Airfoil with internal crossover passages and pin array
US11885230B2 · kind B2 · utility
0Cited by
12References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 16, 2021 |
| Grant date | Jan 30, 2024 |
| Priority date | — |
| Expiry date | Mar 16, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/2214
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine. The airfoil includes a unique cooling path for a coolant, routing the coolant through a cooling cavity, through a column of crossover passages and through a pin array near a trailing edge of the airfoil. The crossover passages produce impingement cooling and the pin array produces convective cooling. This combination of impingement cooling and convective cooling results in increased cooling of the airfoil and better aeromechanical life objectives.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.