Siemens Aktiengesellschaft

Chromalloy Gas Turbine Corporation

Andrea Bolz

Ramesh Subramanian

Eckart Schumann

Francis-Jurjen Ladru

Martin Feldhege

A thermal barrier coating including a two layered ceramic barrier coating, an inner ceramic layer and an outer ceramic layer, is provided. The thermal barrier coating has different thicknesses on different places of the component. In addition, the thickness of the inner ceramic layer and the thickness of the outer ceramic layer vary in relation to one another.

Ceramic thermal barrier coating system with two ceramic layers

A surface of the gas turbine blade is smoothed by way of a drag finish process. A first ring-shaped container is filled with a liquid abrasive medium. A second container which is arranged next to the first container is filled with a second liquid abrasive medium. A pivoting arm is arranged between and above the containers and can be pivoted along a pivoting direction. A drag device is arranged on the pivoting arm. The drag device leads a gas turbine blade on a carrier arm through the abrasive medium.

Method for smoothing the surface of a gas turbine blade

An abrasive device may include first ring-shaped container filled with a liquid abrasive medium. A second container may be arranged next to the first container and filled with a second liquid abrasive medium. A pivoting arm may be arranged between and above the containers and can be pivoted along a pivoting direction. A drag device may be arranged on the pivoting arm. The drag device may lead a gas turbine blade on a carrier arm through the abrasive medium.

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Berlin, Germany

Andrea Bolz