Near wall leading edge cooling channel for airfoil
US11015456B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 20, 2019 |
| Grant date | May 25, 2021 |
| Priority date | — |
| Expiry date | Jul 26, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/204
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Airfoils, gas turbine engine assemblies including such airfoils, and methods of manufacturing the same. The airfoil includes multiple cooling channels proximate a leading edge of the airfoil, each of the cooling channels including an inlet provided on one an inner surface of the airfoil in one of the pressure side wall and the suction side wall, and an outlet provided on an outer surface of the airfoil in the other of the pressure side wall and the suction side wall. The cooling channels are arranged in a staggered configuration such there is an alternate pattern of cooling fluid flow provided at the leading edge of the airfoil, near the airfoil's stagnation point.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.