| MTU Aero Engines GmbH Patent applications |
| Patent application number | Title | Published |
|---|
| 20120128480 | BLADE - The present invention relates to a blade of a turbomachine, in particular an adjustable guide blade or vane of a gas turbine, having at least one thickened area ( | 05-24-2012 |
| 20120125980 | METHOD FOR COATING A TURBINE BLADE - A method for hardfacing a metal component surface ( | 05-24-2012 |
| 20120125979 | REPAIR OF TURBINE COMPONENTS AND SOLDER ALLOY THEREFOR - A method for repairing a component of a gas turbine and a solder alloy are disclosed. In an embodiment, the method includes applying the solder alloy to the component in an area of the component having a punctiform damage or a linear imperfection, where the solder alloy is a mixture of a NiCoCrAlY alloy and a Ni-based solder. A molded repair part made of the solder alloy is applied to the component in an area of the component having a planar defect. The component is heat treated to solder the molded repair part on the component and to solder the solder alloy applied to the component in the area of the component having the punctiform damage or the linear imperfection. The component is cooled after the heat treating and, following the cooling, the component is further heat treated. | 05-24-2012 |
| 20120121437 | ROTOR FOR A TURBO MACHINE - The invention relates to a rotor ( | 05-17-2012 |
| 20120121436 | ROTOR FOR A TURBO MACHINE - The invention relates to a rotor ( | 05-17-2012 |
| 20120121435 | ROTOR FOR A TURBO MACHINE - The invention relates to a rotor ( | 05-17-2012 |
| 20120121431 | BLADE TIP COATING THAT CAN BE RUBBED OFF - The present invention relates to a method for producing a component, in particular a blade for a gas turbine, wherein a main body ( | 05-17-2012 |
| 20120121427 | JOINING ELEMENT AND METHOD FOR THE PRODUCTION OF SUCH A JOINING ELEMENT AS WELL AS AN INTEGRALLY BLADED ROTOR - A joining element, for example, an adapter, for connecting a rotor blade to a rotor disc or a rotor ring, or a rotor blade per se of an aircraft engine is disclosed. The joining element has a base body and a joining surface, with the joining surface formed by a fusion weldable coating made of a compressed powder that is connected in a positive fit to a contour of the base body. A method for the production of such a joining element, as well as an integrally bladed rotor, is also disclosed. | 05-17-2012 |
| 20120121384 | ROTOR AND METHOD FOR MANUFACTURING A ROTOR FOR A TURBO MACHINE - The invention relates to a rotor for a turbo machine, having rotating blades ( | 05-17-2012 |
| 20120107123 | Shroud Segment to be Arranged on a Blade - A shroud segment to be arranged on a gas turbine blade is disclosed. The shroud segment includes a shroud segment surface and a stiffening structure that is raised relative to the shroud segment surface. The stiffening structure is cross-shaped at least in some areas. | 05-03-2012 |
| 20120103830 | DEVICE AND METHOD FOR ELECTROCHEMICALLY REMOVING A SURFACE OF A COMPONENT - The invention relates to a device ( | 05-03-2012 |
| 20120102701 | METHOD FOR REDUCING VIBRATION AMPLITUDES - The English-language Abstract from the international application is to be retained and is therefore not duplicated in the specification. | 05-03-2012 |
| 20120090175 | METHOD FOR MANUFACTURING AN INTEGRALLY BLADED ROTOR - The invention relates to a method for manufacturing an integrally bladed rotor, whereby several rotating blades are attached to a basic rotor body by welding in such a way that first, grooves into which the rotating blades are introduced by their blade feet or adapters, and which extend substantially in the axial direction of the basic rotor body, are introduced into the basic rotor body radially outside, prior to attaching the rotating blades, then, the rotating blades are welded to the basic rotor body, wherein the grooves are introduced in the rotor body and the blade feet or adapters are formed on the rotating blades in such a way that a central axis of the grooves is positioned obliquely relative to a central axis of the blade feet or the adapters, so that a pre-twisting is formed on the rotating blades when the rotating blades are introduced into the groove. | 04-19-2012 |
| 20120087781 | LAYER SYSTEM FOR ROTOR/STATOR SEAL OF A TURBOMACHINE AND METHOD FOR PRODUCING THIS TYPE OF LAYER SYSTEM - The present invention creates a layer system for the rotor/stator seal of a turbomachine, in particular a compressor, which is disposed between components of the turbomachine and can be run in with a movement of the components relative to one another, in such a way that at least one of the components is run into the layer system, having: a first adhesive layer disposed on at least one of the components; a protective layer disposed on the first adhesive layer; a second adhesive layer disposed on the protective layer; and a running-in layer, which is formed softer than the protective layer and which is disposed on the second adhesive layer. The present invention further provides a method for producing a layer system for the rotor/stator seal of a turbomachine, as well as a turbomachine. | 04-12-2012 |
| 20120080415 | METHOD AND DEVICE FOR PRODUCING A HOLE IN AN OBJECT - A method and device for producing a hole in an object is disclosed. The method includes the generation of a beam for removing material such that a bottom of a borehole is placed in a focus position of the beam, and a removal of material by impingement of the beam on the bottom of the borehole. A repeated placing of the bottom of the borehole in a focus position of the beam in order to compensate for the increased depth of the hole as a result of the removal of material is combined with a step of changing a radiation characteristic of the beam when the bottom of the borehole is repeatedly placed in a focus position. | 04-05-2012 |
| 20120063884 | CLEARANCE CONTROL SYSTEM, TURBOMACHINE AND METHOD FOR ADJUSTING A RUNNING CLEARANCE BETWEEN A ROTOR AND A CASING OF A TURBOMACHINE - The invention relates to a clearance control system for adjusting a running clearance (L) between a rotor ( | 03-15-2012 |
| 20120057988 | ROTOR FOR A TURBOMACHINE - The invention relates to a rotor ( | 03-08-2012 |
| 20120055222 | METHOD AND APPARATUS FOR SURFACE HARDENING A COMPONENT, WHICH IS MADE OF AN INTERMETALLIC COMPOUND AT LEAST IN THE REGION OF THE SURFACE TO BE HARDENED - A method and apparatus for surface hardening a component, particularly an aircraft construction component, is disclosed. A force is applied to the surface of the component, which is made of an intermetallic compound at least in the region of the surface to be hardened. The component is heated at least in the region that is made of the intermetallic compound to a temperature higher than the standard temperature. The temperature is set such that a ductility of the intermetallic compound at the temperature is increased compared to a ductility of the intermetallic compound at the standard temperature. The apparatus includes a hardening tool and a heating device where the component is heated to a temperature higher than the standard temperature and the temperature is set such that a ductility of the intermetallic compound at the temperature is increased compared to a ductility of the intermetallic compound at the standard temperature. | 03-08-2012 |
| 20120045313 | FLOW DEVICE COMPRISING A CAVITY COOLING SYSTEM - A flow device having a cooling-air injection system for injecting cooling air into cavities ( | 02-23-2012 |
| 20120039706 | COMPRESSOR HAVING A GUIDE VANE ASSEMBLY WITH A RADIALLY VARIABLE OUTFLOW - A compressor is disclosed. The compressor has at least one guide vane assembly which can be adjusted to change the outflow angle, and a rotor which is connected downstream of the guide vane assembly. The guide vane assembly and rotor are arranged between a housing and a hub of the compressor. The guide vane assembly is divided in the direction of extension from the housing to the hub into two or more sections which can be radially adjusted relative to one another, or has a clearance radially in the direction of extension, the clearance allowing a substantial amount of flow to pass. | 02-16-2012 |
