Gas turbine engine airfoil with variable pitch cooling holes
US11215059B1 · kind B1 · utility
0Cited by
7References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 3, 2020 |
| Grant date | Jan 4, 2022 |
| Priority date | — |
| Expiry date | Sep 3, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil includes a ceramic airfoil section that defines leading and trailing edges, pressure and suction sides, and radially inner and outer ends. The span of the airfoil section has first, second, and third radial span zones. There is a row of cooling holes in an aft 25% of the axial span. The row of cooling holes extends though the first, second, and third radial span zones. The cooling holes in the first radial span zone define a first pitch P1, the cooling holes in the second radial span zone define a second pitch P2, and the cooling holes in the third radial span zone define a third pitch P3, wherein P2<P3<P1.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.