Patent application number | Description | Published |
20080317998 | WEAR-RESISTANT COATING - The present technology generally relates to a wear-resistant coating, especially for gas turbine components, comprising a horizontally segmented or multilayered structure, i.e. at least one relatively hard, ceramic layer and at least one relatively soft, metallic layer. The ceramic layer and the metallic layer are alternately arranged on top of each other in such a way that an external layer forming an external surface of the wear-resistant coating is embodied as a ceramic layer. According to the invention, at least the external, ceramic layer is segmented in a column-type manner in a vertical direction. | 12-25-2008 |
20090233111 | Thermal Barrier Coating System - The invention relates to a thermal insulation layer system ( | 09-17-2009 |
20090269207 | COMPONENT, IN PARTICULAR, A GAS TURBINE COMPONENT - A component, specifically a component for a gas turbine, having a main body of a base material and a wear protection coating applied to a surface of the main body, specifically a protective coating against corrosion and/or oxidation and/or erosion, is disclosed. A barrier coat is applied between the main body and the wear protection coating to protect the main body during chemical or electrochemical decoating of the component. | 10-29-2009 |
20090297876 | THERMAL BARRIER LAYER - 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. | 12-03-2009 |
20090302004 | METHOD FOR REMOVING THE COATING FROM A GAS TURBINE COMPONENT - A method for removing the coating from a gas turbine component, namely for the complete or partial removal of a multilayer wear protection coating from the surface of the gas turbine component, the wear protection coating having at least one relatively hard ceramic layer and at least one relatively soft metallic layer, wherein, in order to remove the multilayer wear protection coating, the gas turbine component is alternately positioned in two different chemical baths, a first bath being used exclusively for the removal of each relatively hard ceramic layer, and a second bath being used exclusively for the removal of each relatively soft metallic layer of the wear protection coating. | 12-10-2009 |
20100064515 | METHOD FOR REPAIRING AND/OR REPLACING INDIVIDUAL ELEMENTS OF A GAS TURBINE COMPONENT - The present invention relates to a method for repairing and/or replacing individual elements of a gas turbine component ( | 03-18-2010 |
20100108538 | METHOD FOR STRIPPING A COMPONENT - A method for stripping a component, in particular a gas turbine component, to completely or partially remove a multilayer or sandwich antiwear coating from the surface of the component, the antiwear coating including at least one relatively hard ceramic layer and at least one relatively soft metallic layer is disclosed. According to the present invention, in order to remove the multilayer or sandwich antiwear coating, the component is placed in a bath of an alkaline electrolyte, the component placed in the electrolyte being stripped at a current density of between 1 A/dm | 05-06-2010 |
20100119376 | INLET CONE FOR JET ENGINE - Inlet cone ( | 05-13-2010 |
20100143108 | Device for the Protection of Components Having A Flammable Titanium Alloy From Titanium Fire, and Method for the Production Thereof - The use of titanium-based materials in the manufacturing of gas turbines, especially of engines, and, in particular, of compressors is made possible in that a device is devised that protects the components (guide vanes, guide vane stages, rotor blades, rotor blade stages) that are subject to the action of titanium fire and/or FODs by employing a layer system that includes at least two layers, is situated on the surface of the components to be protected, and is bonded thereto, as the case may be, via an adhesion-promoting layer is disclosed. The outermost layer is ceramic; the layer that is subjacent thereto is of metallic nature. Additional layers can optionally follow, ceramic and metallic layers alternating with one another. Moreover, a method is provided for producing the device. Through the at least partial use of titanium alloys, in particular for guide vanes of gas turbines, the weight of compressors can be significantly reduced in that the need for the nickel- or steel-based structural materials used under the related art is eliminated in favor of lighter titanium alloys. | 06-10-2010 |
20100143110 | VANE FOR A COMPRESSOR OR A TURBINE OF AN AIRCRAFT ENGINE, AIRCRAFT ENGINE COMPRISING SUCH A VANE AND A METHOD FOR COATING A VANE OF AN AIRCRAFT ENGINE - An aircraft engine comprising a compressor and at least one turbine is disclosed. The compressor and the turbine are each provided with vanes, each of which has a blade that forms a suction side and a pressure side, where at least one first of the blades is coated with a protective layer in order to reduce the erosion or wear. The layer is applied such that at least two areas are formed that adjoin each other at a boundary line. The first area has a protective layer that has a substantially constant first thickness and the second area is free of the protective layer or has the protective layer with a substantially constant second thickness, the second thickness differing from the first thickness. The boundary line has at least two points, of which the connecting line differs from the course of the boundary line between the two points. | 06-10-2010 |
20100226782 | Turbomachine blade with a blade tip armor cladding - A blade of a turbomachine such as a gas turbine includes a blade vane with a blade tip and a blade base. A blade tip armor cladding is applied on the blade tip. A coating covers at least the armor cladding and includes at least one multilayer coating system, and preferably plural such coating systems stacked repetitively on one another. Each coating system includes at least two different layers stacked successively on one another, with one layer of a metal material closer to the blade tip and one layer of a ceramic material farther from the blade tip. | 09-09-2010 |
