Blade component, method for manufacture of same, and gas turbine
US11761340B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 16, 2021 |
| Grant date | Sep 19, 2023 |
| Priority date | — |
| Expiry date | Dec 16, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A blade component of a compressor or turbine stage of a gas turbine, in particular of a gas turbine engine is provided. The blade component has at least two structural elements which can be connected together by means of a connection process, in particular sintering. The at least two structural elements can be coupled and/or connected to at least one means for internal cooling of the blade component, and/or the means for internal cooling of the blade component is arranged in at least one of the least two structural elements. The at least two structural elements, when assembled, can be coupled to a cooling insert inside the blade component, wherein during operation, cooling air flowing into the cooling insert can be guided in targeted fashion via impingement cooling openings onto the inside of the blade component, in particular as impingement flow cooling.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.