Turbine airfoil film cooling holes
US10077667B2 · kind B2 · utility
2Cited by
9References
19Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | May 8, 2015 |
| Grant date | Sep 18, 2018 |
| Priority date | — |
| Expiry date | Sep 5, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbomachinery component includes an airfoil section with a cooling passage extending within the airfoil section. A wall is defined between the cooling passage and an exterior surface of the airfoil. At least one row of cooling holes is positioned along a cooling portion of the external wall proximate a leading edge of the airfoil for fluid communication between the cooling passage and the exterior surface of the airfoil. The cooling portion of the airfoil wall is thicker than an average adjacent airfoil wall thickness.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.