Patent application number | Description | Published |
20080214347 | Drive Unit Comprising Nested Electric Motors - A drive unit ( | 09-04-2008 |
20080221757 | Method for operating an actuator, especially an electric actuator in a stabilizer arrangement - Method for operating an adjustable stabilizer arrangement, comprising an actuator, which applies actuator torque to stabilizer sections as a function of a command variable to influence the rolling movement of a motor vehicle body, where sensors are used to detect the movement of the motor vehicle body and the movements of the wheels, where an operating movement of the actuator supplies a variable which can be used to determine the actuator torque, upon which is superimposed an adjustment signal for the actuator, and where the variable is modified by a weighting factor. | 09-11-2008 |
20090076767 | DEVICE FOR DETERMINING A NEUTRAL POSITION OF TWO COMPONENTS - A device for determining a neutral position of two components ( | 03-19-2009 |
20090189557 | METHOD AND ARRANGEMENT FOR CONTROLLING AN ELECTRIC DRIVE - A method for controlling an electric drive is proposed, in which, in the event of a fault, a motor control unit of an electric motor implements a safety measure to change over to a secure operating condition, such that when a faulty three-phase current feed to the electric motor is detected, a fault-associated operating mode is activated. In addition, an arrangement for controlling an electric drive comprising an electric motor with a motor control unit is proposed, which implements a safety measure in the event of a fault so as to change over to a secure operating condition, such that when a faulty three-phase current feed to the electric motor is detected, the motor control unit activates a fault-associated operating mode. | 07-30-2009 |
20100019741 | CIRCUIT ARRANGEMENT AND METHOD FOR REGULATING THE CURRENT IN AN ON-BOARD ELECTRICAL POWER SUPPLY SYSTEM OF A VEHICLE - A circuit arrangement for regulating the current in an on-board electric power supply system of a vehicle, with a controllable damping resistance, an energy accumulator and an electronic control unit. The damping resistance is adjustable to satisfy a control condition, such that generator current flowing through the control unit can be compensated by a counter-current originating from the energy accumulator and flowing through the damping resistance, having regard to a specified current limit value. In a method for controlling the circuit arrangement, generator current flowing through the control unit is compensated by a counter-current originating from the energy accumulator and flowing through the damping resistance, and the damping resistance is controlled, in such a manner, that a predetermined current limit value is taken into account. | 01-28-2010 |
20100094504 | MOTOR VEHICLE AND METHOD FOR ADJUSTING ASSEMBLIES THEREOF ON THE DRIVE TRAIN SIDE - A motor vehicle, with a drive train comprising a drive assembly, a transmission and wheels ( | 04-15-2010 |
20110004348 | ARRANGEMENT FOR TRANSMITTING DATA AND/OR SIGNALS IN A TRANSMISSION - An arrangement for transmitting data and/or signals between a transmission control device ( | 01-06-2011 |
20120299421 | ELECTRODYNAMIC ENGINE WITH A THREE-POINT SUSPENDED SHAFT AND USAGE OF A THIRD BEARING AS AN ASSISTING SHAFT MOUNT - The electro dynamic machine ( | 11-29-2012 |
Patent application number | Description | Published |
20080201947 | Method For Repairing Turbo Machine Blades - A method is for repairing turbo machine blades, e.g., gas turbine blades on integrally bladed gas turbine rotors. The method includes at least the following steps: a) providing a turbo machine blade to be repaired or an integrally bladed rotor to be repaired having a damaged blade section; b) removing the damaged blade section from the turbo machine blade or from the integrally bladed rotor resulting in a blade stump; c) clamping the blade stump at least in the region of a flow leading edge and a flow trailing edge of the same in a cooling device; d) applying respectively a punctiform welding bead in the region of the flow leading edge and a flow trailing edge of the blade stump by laser powder build-up welding, the welding beads protruding at least over the flow leading edge and the flow trailing edge; e) applying material by laser powder build-up welding between the welding beads in the region of the or each removed blade section for restoring the respective blade section. | 08-28-2008 |
20100028158 | HIGH-PRESSURE TURBINE BLADE AND PROCEDURE FOR REPAIR OF HIGH-PRESSURE TURBINE BLADES - The invention relates to a procedure for repair of high pressure turbine blades of an aircraft engine, with the steps: —separating a damaged section of the high pressure turbine blade; and—generating a section to replace the separated section on or upon the high pressure turbine blade by means of laser beam generation from the powder bed, as well as a high pressure turbine blade. | 02-04-2010 |
20100074755 | METHOD FOR REPAIRING TURBINE BLADES - A method for repairing turbine blades by replacing at least a part of the blade profile, the method having: a) manufacture of a replacement blade part; b) separation of the damaged area with a standardized cutting plane, leaving behind a remaining blade; c) matching of the replacement blade part to the actual geometry of the remaining blade; d) connecting or joining of the replacement blade part to the remaining blade by soldering of at least one web and welding of an outer contour. | 03-25-2010 |
