Doublet vane assembly for a gas turbine engine
US10533425B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 28, 2017 |
| Grant date | Jan 14, 2020 |
| Priority date | — |
| Expiry date | Apr 23, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.