Gas turbine engine airfoil cooling configuration with pressure gradient separators
US10385699B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 26, 2015 |
| Grant date | Aug 20, 2019 |
| Priority date | — |
| Expiry date | Sep 18, 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 includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.