Method for cooling engine components using multi-layer barrier coating
US6599568B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 19, 2002 |
| Grant date | Jul 29, 2003 |
| Priority date | — |
| Expiry date | Sep 19, 2022 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/24996
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
A cooling system for cooling of the flow path surface region of an engine component used in a gas turbine engine and a method for making a system for cooling of the flow path surface region of an engine component used in a gas turbine engine. The method comprises the steps of channeling apertures in a substrate to a diameter of about 0.0005″ to about 0.02″ to allow passage of cooling fluid from a cooling fluid source; applying a bond coat of about 0.0005″ to about 0.005″ in thickness to the substrate such that the bond coat partially fills the channels; applying a porous inner TBC layer of at least about 0.01″ in thickness to the bond coat, such that the TBC fills the channels; applying an intermediate ceramic layer that is more dense than the inner TBC layer on top of the porous TBC; applying an outer TBC layer over the intermediate layer; and, passing cooling fluid from a cooling fluid source through the channel into the porous TBC. The density of thc outer TBC layer can be varied as needed to achieve desired cooling objectives. Because the channel exit is filled with porous TBC material, cooling fluid flows through the porous passageways into the in…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.