Gas turbine engine component with converging/diverging cooling passage
US9279330B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 9, 2012 |
| Grant date | Mar 8, 2016 |
| Priority date | — |
| Expiry date | Dec 4, 2034 |
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 gas path wall having a first surface and a second surface and a cooling hole extending through the gas path wall from the first surface to the second surface. The cooling hole includes an inlet portion having an inlet at the first surface, an outlet portion having an outlet at the second surface, and a transition defined between the inlet and the outlet. The inlet portion converges in a first direction from the inlet to the transition and diverges in a second direction from the inlet to the transition. The outlet portion diverges at least in one of the first and second directions from the transition to the outlet.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.