Airfoils with lobed cooling cavities
US12173618B2 · kind B2 · utility
0Cited by
23References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 26, 2023 |
| Grant date | Dec 24, 2024 |
| Priority date | — |
| Expiry date | Sep 26, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine engine airfoil element has a plurality of main body passageways along a camber line and having two or more chordwise distributed protuberant portions with necks between the protuberant portions. A plurality of skin passageways include: at least one first skin passageway each nested between a first of the pressure side and the suction side and two adjacent main body passageways; and a plurality of second skin passageways each nested between first of the pressure side and the suction side and two said protuberant portions of a corresponding main body passageway.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.