Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Ralf Stolle

Thomas Uihlein

Heinrich Walter

Stefan Schneiderbanger

Michael Schober

Michael Strasser

Josef Linska

Klaus Schweitzer

Thomas Cosack

Joerg Windprechtinger

Wolfgang Wachter

Markus Gether

Michael Pulver

Georg Wahl

Andreas Kaehny

Josef Lachner

Werner Moosrainer

Philipp Utz

Jörg Windprechtinger

A blade for a turbomachine is provided. The blade at its blade tip () includes blade tip armor (), and an erosion protection layer () above the blade tip armor. For the blade, the erosion protection layer in the area of the blade tip has a layer thickness in the range of 5 μm to 100 μm, in particular 10 μm to 50 μm.

Blade for a turbomachine including blade tip armor and an erosion protection layer, and method for manufacturing same

A method for manufacturing a blade () for a turbomachine, the blade having a hardfacing on its tip () and an erosion-protection coating () at least on its airfoil () is provided. Initially, a blade tip hardfacing is applied to the blade tip and, subsequently, a mask () is positioned in the region of the blade tip hardfacing, the mask covering the blade tip hardfacing, and, subsequently, the erosion-protection coating is deposited. The mask is removed after the erosion-protection coating is completed. A blade for a turbomachine, the blade having a hardfacing on its tip () and an erosion-protection coating () at least on its airfoil () is also provided. The erosion-protection coating at least partially covers the blade tip hardfacing, and the thickness of the erosion-protection coating decreases continuously in and/or toward the region of the blade tip hardfacing.

Masking method for producing a combination of blade tip hardfacing and erosion-protection coating

The present invention relates to a method for producing a blade or blade arrangement of a turbomachine, which features the following steps: Furthermore, the invention relates to correspondingly produced blades or blade arrangements.

Method of producing blades or blade arrangements of a turbomachine with erosion protection layers and correspondingly produced component

A method and device for partially masking a component or assembly during a coating process, the device including at least one masking plate for separating a region to be coated from a region to be masked, the masking plate having at least a portion of at least one opening which conforms closely to the contour of the component and is adapted to allow passage of the component therethrough is provided. In masked region, a gap is present along opening, at least one sealing element being disposed at the gap on the side of the masked region.

Device and method for partially masking a component zone of a component

A thermal barrier layer for metallic components, in particular for gas turbine components which are subject to high temperatures or hot gas, is disclosed. The thermal barrier layer includes an inner contact layer and an outer top layer, where the inner contact layer is applied to a surface of the component via an adhesion-promoting layer that is disposed therebetween, and between the outer top layer and the inner contact layer an intermediate layer is formed.

Thermal barrier layer

A process for producing a thermal barrier coating, in which organometal complexes of zirconium and at least one stabilizing element selected from the group of the alkaline earth metals or rare earths are provided as starting substances, the starting substances are evaporated by heating and the coating gases that are generated in this manner are transported to a component to be coated, which is heated at a deposition temperature, where they are broken down so that a layer is deposited, in which process, in order to produce a thermal barrier coating with a columnar structure and a sufficient layer thickness, the starting substances are heated, at a process pressure of 0.5 to 50 mbar, to at most 250&deg; C. so that the coating gases are formed, and the coating gases are transported to the component to be coated, the surface of which is heated at a deposition temperature of between 300&deg; C. and 1100&deg; C.

Method for producing a heat insulating layer

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Wolfratshausen, Germany

Ralf Stolle