20100239429 | WEAR PROTECTION COATING - The English-language Abstract from the international application is to be retained and is therefore not duplicated in the specification. | 09-23-2010 |
20100263694 | DECOATING DEVICE FOR AXIALLY SYMMETRIC COMPONENTS, PARTICULARLY FROM AIRCRAFT ENGINES - A decoating device for axially symmetric components, particularly from aircraft engines is provided, the decoating process being carried out through the use of a decoating fluid-which is brought on a localized basis into contact with the component to be decoated, a receptacle for holding the decoating fluid being provided that rotates at least about one axis of rotation, and the decoating fluid surface forming a rotation paraboloid in response to the rotation, the component(s) to be decoated on a localized basis being accommodated in the receptacle and being dipped on the radially outer side into the decoating fluid. A decoating device is thereby devised which makes it possible for radially symmetric components to be decoated in the radially outer region in a simple process. | 10-21-2010 |
20100284817 | METHOD FOR PRODUCING A BLISK OR A BLING, COMPONENT PRODUCED THEREWITH AND TURBINE BLADE - A method for producing a blisk (bladed disk) or a bling (bladed ring) of a gas turbine is disclosed. The method includes the following steps: a) producing a turbine blade by joining a blade to an adapter element consisting of a metal material that is suitable for fusion welding, the adapter element being used to form a blade root of the turbine blade, and b) joining the turbine blade to a rotor disk consisting of a metal material that is suitable for fusion welding or to a rotor ring consisting of a metal material that is suitable for fusion welding in such a manner that the turbine blade is arranged on the outer periphery of the rotor disk or of the rotor ring. A component of a gas turbine or of a high-pressure or low-pressure compressor, especially a blisk or bling, and a turbine blade are also disclosed. | 11-11-2010 |
20110020548 | DEVICE AND METHOD FOR THE PARTIAL COATING OF COMPONENTS - A device and method for the partial coating of a component, particularly for the coating of components of a gas turbine or an aircraft engine, is disclosed. The device includes at least one base receptacle for at least partially receiving the component and a first partial region of the component not to be coated. The device further includes at least one plate-shaped cover that can be positioned in the base receptacle, where the cover includes at least one recess or opening for a second partial region of the component to be coated to pass through. The shape of the recess or opening corresponds to the profile of the component in the region between the partial region not to be coated and the partial region to be coated. | 01-27-2011 |
20110045264 | EROSION PROTECTION COATING - The invention relates to an erosion protection coating ( | 02-24-2011 |
20110129353 | METHODS FOR JOINING A MONOCRYSTALLINE PART TO A POLYCRYSTALLINE PART BY MEANS OF AN ADAPTER PIECE MADE OF POLYCRYSTALLINE MATERIAL - The present invention relates to methods for joining a rotationally asymmetrical part, preferably a turbine blade, which is made of a monocrystalline material, to a part, preferably a rotor core, which is made of polycrystalline material, having the method steps of:—joining the rotationally asymmetrical part to an adapter piece made of polycrystalline material by means of rotational friction welding, and—joining the adapter piece to the part made of polycrystalline material. The present invention also relates to a turbine blisk having a rotor core made of polycrystalline material and turbine blades made of monocrystalline material. | 06-02-2011 |
20110217176 | METHOD FOR CONNECTING AT LEAST ONE TURBINE BLADE TO A TURBINE DISK OR A TURBINE RING - The invention relates to a method for connecting at least one turbine blade ( | 09-08-2011 |
20110255981 | METHOD FOR THE PRODUCTION OF AN INTEGRALLY BLADED ROTOR, AND ROTOR - A method for manufacturing an integrally bladed rotor ( | 10-20-2011 |
20110290861 | METHOD FOR PRODUCING A BLADE PLATING ON A BLADE FOR A TURBOMACHINE - The invention relates to a method for producing a blade tip plating ( | 12-01-2011 |
20110299996 | ANTI-EROSION COATING SYSTEM FOR GAS TURBINE COMPONENTS - A gas turbine component and a method for producing an anti-erosion coating system are disclosed. The gas turbine component includes a basic material, on which an anti-erosion coating system is provided that is a multilayer system including at least one ductile metal layer and at least one hard, ceramics-containing layer for forming a partial anti-erosion system. At least one anti-corrosion layer that has a lower electrochemical potential than the basic material is provided between the partial anti-erosion system and the basic material, thus providing cathodic corrosion protection. | 12-08-2011 |
20120141822 | ANTI-WEAR COATING AND COMPONENT COMPRISING AN ANTI-WEAR COATING - An anti-wear coating, in particular an anti-erosion coating, which is applied to a surface of a component that is stressed under fluid technology and is to be protected, in particular a gas turbine part, is disclosed. The anti-wear coating includes one or more multilayer systems applied in a repeating order to the surface to be coated, and the/each multilayer system includes at least one relatively soft metallic layer and at least one relatively hard ceramic layer. All the layers of the/each multilayer system are based on chromium, and a diffusion barrier layer is applied between the surface to be protected and the multilayer system(s). | 06-07-2012 |
20130174869 | CLEANING OF A TURBO-MACHINE STAGE - The invention relates to a method for cleaning a turbo-machine stage ( | 07-11-2013 |
20130280480 | ANTI-WEAR COATING - The invention relates to an anti-wear coating, specifically for components which are subject to erosion under mechanical loading, in particular for gas turbine components, said coating comprising at least two different individual layers which preferably alternate with one another multiply and are applied to a surface of a component which is to be coated. The individual layers comprise a ceramic main layer ( | 10-24-2013 |