Gas turbine engine cooling hole with circular exit geometry
US9376920B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 28, 2012 |
| Grant date | Jun 28, 2016 |
| Priority date | — |
| Expiry date | Nov 22, 2034 |
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 structure having an exterior surface. A cooling hole extends from a cooling passage to the exterior surface to provide an exit area on the exterior surface that is substantially circular in shape. A gas turbine engine includes a compressor section and a turbine section. A combustor is provided between the compressor and turbine sections. A component in at least one of the compressor and turbine sections has an exterior surface. A film cooling hole extends from a cooling passage to the exterior surface to provide an exit area that is substantially circular in shape. A method of machining a film cooling hole includes providing a component having an internal cooling passage and an exterior surface, machining a film cooling hole from the exterior surface to the internal cooling passage to provide a substantially circular exit area on the exterior surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.