Turbine blade platform cooling holes
US11401819B2 · kind B2 · utility
0Cited by
23References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 17, 2020 |
| Grant date | Aug 2, 2022 |
| Priority date | — |
| Expiry date | Dec 17, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blades also experience high temperatures. In an embodiment, cooling holes are provided in each platform to cool distressed locations in the platform and improve the durability of each turbine blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.