| 20120034092 | METHOD FOR PRODUCING A PLATING OF A VANE TIP AND CORRESPONDINGLY PRODUCED VANES AND GAS TURBINES - The invention relates to a method for producing a plating ( | 02-09-2012 |
| 20120027603 | DUAL BLISKS IN THE HIGH-PRESSURE COMPRESSOR - The invention relates to a high-pressure compressor of a gas turbine having at least one blisk, specifically a disk with a plurality of blades that are disposed on the disk, wherein the blisk has at least one titanium material from the group that comprises Ti-6246 and Ti-6242, wherein the materials of the disk and the blades of the blisk differ in their chemical composition and/or their microstructure. The blades are welded to the disk, in particular, by means of a pressure welding method supported by high-frequency current, whereby the current is conducted through the joint surfaces and leads to local limited melting therein. | 02-02-2012 |
| 20120011703 | DEVICE FOR FIXING WORKPIECES ON A WORKPIECE CARRIER AND METHOD FOR MACHINING WORKPIECES - A device for fixing at least one workpiece on at least one workpiece carrier is disclosed. The device has at least one engaging and fixing element designed as a mold for releasable arrangement between the workpiece and the workpiece carrier, where at least one first mold surface is designed for receiving a first volume of adhesive and for fixing an adhesive surface of the workpiece to the engaging and fixing element. At least one second mold surface of the engaging and fixing element is designed for receiving a second volume of adhesive and for fixing a contact and adhesive surface of the workpiece carrier to the engaging and fixing element. A method for machining workpieces is also disclosed. | 01-19-2012 |
| 20120003078 | TURBINE SHROUD - A turbine blade assembly is disclosed. The turbine blade assembly includes a turbine blade and an outer shroud section at the radially outer end of the turbine blade. The turbine blade intersects or joins the shroud section. For increased stiffness, the shroud section has a reinforcing rib extending along its outer face and extending substantially in the direction of the principal axis of inertia. | 01-05-2012 |
| 20120000601 | Device and Method for Fixing a Component in Position on a Component Carrier - A device for fixing a component ( | 01-05-2012 |
| 20110318172 | TANDEM BLADE DESIGN - The present invention relates to a tandem blade design for an axial turbomachine, comprising a front blade and a rear blade disposed with an offset thereto in the circumferential direction and in the axial direction. The rear blade is profiled and positioned with respect to the front blade such that it raises the speed level at the trailing edge of the front blade in a predetermined working range in interaction with the front blade. | 12-29-2011 |
| 20110305578 | Component for a gas turbine and a method for the production of the component - A component for a gas turbine, especially a blisk or a bling, whereby the component includes a rotor base ( | 12-15-2011 |
| 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 |
| 20110293408 | SEALING APPARATUS AT THE BLADE SHAFT OF A ROTOR STAGE OF AN AXIAL TURBOMACHINE - A turbomachine is disclosed. The turbomachine includes a rotor, a plurality of blades arranged side by side on the rotor in a circumferential direction, and a plurality of sealing apparatuses each disposed on a respective blade shaft of the plurality of blades. Each of the plurality of sealing apparatuses includes first and second bottom plates protruding in a respective axial direction on the respective blade shaft and first and second bulkheads which extend in a radial direction along the respective blade shaft and form a double-walled seal in the axial direction. A respective rounded or parabolic transitional cross-section from the bottom plates to the bulkheads is provided and at least one of the bulkheads is offset with respect to a blade root edge of the respective blade shaft in a direction toward a radial longitudinal axis of the respective blade shaft. | 12-01-2011 |
| 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 |
| 20110268890 | METHOD AND DEVICE FOR INDUCTIVELY HEATING A COMPONENT | 11-03-2011 |
| 20110265328 | METHOD FOR MOUNTING AN INTEGRAL INNER RING OF A TURBOCOMPRESSOR STATOR - A method for mounting an integral inner ring ( | 11-03-2011 |
| 20110255991 | INTEGRALLY BLADED ROTOR DISK FOR A TURBINE - An integrally bladed rotor disk ( | 10-20-2011 |
| 20110255981 | METHOD FOR THE PRODUCTION OF AN INTEGRALLY BLADED ROTOR, AND ROTOR - A method for manufacturing an integrally bladed rotor ( | 10-20-2011 |
| 20110255980 | Method for repairing a rotor system of a turbomachine, annular element for a rotor system of a turbomachine, and rotor system for a turbomachine - A method for repairing a rotor system ( | 10-20-2011 |
| 20110255973 | DAMPING ELEMENT AND METHOD FOR DAMPING ROTOR BLADE VIBRATIONS, A ROTOR BLADE, AND A ROTOR - A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine is disclosed. A damping element is guided on a support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with a lower platform area of a rotor blade. A circumferential contact surface is formed by an elevation on the lower platform area, where the circumferential contact surface is a limit stop for a movement of the damping element. | 10-20-2011 |
| 20110250072 | REPLACEMENT PART FOR A GAS TURBINE BLADE OF A GAS TURBINE, GAS TURBINE BLADE AND METHOD FOR REPAIRING A GAS TURBINE BLADE - A replacement part for a gas turbine blade is disclosed. The replacement part is designed to replace a removed portion of the blade, the portion including a section of the blade tip and a section of the leading edge and/or the trailing edge, and the replacement part having at least one joining side with which it can be brought to contact with the blade that is reduced by the removed portion and joined therewith. The joining side has at least one section, the cross-section of which is U-shaped. | 10-13-2011 |
| 20110242725 | CAPACITOR ARRANGEMENT AND METHOD FOR PRODUCING A CAPACITOR ARRANGEMENT - The present invention relates to a capacitor arrangement having a capacitor and a first terminal plate and a second terminal plate. The capacitor has a first contact face and a second contact face arranged opposite one another. The terminal plates are each connected to one of the contact faces and have protrusions on one end suitable for engaging in recesses in a power rail. | 10-06-2011 |
| 20110238200 | METHOD FOR DETERMING THE MACHINING QUALITY OF COMPONENTS, PARTICULARLY FOR METAL CUTTING BY NC MACHINES - The present invention relates to a method for determining a selected machining quality of components in a manufacturing process, particularly during metal cutting, having at least the following method steps:
| 09-29-2011 |
| 20110227289 | BRUSH SEAL - The invention relates to a brush seal to seal a gap between two structural components, in particular between a rotor and a stator, having a bristle packet comprising bristles, with the bristles of the bristle packet being firmly attached to a bristle carrier via a fixation element. According to the invention, the bristle packet comprises several layers of bristles that are made of different materials. | 09-22-2011 |
| 20110226755 | METHOD FOR JOINING COMPONENTS - A method for joining at least two components by inductive high-frequency pressure welding is disclosed. The first component has a first material structure with a first hardness and the second component has a second material structure with a second hardness which is smaller than the first hardness. Both components are inductively heated in the region of the joining surfaces and are subsequently pressed together by a compressive force. The joining surface of the first component with the first hardness, which is greater than the second hardness of the second component, is pre-contoured in a spherical, conical or convex manner prior to joining the two components. | 09-22-2011 |
| 20110225979 | TURBO ENGINE - The invention relates to a turbo engine, in particular a gas turbine aircraft engine, having a plurality of compressor components, at least one combustion chamber and a plurality of turbine components, wherein at least one support rib ( | 09-22-2011 |
