CERAMIC MATRIX COMPOSITE TURBINE COMPONENT WITH ENGINEERED SURFACE FEATURES RETAINING A THERMAL BARRIER COAT: Fid-Bau Portal

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CERAMIC MATRIX COMPOSITE TURBINE COMPONENT WITH ENGINEERED SURFACE FEATURES RETAINING A THERMAL BARRIER COAT

SUBRAMANIAN RAMESH / WALTER STEFFEN / VAN DER LAAG NIELS / RETTIG UWE

An oxide and non-oxide based ceramic matrix composite (“CMC”) component for a combustion turbine engine has a solidified ceramic core with a three-dimensional preform of ceramic fibers, embedded therein. Engineered surface features (“ESFs”) are cut into an outer surface of the core and fibers of the preform. A thermal barrier coat (“TBC”) is applied over and coupled to the core outer surface and the ESFs. The ESFs provide increased surface area and mechanically interlock the TBC, improving adhesion between the ceramic core and the TBC.

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CERAMIC MATRIX COMPOSITE TURBINE COMPONENT WITH ENGINEERED SURFACE FEATURES RETAINING A THERMAL BARRIER COAT

SUBRAMANIAN RAMESH / WALTER STEFFEN / VAN DER LAAG NIELS / RETTIG UWE

An oxide and non-oxide based ceramic matrix composite (“CMC”) component for a combustion turbine engine has a solidified ceramic core with a three-dimensional preform of ceramic fibers, embedded therein. Engineered surface features (“ESFs”) are cut into an outer surface of the core and fibers of the preform. A thermal barrier coat (“TBC”) is applied over and coupled to the core outer surface and the ESFs. The ESFs provide increased surface area and mechanically interlock the TBC, improving adhesion between the ceramic core and the TBC.

CERAMIC MATRIX COMPOSITE TURBINE COMPONENT WITH ENGINEERED SURFACE FEATURES RETAINING A THERMAL BARRIER COAT

SUBRAMANIAN RAMESH / WALTER STEFFEN / VAN DER LAAG NIELS / RETTIG UWE

An oxide and non-oxide based ceramic matrix composite (“CMC”) component for a combustion turbine engine has a solidified ceramic core with a three-dimensional preform of ceramic fibers, embedded therein. Engineered surface features (“ESFs”) are cut into an outer surface of the core and fibers of the preform. A thermal barrier coat (“TBC”) is applied over and coupled to the core outer surface and the ESFs. The ESFs provide increased surface area and mechanically interlock the TBC, improving adhesion between the ceramic core and the TBC.

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Title:

CERAMIC MATRIX COMPOSITE TURBINE COMPONENT WITH ENGINEERED SURFACE FEATURES RETAINING A THERMAL BARRIER COAT

Contributors:

SUBRAMANIAN RAMESH (author) / WALTER STEFFEN (author) / VAN DER LAAG NIELS (author) / RETTIG UWE (author)

Publication date:

2018-02-01

Type of media:

Patent

Type of material:

Electronic Resource

Language:

English

Classification:

IPC: C04B Kalk , LIME / C23C Beschichten metallischer Werkstoffe , COATING METALLIC MATERIAL

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