Gas turbine engine airfoil component platform seal cooling
US10794207B2 · kind B2 · utility
0Cited by
9References
15Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Sep 11, 2014 |
| Grant date | Oct 6, 2020 |
| Priority date | — |
| Expiry date | Jan 3, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/323
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component array includes first and second components each having a platform. The platforms are arranged adjacent to one another and provide a gap. A seal is arranged circumferentially between the first and second components and in engagement with the platforms to obstruct the gap. A cooling hole is provided in the seal and is in fluid communication with the gap. The cooling hole has an increasing taper toward the gap.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.