| 20110225822 | ASSEMBLY MECHANISM COMPRISING A TENSION ANCHOR AND CORRESPONDING METHOD FOR A ROTOR SYSTEM OF AN AXIAL TURBO ENGINE - The invention relates to a device ( | 09-22-2011 |
| 20110223325 | MASK FOR KINETIC COLD GAS COMPACTING - A mask and method for kinetic cold gas compacting is disclosed. The mask includes a body for covering a not-to-be-coated region of a substrate to be coated having a work side exposed to a coating substance. The work side has a hardness such that the work side is not plastic deformable by a striking coating particle. | 09-15-2011 |
| 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 |
| 20110217457 | REPAIR METHOD - A method for repairing gas turbine components, in particular gas turbine blades, including at least the following steps: a) preparing a gas turbine component to be repaired; b) removing a damaged portion from the gas turbine component to be repaired, thereby forming a plane separation surface; c) placing the gas turbine component at least partly in a process chamber in such a way that the plane separation surface extends approximately horizontally within the process chamber; d) filling the process chamber with a metal powder that is bonding-compatible with the material of the gas turbine component to be repaired, namely up to the level of the separation surface; e) building up the removed portion on the separation surface by depositing metal powder in layers onto the separation surface and by fusing the metal powder, which has been deposited in layers onto the separation surface, to the separation surface. | 09-08-2011 |
| 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 |
| 20110213569 | METHOD AND DEVICE FOR DETECTING CRACKS IN COMPRESSOR BLADES - A detection device for detecting cracks in compressor blades, having non-contacting sensors distributed in several planes and disposed in the vicinity of the rotor detects cycle times of blades at the sensors and/or relative and absolute changes in a gap width between a blade and the compressor housing. The captured data are compared to corresponding reference data in a memory device and analyzed. | 09-01-2011 |
| 20110200470 | COMPRESSOR - A compressor is disclosed, which has an inflow channel for guiding a compression medium into a compressor housing, a pressure chamber formed within the compressor housing, and a liner segment with nozzles that transport the compression medium from the pressure chamber to a rotor. The nozzles are formed in the liner segment as a plurality of nozzles arranged in a group in fan-like manner. | 08-18-2011 |
| 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 |
| 20110189014 | GAS TURBINE AND METHOD FOR VARYING THE AERODYNAMIC SHAPE OF A GAS TURBINE BLADE - A gas turbine and a method for varying the aerodynamic shape of a blade of the gas turbine is disclosed. The blade has a coating made of a shape-memory alloy. Hot air is transported via channels to the coated blade in order to cause a phase change in the coating and an aerodynamic shape change to the blade. | 08-04-2011 |
| 20110186442 | METHOD FOR MACHINING A METAL COMPONENT - The invention concerns a method for the machining of a metallic structural component, particularly a structural component of a gas turbine, by means of finishing with a pulsed electrochemical ablation process, whereby the structural component features a pre-contour, to be finished, with different over-measures. The method is characterized by the following processing steps: a) determination of the different over-measures of the pre-contour, and b) bilateral and simultaneous finishing by means of a simultaneous feed of respectively at least one electrode disposed on different sides of the structural component, whereby the feed velocity of the electrode in the area of the largest over-measure of the pre-contour is higher than the feed velocity in the area of the smaller over-measure of the pre-contour. | 08-04-2011 |
| 20110186439 | DEVICE FOR USE IN A METHOD FOR THE PRODUCTION OF A PROTECTIVE LAYER AND METHOD FOR THE PRODUCTION OF A PROTECTIVE LAYER - A device for use in a method for the galvanic production of a protective layer featuring hard material particles on a component of a turbomachine, particularly a blade tip armoring of a blade tip of a rotor blade, is disclosed. The device includes a pouch-, bag- or sack-like receiving device for receiving the hard material particles and is made of a net-, screen- or non-woven-like material that is pervious to an electrochemical coating solution and has a mesh size smaller than the diameter of the hard material particles. The receiving device is designed such that it can be removably attached with an opening over and around a region of the component to be coated. A method for the galvanic production of a protective layer featuring hard material particles on a component of a turbomachine using a pouch-, bag- or sack-like receiving device filled with hard material particles, is also disclosed. | 08-04-2011 |
| 20110182746 | BLADE FOR A TURBO DEVICE WITH A VORTEX-GENERATOR - A blade construction for a turbo device, preferably a blade array of a low-pressure turbine, is disclosed. On the inlet-side profile surface of the blade a vortex generator is arranged downstream from the speed maximum. The vortex generator is formed by a surface undulation with at least one wave, the wave tail of which runs in the form of a wave trough and/or a wave peak in the blade vertical direction. | 07-28-2011 |
| 20110176922 | METHOD FOR THE PRODUCTION OF A ROTOR AND ROTOR - A method for producing a rotor, particularly a turbine disk or a turbine ring for a turbine stage of a turbomachine, wherein at least the following steps are carried out: producing a blade ring ( | 07-21-2011 |
| 20110166798 | DEVICE AND METHOD FOR SERVICE-LIFE MONITORING - In the case of a device and a method for monitoring the service life of an engine or of a turbine having a compressor blisk and/or a turbine blisk, momentary stresses of blisk substructures, such as the blade ( | 07-07-2011 |
| 20110164967 | AXIAL FLOW MACHINE HAVING AN ASYMMETRICAL COMPRESSOR INLET GUIDE BAFFLE - An axial flow machine having an asymmetrical air inlet and, downstream therefrom, a compressor having an inlet guide baffle composed of guide vanes is characterized in that at least some of the guide vanes of the inlet guide baffle have a vane profile and/or an angle of attack that deviate(s) from the remaining guide vanes. The inlet flow angle of the first compressor stage is hereby evened out circumferentially symmetrically. This is accomplished in that the different inlet angles resulting at various circumferential positions of the inlet guide baffle due to the asymmetry of the air inlet, are influenced by selective profiling and/or by selectively modifying the angle of incidence of individual guide vanes in such a way that a circumferentially symmetrical outflow angle from the inlet vane ring results. In this way, the circumferential distortions caused by the asymmetrical air inlet are minimized and, thus, circumferentially symmetrical inlet conditions are passed onto the first compressor stage, which results in an improved stability and an enhanced efficiency of the compressor. | 07-07-2011 |
| 20110143039 | PROCESS AND DEVICE FOR COLD SPRAYING - The invention relates to a process for cold spraying, wherein particles of at least one coating material, together with a carrier gas, are directed onto a surface of a workpiece to be coated by means of a spray gun. According to the invention, the particles of at least one coating material are preheated. | 06-16-2011 |
| 20110142652 | ROTATING BLADE SYSTEM FOR A ROW OF ROTATING BLADES OF A TURBOMACHINE - The invention concerns a moving blade system for a moving blade sequence of a continuous-flow machine, in particular a thermal gas turbine with at least two moving blade segments, of which each moving blade segment encompasses at least two moving blades that are disposed, in reference to a rotation axis of the moving blade sequence, at least primarily radially between a radially interior and a radially exterior shroud band and are coupled to the shroud bands, wherein at least the radially exterior shroud bands of the two moving blade segments encompass contact surfaces that correspond to one another, wherein radial equilibrium axes of neighboring moving blades of the at least two moving blade segments are disposed in a tilted manner by respectively axially an angle (60 | 06-16-2011 |
