Blade/vane cooling passages
US10871074B2 · kind B2 · utility
8Cited by
21References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 28, 2019 |
| Grant date | Dec 22, 2020 |
| Priority date | — |
| Expiry date | Jun 15, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for use with a gas turbine engine includes a pressure side wall and a suction side wall. The suction side wall is configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of ribs forming a plurality of trapezoidal shaped cavities to receive a cooling airflow. The plurality of ribs being shaped in a way to allow for thermal growth of the airfoil, while minimizing stress in the airfoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.