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

Fachinformationsdienst BAUdigital

Eine Plattform für die Wissenschaft: Bauingenieurwesen, Architektur und Urbanistik

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.

Zugriff

Seitennavigation

Dokumentinformationen

Ähnliche Titel

Exportieren, teilen und zitieren

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.

Zugriff

Seitennavigation

Dokumentinformationen

Ähnliche Titel

Exportieren, teilen und zitieren

Dokumentinformationen

Titel:

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

Beteiligte:

SUBRAMANIAN RAMESH (Autor:in) / WALTER STEFFEN (Autor:in) / VAN DER LAAG NIELS (Autor:in) / RETTIG UWE (Autor:in)

Erscheinungsdatum:

01.02.2018

Medientyp:

Patent

Format:

Elektronische Ressource

Sprache:

Englisch

Klassifikation:

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

Ähnliche Titel

Preparation method of ceramic matrix composite surface priming coat

LUO WENDONG / QIU HAIPENG / GUAN HONG et al. | Europäisches Patentamt | 2020

Freier Zugriff

CERAMIC MATRIX COMPOSITE COMPONENT, GAS TURBINE SEAL ASSEMBLY, AND METHOD OF FORMING CERAMIC MATRIX COMPOSITE COMPONENT

HAFNER MATTHEW TROY / ITZEL GARY MICHAEL / JOHN MCCONNELL DELVAUX | Europäisches Patentamt | 2017

Freier Zugriff

CERAMIC MATRIX COMPOSITE COMPONENT,GAS TURBINE SEAL ASSEMBLY, AND METHOD OF FORMING CERAMIC MATRIX COMPOSITE COMPONENT

HAFNER MATTHEW TROY / ITZEL GARY MICHAEL / DELVAUX JOHN MCCONNELL | Europäisches Patentamt | 2017

Freier Zugriff

Method of forming a ceramic matrix composite (CMC) component having an engineered surface

SHIM SUNGBO / LAI BENJAMIN | Europäisches Patentamt | 2021

Freier Zugriff

METHOD OF FORMING A CERAMIC MATRIX COMPOSITE (CMC) COMPONENT HAVING AN ENGINEERED SURFACE

SHIM SUNGBO / LAI BENJAMIN | Europäisches Patentamt | 2019

Freier Zugriff