| 20110142386 | BEARING RING AND METHOD FOR COOLING A BEARING RING - The present invention relates to a bearing race, which exhibits an inside facing a rotational bearing-race axis and an outside facing away from the rotational bearing-race axis, in which at least one cooling-medium channel is disposed at the outside of the bearing race, which exhibits a hydraulic diameter of at least 1 millimeter and a length of at least two spiral turns. | 06-16-2011 |
| 20110138925 | MATERIAL SAMPLE FOR TESTING BIAXIAL STRESS CONDITIONS - Described is a material sample for testing material properties under biaxial load as well as a method therefor. The material sample has a circular disk shape and, for rotation about the center line thereof, is provided with an integrally formed hub. The edge of the material sample and the hub are thicker than the ring section of the material sample located in between. In one embodiment, the ring section is designed with an annular concave fillet concentric to the hub and the concave fillet may extend from the edge to the hub and have a continuous curvature over its width. In the method, it is rotated about its center line at least at 100,000 rpm, preferably at 150,000 rpm±10,000 rpm. | 06-16-2011 |
| 20110137450 | METHOD AND DEVICE FOR COMPENSATING FOR POSITIONAL AND SHAPE DEVIATIONS - A method for compensating positional and/or shape deviations in NC-controlled cutting production machines The method including the steps of securing a new workpiece, processing the workpiece using nominal data of the NC program, acquiring set deviation, optimizing the NC program using the acquired data and repeating the above steps until at least one of required positional and shape tolerances are achieved. | 06-09-2011 |
| 20110133102 | METHOD AND ARRANGEMENT FOR DETECTING A SURFACE OF AN OBJECT - The invention relates to a method for optically detecting surfaces wherein strip patterns are projected onto the surface, images are captured, and the three-dimensional contour thereof is determined from the reproduction of the strip pattern on the surface of the object. The aim of the invention is to prevent reflections that interfere with the images and as a result, the surface of the object is covered with a layer of a fluorescent material, is then radiated with ultraviolet radiation, and the radiation emitted by the fluorescent material in the visible light is detected. | 06-09-2011 |
| 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 |
| 20110129347 | PROCESS FOR PRODUCING A JOIN TO SINGLE-CRYSTAL OR DIRECTIONALLY SOLIDIFIED MATERIAL - A process for producing a join between a first component and a second component is disclosed. The second component contains a single-crystal or directionally solidified material. A polycrystalline layer is produced on a joining surface of the second component for joining the second component to the first component. The joining surface of the second component is joined to the first component by friction welding. | 06-02-2011 |
| 20110126943 | METHOD FOR JOINING AND JOINED CONNECTION OF TWO COMPONENTS MADE OF A METAL MATERIAL - The invention relates to a method for joining two components ( | 06-02-2011 |
| 20110103956 | SHROUD FOR ROTATING BLADES OF A TURBO MACHINE, AND TURBO MACHINE - The invention relates to a shroud for rotating blades of a turbo machine, in particular a gas turbine. Said shroud ( | 05-05-2011 |
| 20110103931 | GAS TURBINE COMPRESSOR - A gas turbine compressor is disclosed. The compressor includes a compressor housing, guide vanes, rotor blades, and valve-controlled blow-in openings for stabilizing the compressor flow by air that is blown in. The air flow is detected by pressure sensors and the valves are controlled as a function thereof. | 05-05-2011 |
| 20110085900 | HOUSING FOR A COMPRESSOR OF A GAS TURBINE, COMPRESSOR, AND METHOD FOR PRODUCING A HOUSING SEGMENT OF A COMPRESSOR HOUSING - The invention at hand relates to a housing for a compressor of a gas turbine, in particular of an aircraft gas turbine, with an external housing with at least one air supply opening and an interior housing formed by at least two housing segments, with the housing segments having at least one injection nozzle to inject air suctioned in via the air supply openings into a flow channel in the area of blade tips of blades of a rotor of the compressor. In this case, the housing segment has at least one air flow channel, with the air flow channel being designed in such a way that a direct air supply to the at least one injection nozzle occurs via at least one air supply element arranged in the air supply opening of the exterior housing. The invention relates moreover to a compressor of a gas turbine as well as to a method for the manufacture of a housing segment of a compressor housing. | 04-14-2011 |
| 20110070369 | COVERING DEVICE AND METHOD FOR COATING COMPONENTS - A covering device for the coating of components via cold kinetic compaction or kinetic cold gas spraying, which can be used to cover a region which is not to be coated of a surface of the component which is to be coated. The covering device is profiled such that it encloses an acute angle with that region of the surface which is not to be coated. The particles of a coating material can be deflected from the component such that the particles do not adhere to the covering device. | 03-24-2011 |
| 20110058952 | HIGH-TEMPERATURE ANTI-CORROSIVE LAYER AND METHOD FOR THE PRODUCTION THEREOF - A method for producing a high-temperature protective layer containing metal on a metallic high-temperature material is disclosed. The metal is deposited on the high-temperature material via the gaseous phase to form the high-temperature protective layer. The high-temperature material is held at a diffusion temperature for a specific length of time so that at least a portion of the deposited metal is diffused into the high temperature material to form a diffusion zone and where the high-temperature material is not in contact with solids or liquids in the region of the surface to be coated, but merely has a solid/gas interface. Also disclosed is a component made of a high-temperature material with a hot-gas anti-corrosive layer containing chromium. There is a coating layer containing chromium applied to the surface of the high-temperature material, a diffusion layer in the high-temperature material, and a build-up zone between the coating layer and the diffusion layer. | 03-10-2011 |
| 20110058951 | TURBINE BLADE OF A GAS TURBINE AND METHOD FOR COATING A TURBINE BLADE OF A GAS TURBINE - A turbine blade of a gas turbine is disclosed. The turbine blade includes a blade pan, a blade root, and a platform positioned between the blade pan and the blade root. The turbine blade is provided with an anti-corrosion coating at least in regions, in particular on a lower side of the platform and/or in the transition region between the lower side of the platform and the blade root. The anti-corrosion coating is a diffusion coating having a chromium content in the surface region of more than 30% by weight. | 03-10-2011 |
| 20110052412 | HIGH-PRESSURE TURBINE ROTOR, AND METHOD FOR THE PRODUCTION THEREOF - A method for producing a high-pressure turbine rotor, as well as a turbine rotor, is disclosed. The turbine rotor is designed as a blisk (i.e., bladed disk) and forms a radially inward disk and several vanes or blades that project from the disk. The turbine rotor has an internal duct system for air cooling and at least one section of the turbine rotor is manufactured in a generative production process. | 03-03-2011 |
| 20110045264 | EROSION PROTECTION COATING - The invention relates to an erosion protection coating ( | 02-24-2011 |
