Siemens Westinghouse Power Corporation

John G Goedjen

Stephen M Sabol

Steven James Vance

Kelly M Sloan

Ramesh Subramanian

Jeffrey Charles Bowker

A turbine component, such as a turbine blade having a metal substrate ( ) is coated with a metal MCrAlY alloy layer ( ) and then a thermal barrier layer ( ) selected from LaAlO , NdAlO , La Hf O , Dy Al O , HO Al O , ErAlO , GdAlO , Yb Ti O , LaYbO , Gd Hf O or Y Al O .

Thermal barrier coatings for turbine components

The present invention generally describes multilayer coating systems comprising a composite metal/metal oxide bond coat layer. The coating systems may be used in gas turbines.

Thermal barrier and overlay coating systems comprising composite metal/metal oxide bond coating layers

A thermal barrier coating for hot gas path components of a combustion turbine based on a zirconia-scandia system. A layer of zirconium scandate having the hexagonal Zr,Sc,O,structure is formed directly on a superalloy substrate or on a bond coat formed on the substrate.

Thermal barrier coating

A turbine component contains a substrate (,) such as a superalloy, a basecoat (,) of the type MCrAlY, and a continuous barrier layer (,) between the substrate and basecoat, where the barrier layer (,) is made of an alloy of (Re, Ta, Ru, Os)X, where X can be Ni, Co or their mixture, where the barrier layer is at least 2 micrometers thick and substantially prevents materials from both the basecoat and substrate from migrating through it.

Barrier layer for a MCrAlY basecoat superalloy combination

The present invention generally describes methods for modifying MCrAlY coatings by using gaseous carburization, gaseous nitriding or gaseous carbonitriding. The modified MCrAlY coatings are useful in thermal barrier coating systems, which may be used in gas turbine engines.

Gaseous modification of MCrAlY coatings

The present invention generally describes multilayer thermal barrier coating systems and methods of making the multilayer thermal barrier coating systems. The thermal barrier coating systems comprise a first ceramic layer, a second ceramic layer, a thermally grown oxide layer, a metallic bond coating layer and a substrate. The thermal barrier coating systems have improved high temperature thermal and chemical stability for use in gas turbine applications.

Multilayer thermal barrier coating systems

A substrate (12) such as a superalloy turbine component is coated with a basecoat (14) of the type MCrAlY which also contains boron, where the amount of boron in the basecoat is in a concentration gradient where more boron is present near the top (16) than the bottom (20) of the basecoat (14) and boron is present in an average amount of over 0.50 wt. % throughout the basecoat cross-section (14) of the composite (10).

Growing community of inventors

Oviedo, FL, United States of America

John G Goedjen