 20, 2009 |
| Priority date | — |
| Expiry date | Nov 23, 2024 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil, and in a disclosed embodiment a rotor blade, has film cooling holes formed at a leading edge. A supplemental film cooling channel is positioned near the leading edge, but spaced toward the trailing edge from the leading edge. The supplemental film cooling channel directs film cooling air onto a suction wall. The supplemental film cooling channel air is generally directed to a location on the suction wall that has raised some challenges in the past. In a disclosed embodiment, the airfoil is provided with a thermal barrier coating, and the supplemental film cooling air protects this thermal barrier coating.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.