Gas turbine engine component with film cooling hole
US10982552B2 · kind B2 · utility
0Cited by
16References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 21, 2015 |
| Grant date | Apr 20, 2021 |
| Priority date | — |
| Expiry date | Feb 2, 2039 |
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 includes a wall that provides an exterior surface and an interior flow path surface. The wall has a wall thickness. A protrusion is arranged on the wall that extends a height beyond the wall thickness and provides a portion of the interior flow path surface. A film cooling hole that has an inlet is provided on the protrusion and extends to an exit on the exterior surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.