Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method
US11572803B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 1, 2022 |
| Grant date | Feb 7, 2023 |
| Priority date | — |
| Expiry date | Aug 1, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/204
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine airfoil includes a body including a wall defining pressure and suction sides, and a leading edge extending between the pressure and suction sides. A cooling circuit inside the wall of the body includes at least one of: a) a suction side to pressure side cooling sub-circuit including a first cooling passage(s) extending from the suction side to the pressure side around the leading edge to a first plenum, and a plurality of first film cooling holes communicating with the first plenum and extending through the wall on the pressure side; and b) a pressure side to suction side cooling sub-circuit including second cooling passage(s) extending from the pressure side to the suction side around the leading edge to a second plenum, and a plurality of second film cooling holes communicating with the second plenum and extending through the wall on the suction side.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.