Component for a turbine engine with a cooling hole
US11391161B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 19, 2018 |
| Grant date | Jul 19, 2022 |
| Priority date | — |
| Expiry date | Mar 7, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An apparatus and method relating an airfoil for a turbine engine with an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The airfoil includes a first cooling passage extending in the span-wise direction within the interior and a second cooling passage defining an impingement surface and located proximate the first cooling passage, an interior wall separating the first cooling passage from the second cooling passage, and at least one cooling hole passing through the interior wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.