| 20110033290 | STRUT FOR AN INTERMEDIATE TURBINE HOUSING, INTERMEDIATE TURBINE HOUSING, AND METHOD FOR PRODUCING AN INTERMEDIATE TURBINE HOUSING - The present invention relates to a strut for a turbine center frame of a jet engine, in particular a gas turbine, with a first end for disposition on an internal structure of the turbine center frame and a second end opposite the first end for attaching the strut on a housing or an internal boundary wall of the turbine center frame, and on the second end at least one flange-like element with at least one first aperture is removably arranged with at least one first aperture for accommodating or passing through an attachment means. The invention further relates to a turbine center frame for a jet engine, in particular a gas turbine as well as a method for producing a turbine center frame of a jet engine, in particular a gas turbine. | 02-10-2011 |
| 20110020560 | Method for Manufacturing a Run-In Coating - A method for the production of a run-in coating is provided, whereby a metallic run-in coating material is provided on a component on the stator side of a turbomachine, especially a gas turbine. According to an embodiment of the invention, the provided run-in coating undergoes a heat treatment for purposes of improving its run-in characteristics. | 01-27-2011 |
| 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 |
| 20110018204 | BRUSH SEAL AND METHOD FOR MOUNTING A BRUSH SEAL - A brush seal and a method for mounting a brush seal is disclosed. The brush seal includes a sealing element provided with a plurality of filaments or wires that are joined at a filament or wire end to form a filament or wire bundle and a clamp-like sealing housing for receiving and fixing the filament or wire end between a first and a second limb and for fixing the brush seal in a mounting recess of a housing. A free end of the filament or wire bundle of the sealing element is clamped between a partial area of an inner contour of the second limb that is adjacent to a region of an outlet opening of the mounting recess of the housing and an area of the outlet opening that is opposite from the partial area. | 01-27-2011 |
| 20110014055 | GAS DYNAMIC COLD SPRAYING OF OXIDE-CONTAINING PROTECTIVE LAYERS - The present invention relates to a method for producing a coating on a gas turbine component, in which particles at least of parts of a material to be applied as coating are accelerated by means of kinetic gas dynamic cold spraying in a spray jet onto the surface ( | 01-20-2011 |
| 20110008195 | CENTRIFUGAL PUMP HAVING INCREASED OPERATIONAL SAFETY - An electric centrifugal pump for conveying a fluid, in particular for conveying fuel to an aircraft engine, is disclosed. The pump includes a housing in which a rotor shaft is rotationally mounted and an impeller for conveying the fuel which is arranged on the rotor shaft. A motor arrangement is provided for driving the rotor shaft in a rotary manner around a rotor axis. The impeller includes at least one rotor, and at least one stator is arranged in the housing in a plane-parallel manner adjacent to the rotor such that the rotor and the stator form the motor arrangement. | 01-13-2011 |
| 20110007304 | METHOD AND DEVICE FOR AUTOMATIC LASER FOCUSING - The invention relates to a process and an apparatus for automatic laser focusing. The core concept of the process is the automatable and especially preferably the automated photographing of the focal spot generated during a focus series by camera and a determination of the particular focal spot diameter as well as an evaluation of this data by an interpolated or approximating function that allows a conclusion about the focal spot with the smallest focal spot diameter and thus with the associated optimal focal distance. A series of disadvantages present in the state of the art can be avoided by using the process in accordance with the invention, in particular the great expenditure of time in the determining of the optimal focal distance and the uncertainty in the selection of the optimal focal spot associated with an operator are eliminated in the framework of the photographing of a focus series. | 01-13-2011 |
| 20110006791 | PROBE FOR A CAPACITIVE SENSOR DEVICE AND GAP-MEASURING SYSTEM - A probe for a capacitive sensor device, and a gap measuring system using the probe, is disclosed. The probe has a probe head including a measuring element with at least one measuring and front face, a first electrically non-conductive isolator element, and a first partial element of a first shield. The measuring and front face, the first isolator element, and the first partial element of the first shield are adhesively connected to one another and configured as a multilayer, where the first isolator element is disposed between the measuring element with its measuring and front face and the first partial element. | 01-13-2011 |
| 20110005549 | METHOD FOR THE THERMOCHEMICAL CLEANING AND/OR STRIPPING OF TURBINE COMPONENTS - The invention relates to a process for the thermochemical cleaning and/or stripping of turbine components, in particular engine components, with the steps: Production of a first gaseous mixture containing HF and H | 01-13-2011 |
| 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 |
| 20110000084 | Method for repairing a sealing segment of a gas turbine - A method for repairing a sealing segment of a gas turbine is provided. The sealing segment includes a radially outer holding portion for a radially inner abradable portion. The method includes the steps of providing a sealing segment to be repaired; removing a damaged, radially inner abradable portion of the sealing segment along a circumferentially extending parting plane, such that the abradable portion is completely removed from the holding portion; making a replacement part for the separated abradable portion of the sealing segment; and joining the replacement part to the holding portion of the sealing segment. | 01-06-2011 |
| 20100329852 | CIRCULATION STRUCTURE FOR A TURBO COMPRESSOR - A circulation structure for a turbo compressor, in particular for a compressor of a gas turbine, is disclosed. The circulation structure includes at least one annular chamber that can be traversed in a circumferential direction, is concentric with a shaft of the turbo compressor in the region of the free blade ends of a blade ring, and radially borders a main flow channel. Several chambers that can be traversed in an axial direction are situated upstream of the or each annular chamber, when viewed from the main flow direction of the main flow channel. | 12-30-2010 |
| 20100327536 | BRUSH SEAL AND METHOD FOR MOUNTING A BRUSH SEAL - A brush seal and a method for mounting a brush seal is disclosed. The brush seal includes a sealing element provided with a plurality of filaments or wires that are joined at a filament or wire end to form a filament or wire bundle. The filament or wire end is arranged in a mounting recess of a housing. A free end of the filament or wire bundle protrudes from the housing and is opposite from the filament or wire end. At least one projection is formed on an inner contour of the mounting recess in such a manner that the filament or wire bundle is clamped by the projection at a predefined distance from the filament or wire end. | 12-30-2010 |
| 20100322780 | SOLDER COATING, METHOD FOR COATING A COMPONENT, COMPONENT, AND ADHESIVE TAPE HAVING A SOLDER COATING - A solder coating ( | 12-23-2010 |
| 20100322758 | COMPRESSOR OF A GAS TURBINE - The invention relates to a compressor, particularly a high pressure compressor, of a gas turbine, particularly of a gas turbine aircraft engine, having at least one rotating blade ring on the rotor side, and having at least one guide blade ring on the stator side, wherein the, or each, guide blade ring is formed of a plurality of guide blade segments, and wherein each guide blade segment is formed of a plurality of individual blades. According to the invention, adjacent individual blades ( | 12-23-2010 |
| 20100320696 | SEAL ARRANGEMENT - The invention relates to a sealing arrangement for a non-hermetic seal of a gap ( | 12-23-2010 |
| 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 |
