Cooling arrangement for gas turbine engine components
US11168570B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Aug 27, 2020 |
| Grant date | Nov 9, 2021 |
| Priority date | — |
| Expiry date | Aug 27, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, at least one of an airfoil section and a platform section including a wall. The wall includes a plurality of pedestals having adjacent pedestals extending from an external wall surface to establish a respective cooling passage, and the cooling passage includes an inlet and an outlet. The adjacent pedestals are dimensioned such that the adjacent pedestals taper inwardly from the inlet in a first direction towards the outlet to establish a throat in the respective cooling passage. A method of fabricating a gas turbine engine component is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.