Variable thickness core for gas turbine engine component
US10815827B2 · kind B2 · utility
2Cited by
7References
26Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 25, 2016 |
| Grant date | Oct 27, 2020 |
| Priority date | — |
| Expiry date | Dec 16, 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 has a body extending between two circumferential sides, and between a leading edge and a trailing edge. A refractory metal core within the body forms at least one cooling circuit to utilize fluid to cool the body. When the refractory metal core is removed from the body, the at least one cooling circuit includes an inlet, an outlet, and a passage that varies in cross-sectional area between the inlet and outlet. A method of manufacturing a gas turbine engine, a method of manufacturing a core, and a refractory metal core are also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.