Component core with shaped edges
US10167726B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 10, 2015 |
| Grant date | Jan 1, 2019 |
| Priority date | — |
| Expiry date | Dec 23, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, at least one cooling passage. The at least one cooling passage includes a first wall and a second wall bounding the at least one cooling passage, the first wall having a plurality of first surface features and the second wall having a plurality of second surface features. The plurality of first surface features and the plurality of second surface features are arranged such that a width of the cooling passage varies along a length of the cooling passage defined by the plurality of first surface features and the plurality of second surface features. The plurality of first surface features has a first profile, and the plurality of second surface features has a second, different profile. A casting core for forming cooling passages in an aircraft component is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.