Gas turbine engine cooling component
US10648351B2 · kind B2 · utility
0Cited by
9References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 6, 2017 |
| Grant date | May 12, 2020 |
| Priority date | — |
| Expiry date | May 31, 2038 |
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 an internal cavity that has an inlet on 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 is at least partially aligned with the inlet.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.