| 20100304064 | METHOD FOR PRODUCING A CAST PART, CASTING MOULD AND CAST PART PRODUCED THEREWITH - A method for producing a cast part from metal, a metal alloy or from plastic, with at least one complex internal structure, in particular with at least one hollow space, by at least one casting mold, is disclosed. The method includes the following steps: a) providing at least one core element, wherein the core element peripherally reproduces the complex internal structure and has a metallic layer on its outer periphery; b) forming a first casting mold or negative mold for producing a positive mold reproducing the cast part, with one or more cast-in core elements; c) casting an enclosure around the positive mold to form a second casting mold or negative mold of the cast part and removing the positive mold; d) filling the casting mold or negative mold with casting material and cooling the casting material down; and e) removing the enclosure and removal of the cast part. | 12-02-2010 |
| 20100288399 | Device and method for remelting metallic surfaces - A method for remelting metallic surfaces of components using the effect of a stable high pressure plasma jet, includes melting the surface in localized areas, the surface having a structure refinement after solidification. The plasma jet action is generated by the microwave impact on a carrier gas, the pressure of the high pressure plasma jet being above the atmospheric pressure. In addition, a plasma torch for generating a directed high pressure plasma jet includes a gas supply, a device for generating a plasma, and an outlet nozzle for a plasma jet. The device for generating the plasma includes a magnetron and a resonator in which the supplied pressurized carrier gas is transferred into a plasma under the effect of microwaves, causing the plasma to exit through the outlet nozzle at a pressure above 0.1 MPa. | 11-18-2010 |
| 20100283211 | HONEYCOMB STRUCTURE - Disclosed is a honeycomb structure for non-hermetic rotor-stator and rotor-rotor seals in turbo machines. Said honeycomb structure comprises a plurality of at least predominantly radially oriented honeycomb cells which are separated by cell walls, are open on one side, cooperate with at least one sharp sealing edge that rotates relative to the honeycomb structure, and can yield relative to the sharp sealing edge by being deformed and/or material being removed therefrom when being touched. The walls of the honeycomb cells have holes according to a defined perforation pattern. | 11-11-2010 |
| 20100272572 | METHOD FOR PRODUCING AN INTEGRALLY BLADED ROTOR, AND ROTOR - A method for producing an integrally bladed rotor, as well as a rotor, is disclosed. A rotor support is composed of several disk-type rotor base bodies that are welded onto the blade ring. | 10-28-2010 |
| 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 |
| 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 |
| 20100253168 | ELECTRIC DRIVE, PARTICULARLY FOR A FUEL METERING UNIT FOR AN AIRPLANE ENGINE - An electric drive, particularly for a fuel metering unit for delivering and metering fuel from a fuel tank into a combustion chamber of an airplane engine, is disclosed. The electric drive drives at least one work module and is composed of at least two engine modules that are supplied separately with electricity and disposed on a common rotor shaft to form a redundant engine arrangement. | 10-07-2010 |
| 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 |
| 20100232952 | TURBO COMPRESSOR IN AN AXIAL TYPE OF CONSTRUCTION - A turbo compressor in an axial type of construction is disclosed. The turbo compressor having a bladed stator and a bladed rotor, and having a longitudinally split compressor casing and a guide blade ring with adjustable guide blades. The guide blades are pivotably mounted about radial axes radially within their aerofoil on an inner ring belonging to the stator. The inner ring is split, i.e., segmented, at at least two points of its circumference. Furthermore, the inner ring has for each guide blade at least one bearing bush which can be inserted radially into an opening from inside. | 09-16-2010 |
| 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 |
| 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 |
| 20100202872 | MULTILAYER SHIELDING RING FOR A FLIGHT DRIVING MECHANISM - A shielding ( | 08-12-2010 |
| 20100196137 | CLOSED-LOOP CONTROL FOR A GAS TURBINE WITH ACTIVELY STABILIZED COMPRESSOR - A regulating system for a gas turbine, in particular an aircraft engine, has devices for blade-tip injection for increasing the compressor stability, these devices being activated as needed. The regulating system has devices for active clearance control, preferably in the high-pressure compressor, with which the radial clearance in the high-pressure compressor is kept in an optimum operating range, and the regulating system has a shared engine regulator for both devices. The technical problems of the prior art are avoided through the present invention, and an improved regulating system for a gas turbine, in particular an aircraft engine, is made available for active stabilization of the compressor. | 08-05-2010 |
| 20100193572 | DAMPING DEVICE, WELDING SYSTEM FOR ROTARY FRICTION WELDING AND ROTARY FRICTION WELDING METHOD - The invention relates to a damping device ( | 08-05-2010 |
| 20100186472 | METHOD AND DEVICE FOR SURFACE PEENING OF A COMPONENT IN THE REGION OF A PASSAGE OPENING - A method and device for surface peening, particularly ultrasonic shot peening, of a component in the region of a passage opening is disclosed. A vibration device impinging the blasting material is disposed on one side and a counter-element is disposed on an opposite side relative to a component region having the passage opening. The counter-element is disposed at a distance relative to the corresponding side of the component region. | 07-29-2010 |
| 20100181298 | INDUCTION COIL, METHOD AND DEVICE FOR THE INDUCTIVE HEATING OF METAL COMPONENTS - An induction coil for use in a method for the inductive heating of metallic components, particularly components of a gas turbine, is disclosed. The coil includes at least two windings and the distance between the individual windings is configured such that the component or components to be heated can be inserted between two windings that are spaced apart from each other. A method and a device for the inductive heating of metallic components, particularly components of a gas turbine, and to a component produced by the method is also disclosed. | 07-22-2010 |
| 20100173094 | METHOD FOR MANUFACTURING AN ABRASIVE COATING ON A GAS TURBINE COMPANENT - A method for manufacturing an abrasive coating on a gas turbine component, especially on a gas turbine rotor blade tip, comprising at least the following steps: a) providing a gas turbine component, especially a gas turbine rotor blade; b) providing a high temperature melting alloy powder; c) providing abrasive particles; d) providing a low temperature melting alloy powder; e) blending at least said high temperature melting alloy powder and said abrasive particles to provide a mixture; f) applying said low temperature melting alloy powder and said mixture to an area of said gas turbine component, especially to a tip of said turbine rotor blade; g) locally heating said area of said gas turbine component to a temperature above the melting point of said low temperature melting alloy powder but below the melting point of said high temperature melting alloy powder is provided. | 07-08-2010 |
| 20100173092 | ADHESIVE MASKING TAPES AND METHOD FOR COATING AND/OR REPAIRING COMPONENTS - A masking tape, particularly for use with thermal spraying methods, comprises a tape- and/or strip-like base layer, the base layer including silicone and a glass fiber and/or glass fabric insert, an adhesive layer disposed on the base layer, and at least two scale-like or lamellar elements made of metal or a metal alloy that are attached to the base layer on the surface located opposite the adhesive layer. Another masking tape, particularly for use with thermal spraying methods, comprises a tape- and/or strip-like base and adhesive layer, the base and adhesive layer comprising a glass fiber and/or glass fabric tape and a silicone adhesive, and at least two scale-like or lamellar elements made of metal or a metal alloy that are attached to a surface of the base and adhesive layer. Further, a method of coating and/or repairing components, in particular, turbine or power unit components, uses the aforesaid masking tape and a thermal spraying method. | 07-08-2010 |
