US Patent Application 20090317548 - GAS TURBINE COMPONENT WITH A THERMAL BARRIER COATING, THERMAL BARRIER COATING FOR A GAS TURBINE COMPONENT AND PROCESS FOR PRODUCING A THERMAL BARRIER COATING ON A GAS TURBINE COMPONENT

Application 20090317548 Filed on July 31, 2007. Published on December 24, 2009

Abstract Claims Description Full Text

Inventor

Meier, Reinhold

US Class

427/248.1COATING BY VAPOR, GAS, OR SMOKE

Attorney, Agent or Firm

CROWELL & MORING LLP;INTELLECTUAL PROPERTY GROUP

Foreign Documents

10 2006 036 520.8 DE 08/04/2006

International Class

C23C 16/00

Abstract text

A gas turbine component of an aircraft engine having a base body, which comprises at least a first material, and a thermal barrier coating that is applied to the base body and consists of or includes an oxide ceramic, is disclosed. Micro-defects and/or nano-defects are included in the oxide ceramic in order to reduce the thermal conductivity of the thermal barrier coating.

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