Turbomachine component for a gas turbine, turbomachine assembly and gas turbine having the same
US11480060B2 · kind B2 · utility
Inventors
Key dates
| Filing date | Jan 14, 2021 |
| Grant date | Oct 25, 2022 |
| Priority date | — |
| Expiry date | Jan 14, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/232
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present technique presents a turbomachine component having an airfoil e.g. a vane of a gas turbine. The airfoil wall defines an internal space which includes a first and a second cooling channels having a first and a second impingement inserts, that define a first main and a first peripheral flow channels in the first cooling channel and a second main and a second peripheral flow channels in the second cooling channel, respectively. Impingement jets ejected from the main flow channels via impingement holes of the corresponding impingement inserts are received in the corresponding peripheral flow channels. A channel connecting conduit conducts a flow of the cooling air from the first cooling channel to the second cooling channel. The channel connecting conduit includes an inlet connected to an outlet of the first cooling channel, and an outlet connected to an inlet of the second cooling channel.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.