| 20100171270 | Sealing Device for a Cooling Agent Supply on a Rotating Spindle and Machine Tool Comprising Such a Sealing Device - A sealing device for a coolant supply on a rotating spindle is characterized in that a first brush seal ( | 07-08-2010 |
| 20100169048 | MAINTENANCE PLANNING METHOD - A maintenance planning method for turbomachines, especially for gas turbine aircraft engines, is disclosed. In an embodiment, the method includes: a) data obtained from the previous maintenance of turbomachines is stored in a database in a structured manner, where the data especially correlates maintenance work carried out with operating loads of a serviced turbomachine; b) in order to pre-plan the maintenance of a turbomachine undergoing further maintenance, the maintenance work to be carried out is planned in terms of type and sequence on the basis of the database; and c) the turbomachine undergoing further maintenance is inspected for the final planning of the maintenance, and the type and/or sequence of the maintenance work to be carried out, which was specified during the pre-planning of the maintenance, is adapted and/or supplemented on the basis of the inspection. | 07-01-2010 |
| 20100166944 | METHOD FOR DETERMINING THE POLYESTER FRACTION OF A MULTI-COMPONENT POWDER DURING A THERMAL SPRAYING PROCESS, METHOD FOR COATING OR TOUCHING UP AN OBJECT BY MEANS OF A THERMAL SPRAYING PROCESS AND THERMAL SPRAYING DEVICE - A method for determining the polyester fraction in a multi-component powder during a thermal spraying process is disclosed. The multi-component powder is heated and fed to an object with the aid of a carrier, forming a coating on the object. At least one measured value for the intensity of the light emitted by the combination of the carrier and multi-component powder material on the way to the object is detected at least in the range of a characteristic wavelength of polyester. A characteristic value is derived from the combination of the measured values, and the fraction of the polyester to be determined is calculated on the basis of a previously determined relationship between the characteristic value and the polyester fraction. | 07-01-2010 |
| 20100164501 | ALTERNATING CURRENT SWITCH DEVICE AND METHOD FOR THE MONITORING OR DIAGNOSIS OF THE OPERABILITY OF AN ALTERNATING CURRENT SWITCH DEVICE - The invention relates to an alternating current switch device for the optional closure and opening of at least one electrically conducting connection, wherein this alternating current switch device has at least two parallel connected branches ( | 07-01-2010 |
| 20100158691 | Component and Method for Joining Metal Elements - A component, in particular a component of a gas turbine, is described composed of at least two metallic structural elements, the first structural element having a first joining surface, and the second structural element having a second joining surface, and the structural elements being joined via their joining surfaces by an inductive high-frequency pressure welding. One of the joining surfaces is shaped to widen peripherally in comparison to the other joining surface, and an upsetting deformation produced in a join region in response to the joining of the structural elements rests virtually entirely within and, in particular, on a peripheral collar formed by the peripheral widening of the one joining surface. A method is described for joining metallic structural elements, in particular structural elements of a gas turbine, an inductive high-frequency pressure welding being used to join corresponding joining surfaces of the structural elements. | 06-24-2010 |
| 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 |
| 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 |
| 20100143100 | Jet Engine With Active-Magnetic Bearing - Jet engine ( | 06-10-2010 |
| 20100135779 | SEMI-FINISHED PRODUCT FOR PRODUCING A REPAIRED BLADE FOR A GAS TURBINE AND REPAIR METHOD FOR REPAIRING A BLADE FOR A GAS TURBINE - The invention relates to a semi-finished product for producing a repaired blade for a gas turbine. Said semi-finished product comprises a first part ( | 06-03-2010 |
| 20100132177 | METHOD AND BLASTING AGENT FOR SURFACE PEENING - The present invention relates to a method for the surface peening, in particular for the ultrasonic shot peening, of component ( | 06-03-2010 |
| 20100125990 | METHOD AND DEVICE FOR THE SURFACE PEENING OF A PARTIAL ELEMENT OF A COMPONENT OF A GAS TURBINE - A method and device for the surface peening, especially ultrasonic shot-peening, of at least one partial element of a component of a gas turbine, is disclosed. The partial element, e.g., a sealing fin, and at least one surface of a vibration device impinging the blasting material are positioned relative to each other at an angle between 70° and 90° based on the direction of extension of the sealing fin. | 05-27-2010 |
| 20100119706 | METHOD FOR THE PRODUCTION OF AN ABRADABLE COATING - A method for producing an abradable coating for a component of a turbo-machine is disclosed. The method includes a) a powdery material is pretreated; b) a processable preliminary product is produced which is to be applied to a component that is to be coated; c) the preliminary product is applied to the component that is to be coated; d) a synthetic binder contained in the preliminary product is burned off; e) the component is sintered; and f) the component is post-processed. The method for producing an abradable coating for a turbo-machine eliminates the drawbacks of the solutions known from the prior art. In particular, the method is inexpensive, can easily be combined with other production process steps, for example, thermal treatments that have to be carried out anyway, and is also suitable as a method for repairs. | 05-13-2010 |
| 20100119376 | INLET CONE FOR JET ENGINE - Inlet cone ( | 05-13-2010 |
| 20100108745 | METHOD FOR THE SOLDERING REPAIR OF A COMPONENT IN A VACUUM AND AN ADJUSTED PARTIAL OXYGEN PRESSURE - A method for the repair of a component by a solder is disclosed. The method is performed under specifically selected vacuum conditions in order to prevent oxidation and vaporization. | 05-06-2010 |
| 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 |
| 20100104418 | GAS TURBINE - A gas turbine having a rotor which includes a turbine rotor, a shaft and a compressor rotor, the turbine rotor having at least one rotor disk and a rotor cone leading from the or a rotor disk to the shaft, the downstream end of the shaft being rotatably supported in a bearing having a bearing chamber, the interior space of the shaft being designed as a flow channel for bearing-chamber sealing air, and the space surrounding the rotor cone upstream of the same being designed as a flow space for cooling air is disclosed. In the region of the rotor connection, the shaft exhibits an expanded portion, at whose upstream end, openings are provided to allow cooling air to enter, and, at whose downstream end, openings are provided to allow cooling air to exit into the space between the bearing chamber and the rotor cone, a wall separating the streams of the cooling air and of the sealing air in the shaft interior from one another. | 04-29-2010 |
| 20100101698 | METHOD FOR PRODUCING A STRUCTURAL ELEMENT - A method for producing a structural element having a low density and high temperature resistance, where a plurality of hollow spheres made of a high temperature resistant material are connected together in a material fit, is disclosed. Adhesive bridges made of a high temperature resistant, inorganic adhesive are formed between the hollow spheres. The structural mass made of hollow spheres and adhesive is dried and cured at temperatures that are higher than the ambient temperature and are no higher than the subsequent utilization temperature of the structural element. | 04-29-2010 |
