Transpiration cooling in thermal barrier coating
US6375425B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 6, 2000 |
| Grant date | Apr 23, 2002 |
| Priority date | — |
| Expiry date | Nov 6, 2020 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49341
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method for transpiration cooling of the flow path surface region of an engine component used in a gas turbine engine by channeling a substrate to provide cooling channels through the substrate having a diameter of about 0.005″ to about 0.02″ to allow passage of cooling fluid from a cooling fluid source through the cooling channels. A bond coat of about 0.0005″ to about 0.005″ in thickness is applied to the substrate such that the bond coat partially fills the cooling channels. A porous TBC of at least about 0.003″ to about 0.01″ thick is applied over the bond coat, such that the TBC completely fills the cooling channels. Cooling fluid from a cooling fluid source is passed through the cooling channels and porous TBC. Because the channel exit is filled with TBC, the cooling fluid is transmitted through the porous passageways of the TBC. The porous passageways provide a plurality of tortuous routes to the TBC surface. The present invention further comprises both the cooled flow path surface region formed by the foregoing methods and the turbine component having a porous TBC cooling system connected to a cooling fluid source for cooling the compone…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.