Turbine blade tip cooling hole arrangement
US11781433B1 · kind B1 · utility
0Cited by
7References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 8, 2022 |
| Grant date | Oct 10, 2023 |
| Priority date | — |
| Expiry date | Dec 8, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine blade for a gas turbine engine includes a plurality of cooling holes positioned adjacent a tip of the turbine blade. The plurality of cooling holes are oriented at specific angles to produce film-cooling of the turbine blade tip to improve durability and performance of the turbine blade. Further, the plurality of cooling holes are positioned at specific locations to improve film-cooling of the turbine blade while reducing negative impacts on performance of the turbine blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.