Gas turbine engine cooling component
US11131212B2 · kind B2 · utility
2Cited by
8References
21Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 6, 2017 |
| Grant date | Sep 28, 2021 |
| Priority date | — |
| Expiry date | Jul 13, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge at least partially defines a fluid passageway with the serpentine turn.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.