Internal cooling circuit for blade outer air seal formed of laminate
US10822985B2 · kind B2 · utility
0Cited by
8References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 29, 2018 |
| Grant date | Nov 3, 2020 |
| Priority date | — |
| Expiry date | Oct 5, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of forming a gas turbine engine component includes the steps of (a) forming an intermediate portion, (b) forming cooling circuit structure into at least an outer layer of the intermediate portion, (c) providing an outer layer over the formed cooling circuits to close off the cooling circuits, such that there are laminate on both a radially inner and a radially outer side of the cooling circuits, and (d) forming an inlet and an outlet to the cooling circuits through the outer layer. A gas turbine engine is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.