20100151145 | DEVICE AND METHOD FOR THE REPAIR OR PRODUCTION OF BLADE TIPS OF BLADES OF A GAS TURBINE, IN PARTICULAR OF AN AIRCRAFT ENGINE - The invention relates to a device for the production or repair of a blade for a gas turbine, said device comprising: a holding device for holding a blade or an aerofoil of a blade; a lowering mechanism for lowering the blade or the aerofoil; a container for receiving power and/or for receiving the blade or the aerofoil; a heating device; and a radiation source, wherein the heating device is formed as an induction coil. | 06-17-2010 |
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 |
20110198390 | METHOD FOR PRODUCING OR REPAIRING INTEGRALLY BLADED GAS TURBINE ROTORS - The invention relates to a method for producing integrally bladed gas turbine rotors, especially of integrally bladed turbine rotors, wherein rotating blades ( | 08-18-2011 |
20110219616 | METHOD FOR REPLACING AN INNER DISK ELEMENT OF AN INTEGRALLY BLADED DISK - The present invention relates to a method for replacing an inner disk element of a blade integrated disk wherein the blade integrated disk has a plurality of recesses in the form of axial through-bores in the joining area. The method begins with filling the axial through-bores, after which the inner disk element of the blade integrated disk is separated from the remaining blade ring. Next a new inner disk element is inserted into the remaining blade ring and the new inner disk element and the remaining blade ring are joined. Finally the axial through-bores are restored. | 09-15-2011 |
20120125980 | METHOD FOR COATING A TURBINE BLADE - A method for hardfacing a metal component surface ( | 05-24-2012 |
20120148413 | METHOD FOR REPLACING A BLADE OF A ROTOR HAVING INTEGRATED BLADES AND SUCH A ROTOR - A method for replacing a blade ( | 06-14-2012 |
20120183404 | METHOD FOR INTEGRALLY CONNECTING BLADES AND DISKS IN ORDER TO FORM A BLADE-DISK UNIT, AS WELL AS CORRESPONDINGLY PRODUCED BLADE-DISK UNIT - A blade-disk unit for a turbine engine includes a disk and a plurality of blades which are integrally connected to the disk, a welding seam being disposed in the joining region between the blade and the disk, which welding seam is situated entirely either in the blade or in the disk. | 07-19-2012 |
20120213659 | METHOD AND DEVICE FOR PRODUCING A COMPONENT OF A TURBOMACHINE - A method for producing a component of a turbomachine is disclosed. The method includes a) layer-by-layer deposition of a powder component material onto a component platform in a region of a buildup and joining zone, where the deposition takes place in accordance with layer information of the component to be produced; b) local layer-by-layer fusion or sintering of the powder component material by energy supplied in the region of the buildup and joining zone, where the buildup and joining zone is heated to a temperature just below a melting point of the powder component material; c) layer-by-layer lowering of the component platform by a predefined layer thickness; and d) repetition of steps a) to c) until the component is finished. A device for producing a component of a turbomachine is also disclosed. | 08-23-2012 |
20130156586 | METHOD FOR CONNECTING A TURBINE BLADE OR VANE TO A TURBINE DISC OR A TURBINE RING - The present invention provides a method for connecting a turbine blade or vane to a turbine disk or to a turbine ring. First, a connecting body is formed on the turbine blade or vane by supplying an additive suitable for fusion welding to a surface of the turbine blade or vane, melting the additive on the surface, with incipient melting of the surface, and allowing the additive and the surface to solidify. Then, the connecting body is connected to the turbine disk or to the turbine ring by means of a fusion welding process. | 06-20-2013 |
20140044532 | PROCESS FOR PRODUCING A TiAl GUIDE VANE RING FOR A GAS TURBINE AND A CORRESPONDING GUIDE VANE RING - Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising:
| 02-13-2014 |
20140308117 | Armoring Sealing Fins of TiAl Vanes by Induction Brazing Hard-Material Particles - A method for armoring TiAl vanes of turbomachines is disclosed. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by an inductive heating process. A TiAl vane for a turbomachine, in particular for an aircraft engine, is also disclosed. The TiAl vane includes a TiAl main part and an armor which consists of a mixture of hard materials and braze material. | 10-16-2014 |
20140342169 | METHOD FOR HARDFACING THE Z-NOTCH OF TIAL BLADES - A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component. | 11-20-2014 |
20150108101 | METHOD FOR MARKING COMPONENTS OF AN AIRPLANE ENGINE - A method of marking components of an aircraft engine, especially turbine blades of a titanium aluminide intermetallic compound. A solid state laser generates a pulsed laser beam with a pulse width of less than 10 ps and the component is marked with the pulsed laser beam. | 04-23-2015 |
20150129583 | METHOD FOR PRODUCING LOW-PRESSURE TURBINE BLADES FROM TiAl - The invention relates to a method for producing a low-pressure turbine blade from a TiAl material by means of a selective laser melting process, wherein during production in the selective laser melting process the already partially manufactured low-pressure turbine blade is preheated by inductive heating, and wherein the selective laser melting process is carried out under protective gas, the protective gas atmosphere containing contaminants of oxygen, nitrogen, and water vapor in each case of less than or equal to 10 ppm. | 05-14-2015 |