| Patent application number | Description | Published |
|---|
| 20080305276 | Method of Applying Hot Gas Anticorrosion Layers - A method for applying hot gas anticorrosion layers to high-temperature-resistant alloys, either nickel-based or cobalt-based alloys, in the form of a gradient layer consisting of one or more elements of the platinum group in combination with aluminum. The components are introduced into a directional high-temperature, high-enthalpy, free jet of solid, liquid or gaseous precursors in mixing ratios such that defined concentration gradients can be established in the layer. | 12-11-2008 |
| 20090008265 | Method for producing aerodynamic structures during the production of integrally bladed gas turbine rotors - The invention relates to a method for the production of aero-dynamic structures during the production of integrally bladed gas turbine rotors. Aerodynamic structures of an integrally bladed gas turbine rotor are produced on a rotor disk base body, whereon the end contours are precise, by removing material according to an electrochemical removal process, i.e. by means of an electrochemical machining (ECM)-process. The method comprises the following steps: a) preparing a rotor disk base body which is made of a material which is difficult to machine; b) removing the material which is between the blade wings until a specific dimension is obtained, according to a removal process; c) preparing at least one working electrode in order to finish at least one aerodynamic structure of an integrally bladed gas turbine rotor. The contours of the or each of the working electrodes are adapted to the contours of the aerodynamic structure, which are produced by means of the respective working electrode, such that a gap between the rotor disk base body and a working electrode are produced in an approximately identical manner during the removal process of the material; d) electrochemically machining the or each aerodynamic structure in an electrochemical sinking by placing the rotor disk base body and the or each working electrode in an electrolyte and by applying voltage and/or current, whereby the applied current and/or voltage is temporally pulsed; e) pressure-rinsing the gap which is filled with electrolytes between the aero-dynamic structure and the or each working electrode by a pulsed movement of the or each working electrode. | 01-08-2009 |
| 20090211921 | PROCEDURE FOR THE PRODUCTION AND APPLICATION OF A PROTECTIVE LAYER - The invention at hand relates to a method for processing and repairing a metal component with at least one finished or nearly finished partial component surface and at least one working surface to be further processed by means of an electrochemical treatment process and abutting the at least one finished or nearly finished partial component surface, with the process comprising the following steps: a) application of an electrically conductive layer on at least one area of the at least one finished or nearly finished partial component surface abutting the working surface to be processed, with the layer containing a metal or a metal alloy that has a similar or the same as, or a desiredly different electrochemical erosion behavior than the metal component; and b) electrochemical treatment of the working surface and of the layer, with the layer being completely or nearly completely eroded. The invention moreover relates to a component of a gas turbine or of a high or low pressure compressor. | 08-27-2009 |
| 20100012507 | METHOD FOR PRODUCING GEAR WHEELS - A method for manufacturing gear wheels, specifically transmission gear wheels, is disclosed. An embodiment of the method includes the following steps: a) preparation of a base body for a gear wheel, b) electrochemical processing of the base body by a precise electrochemical machining process (PECM process), where several recesses running between the teeth of the gear wheel are made simultaneously electrochemically to manufacture the teeth of the gear wheel. | 01-21-2010 |
| 20100202889 | METHOD FOR PRODUCING A LIGHTWEIGHT TURBINE BLADE - A method for producing a lightweight turbine blade for a gas turbine is disclosed. In an embodiment, the method includes casting of a blade element with a blade wall and at least one cavity enclosed by the blade wall. The blade wall is at least partially reduced in thickness by machining after the casting. This provides a method for producing a blade element, in which the wall thickness of the blade wall can be adapted to the mechanical load of the blade element, and the weight of the blade element can be reduced at the same time. | 08-12-2010 |
| 20100270168 | METHOD FOR REMOVING MATERIAL FROM A COMPONENT, AND ELECTRODE - A method for removing material from a component that is connected as an anode is disclosed. In an embodiment, an electrode that is connected as a cathode is guided to the component such that a gap is formed, an electrolyte is introduced into the gap, and a closed system is formed for the electrolyte by the formation of a duct. The electrolyte is continuously guided from an inlet opening to an outlet opening of the duct. Forming the duct, e.g., by guide elements that are mounted on the electrode, ensures that only those surface parts of the component to be machined from which material is to be removed enter in contact with the electrolyte while the other surface parts do not enter in contact with the electrolyte. Since the electrolyte is continuously guided across the surface, used electrolyte is continuously discharged along with residual matter while fresh electrolyte is delivered. | 10-28-2010 |
| 20100319194 | METHOD FOR PRODUCING INTEGRALLY BLADED ROTORS - A method for producing integrally bladed rotors comprises the following steps: a) defining and providing a blade profile of a blade to be manufactured with a pre-contour and a theoretical contour; b) producing at least two sectional planes of the blade profile, which sectional planes run vertically to a threading axis of the blade profile and of the blade to be manufactured; c) determining a point of rotation per sectional plane to produce an interval between the pre-contour and the theoretical contour that is approximately the same circumferentially, which points of rotation are located on a connecting line running parallel to the threading axis; and d) providing a base rotor body and electrochemically working the base rotor body in order to produce a raw blade with the blade pre-contour by movement of a hollow electrode into the base rotor body, the electrode movement including advancing motion along the connecting line superposed by rotation at the points of rotation, and which hollow electrode has an inner contour adapted to the pre-contour of the raw blade at least in an end area that is moved into the base rotor body. | 12-23-2010 |
| 20110002789 | METHOD FOR PRODUCING AND REPAIRING A PART, AND PART OF A GAS TURBINE - The invention relates to a method for producing and repairing a part comprising at least two joined metal components, especially components of a gas turbine. In said method, corresponding joining surfaces of the components are joined together and connected by means of a pressure welding process, a machining allowance in the area of a joining zone of the two joining surfaces is upset during the joining process, and once the two components have been joined together, the machining allowance is machined by means of a precise electrochemical machining (PECM) process until a predefined final contour of the part has been obtained. The invention further relates to a gas turbine part obtained by means of the disclosed method. | 01-06-2011 |
