Process for forming micro cooling channels inside a thermal barrier coating system without masking material
US6551061B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 27, 2001 |
| Grant date | Apr 22, 2003 |
| Priority date | — |
| Expiry date | Jun 8, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49316
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present invention provides a process for forming active convection cooling micro channels within or adjacent to a bond coat layer applied to a turbine high pressure turbine airfoil. When placed adjacent or within a porous TBC, the micro channels additionally provide transpiration cooling through the porous TBC. The micro channels communicate directly with at least one cooling circuit contained within the airfoil from which they receive cooling air, thereby providing direct and efficient cooling for the bond coat layer. Because the substrate includes an actively cooled flow path surface region that can reduce the cooling requirement for the substrate, the engine can run at a higher firing temperature without the need for additional cooling air, achieving a better, more efficient engine performance. In one embodiment, a metallic bond coat is applied to an airfoil. The bond coat is grooved such that the grooves are structured, with at least one structured micro groove communicating with at least one cooling fluid supply contained within the airfoil. A TBC layer is applied over the structured grooves, resulting in the formation of hollow micro channels for the transport of the cool…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.