Deutsches Zentrum Fur Luft-Und Raumfahrt E.v.

Deutsches Zentrum Fuer Luft-Und Raumfahrt E.v

University of Central Florida Research Foundation Inc

Mtu Aero Engines Gmbh

Forschungszentrum Juelich Gmbh

Uwe Schulz

Bilge Saruhan-Brings

Klaus Fritscher

Hartmut Schurmann

Jorg Brien

Robert Vassen

Detlev Stoever

Seetha Raghavan

Christian Friedrich

Ravisankar Naraparaju

Wolfgang Wachter

Gerhard Pracht

Uwe Kaden

Estefania Bohorquez

Harmut Schurmann

Claus-Juergen Kroeder

Claus-Jurgen Kroder

Claus Jürgen Kröder

Claus Kroder

Claus Jürgen Kroder

J&ouml;rg Brien

Claus-J&uuml;rgen Kr&ouml;der

The present invention provides a non-destructive method of characterizing CMAS infiltration and CMAS assisted damage in thermal barrier coatings (TBCs). Such approach is especially relevant for determining the lifetime of coatings on e.g. turbines or parts of the turbines such as blades or in-liners of the combustion chambers. The turbines can be gas turbines or high-pressure turbines or others and may be stationary or used for example in aviation.

Non-destructive CMAS-infiltration characterization of thermal barrier coatings

A heat-insulating layer system for a metallic structural component, especially for a structural component of a gas turbine such as an aircraft engine, includes an adhesion promoting layer (), an inner contact layer (), and an outer cover layer () , whereby the adhesion promoting layer (). is disposed on a surface () of the gas turbine structural component (). The inner contact layer () is formed of a zirconium oxide partially stabilized with yttrium or yttrium oxide, and the outer cover layer () is formed of a material that consists of at least one component with at least one phase, which stoichiometrically comprises 1 to 80 Mol-% MxO, 0.5 to 80 Mol-% MyO and AlOas a remainder with incidental impurities, wherein Mx is selected from the elements chromium and barium or mixtures thereof, and wherein My is selected from the alkaline earth metals, the transition metals and the rare earths or mixtures thereof.

Heat-insulating layer system

The subject matter of the invention is a thermal-insulating material having an essentially magnetoplumbitic crystal structure, a metal substrate having a adhesive layer and a thermal-insulating layer made of the thermal-insulating material on its surface, and a process for coating metal substrates with the thermal-insulating material.

Thermal-insulating material having an essentially magnetoplumbitic crystal structure

Thermal-insulating material provided on a metal substrate by means of an EB-PVD process includes a metal having a substantially magnetoplumbitic crystal structure and having a chemical composition according to general formula: LnMQA1O. The thermally-insulated metal substrate may advantageously include an adhesive layer provided between the surface of the metal substrate and the thermal-insulating layer. The process for producing the thermal-insulated metal substrate includes applying the thermal-insulating material onto a surface of the metal substrate employing an EB-PVD process.

The present invention relates to a process for vapor-depositing zirconium dioxide on ceramic or metallic substrates, and the heat-insulating layers obtainable by such process.

Ceramic heat-insulating layers with club-structure

The present invention relates to a method for coating monocrystalline or polycrystalline metal substrates with a ceramic heat-insulating layer of zirconia by electron-beam vapor deposition, and to a method for coating turbine blades made of Ni-based superalloys. The method is characterized in that the metal substrate is moved during the vapor deposition in terms of a superposition of two rotational motions around horizontal axes, but in essentially perpendicular directions.

Heat-insulating layers on monocrystalline and polycrystalline metal

The present invention relates to a process for vapor-depositing zirconium dioxide on ceramic or metallic substrates, and the heat-insulating layers obtainable by such process. In particular, the invention relates to a process for vapor-depositing zirconium dioxide, optionally doped with rare-earth metal oxides or mixtures of such oxides, on ceramic or metallic substrates in a range of substrate temperatures of from 600 to 1550.degree. C. while the substrate is continuously rotated at a speed in the range of from 1 to 300 rpm, characterized in that, following the nucleation phase, the rotational speed and the temperature are adjusted to a range defined by the equations: ##EQU1## where T represents the substrate temperature in .degree. K, and .omega. represents the rotational speed of the substrate in rpm, wherein the rotational speed is varied continuously or discontinuously, or alternatively in alternating senses of rotation.

Growing community of inventors

Neunkirchen-Seelscheid, Germany

Uwe Schulz