Gas turbine engine with fillet film holes
US10267161B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 7, 2015 |
| Grant date | Apr 23, 2019 |
| Priority date | — |
| Expiry date | Jul 1, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.