| 20100098551 | METHOD AND DEVICE FOR COATING COMPONENTS OF A GAS TURBINE - The present invention relates to a method for coating components of a gas turbine, in particular for producing a wear-resistant, temperature, oxidation and/or corrosion-resistant protective coating on the component, wherein the protective coating is made of at least one solder film or slurry coating, which is connected to the corresponding region of the component by means of an inductive high-temperature soldering method. The bonded connection between the component and the solder film or slurry coating disposed on the component is achieved by locally heating the component in the region of the solder film or slurry coating to be applied, and simultaneously heating the solder film or slurry coating by means of thermal energy generated and emitted by at least one induction amplifier, wherein the induction amplifier is disposed between the inductor and the component in the region of the solder film or slurry coating. The invention further relates to a device for coating components of a gas turbine, in particular for producing a wear-resistant, temperature, oxidation and/or corrosion-resistant protective coating on the component, using at least one inductor for carrying out an inductive high-temperature soldering method for heating and bonding at least one component to at least one solder film or slurry coating forming the protective coating, wherein according to the invention at least one induction amplifier is disposed in the region of the solder film or slurry coating between the inductor and the component having the solder film or slurry coating. | 04-22-2010 |
| 20100089166 | APPARATUS AND METHOD FOR NON-CONTACTING BLADE OSCILLATION MEASUREMENT - An apparatus and method for non-contact blade vibration measurement is disclosed. The apparatus and method includes sensors which are arranged around the circumference of a rotor which is formed with rotor blades, a signal detection unit, and an evaluation unit. Devices are provided to determine the rotor position and/or the housing deformation. This avoids the technical problems of the prior art, and provides an improved apparatus and an improved method for non-contact blade vibration measurement. In particular, the attainment according to the invention eliminates the effect of rotor radial movements and housing deformations, i.e., oval deformations, on the measurement data, thereby ensuring high amplitude resolution for the vibration analysis under all conditions. | 04-15-2010 |
| 20100077849 | DEVICE AND METHOD FOR MEASURING LAYER THICKNESSES - The present invention concerns a device for measuring of layer thicknesses, especially for measuring of layer thicknesses of a structural part ( | 04-01-2010 |
| 20100074740 | VANE RING, AND METHOD FOR THE PRODUCTION THEREOF - The invention relates to a vane ring of a turbo engine, particularly a gas turbine, comprising a vane support ring and several guide vanes that are mounted on the vane support ring. According to the invention, the vane support ring and the guide vanes are made of different materials, the materials of which the guide vanes are made being of a higher quality than the material of which the vane support ring is made. | 03-25-2010 |
| 20100074704 | METHOD OF MANUFACTURING AND REFINISHING INTEGRALLY BLADED ROTORS - A method of forming integrally bladed rotors for gas turbines is described. The method includes drilling in a workpiece material recesses defining flow passages and rotor blades, performing a coarse milling step to refine surfaces of the rotor blades, and filling the recesses between the rotor blades with a damping material, thus encasing the rotor blades in the damping material. The method further includes performing a finishing milling step to remove the damping material and the workpiece material on surfaces of the rotor blades, while maximizing a damping effect of the damping material on the rotor blades. To maximize the damping effect, the finishing milling tool moves along a path that preferentially mills one surface of a blade while the other surface is in contact with the damping material. | 03-25-2010 |
| 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 |
| 20100062172 | METHOD FOR THE PRODUCTION OF AN ABRADABLE SPRAY COATING - A method for producing a spray coating, in particular an abradable spray coating for components of a turbine engine by a thermal spraying process, is disclosed. An online process monitoring system, especially a PFI unit and/or a spectrometer unit, is provided for monitoring and regulating the thermal spraying process, where at least one process parameter is calculated according to the formula p | 03-11-2010 |
| 20100054921 | TURBO ENGINE - A turbine engine is disclosed. A blade ring is surrounded by a housing wall, the housing wall being configured as an outer ring, and delimits therewith a gap, the gap being adjustable by deformation of the outer ring. The outer ring is concentrically surrounded by an adjusting element, opposite faces of the outer ring and the adjusting element having the contour of a truncated cone, and rolling bodies being positioned between the outer ring and the adjusting element, the rolling bodies being put at an oblique angle in relation to the axial direction in the radial direction and in the peripheral direction, making it possible for the adjusting element to be rotated in relation to the outer ring while simultaneously adjusting the gap. | 03-04-2010 |
| 20100037669 | DEVICE AND METHOD FOR THE SURFACE PEENING OF A COMPONENT OF A GAS TURBINE - A device for surface-peening, especially for the ultrasound shot-peening of a component of a gas turbine, having at least one vibration means that comprises a surface that propels the peening material, and having a holding means with which a surface area of the component and the surface of the vibration means can be arranged with respect to each other is disclosed. In this context, the angular position of the surface of the at least one vibration means can be adjusted relative to the surface area of the component of the gas turbine. Moreover, a method is provided in which the angular position of the surface of the at least one vibration means can be adjusted relative to the surface area of the component. | 02-18-2010 |
| 20100031631 | GAS TURBINE COMPRISING A GUIDE RING AND A MIXER - A gas turbine is disclosed. The gas turbine includes a rotor which is driven by a turbine, a stator, struts that are fixed to the stator downstream from the turbine and that configure a guide ring for deflecting the rotational flow of hot gas, and a mixer arranged on the downstream end of the hot gas channel. The guide ring and the mixer are structurally and fluidically combined, the struts of the guide ring being connected to the wall structure of the mixer in the region of their radially outer ends. | 02-11-2010 |
| 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 |
| 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 |
| 20100012230 | APPARATUS AND METHOD FOR THE HEAT TREATMENT OF INTEGRAL ROTORS OF GAS TURBINES - An apparatus for the heat treatment of integral rotors of gas turbines is disclosed. The apparatus includes a closable working space which can be evacuated or filled with inert gas, a heat source, a distance-measuring instrument, and a pyrometer. A method for diminishing and/or for eliminating internal stresses which are introduced into a component through welding is also disclosed. | 01-21-2010 |
| 20100011739 | APPARATUS AND METHOD FOR DRAWING OFF AND RECIRCULATING A COOLING STREAM - A device and method for drawing off and recirculating cooling streams, specifically for drawing off and recirculating a cooling stream of fuel for cooling at least one aircraft engine accessory, is disclosed. The device having a tubular jacket part defining a flow cross-section through which a primary stream, specifically a fuel stream, flows by way of an extraction pipe which is positioned approximately in the center of the flow cross-section, or jacket part, in order to draw off a cooling stream from the primary stream, by way of a hollow strut extending in the radial direction to divert this cooling stream from the device with the aid of the extraction pipe and to supply it to at least one accessory to be cooled, and by way of a return opening to recirculate the cooling stream directed through the accessory for cooling purposes to the primary stream. | 01-21-2010 |
| 20100006187 | METHOD FOR SURFACE STABILIZING METAL COMPONENTS - The invention relates to a method for the strengthening of the surface of a structural component with the aid of laser shock processing in which a coating applied to a metallic surface of the component to be strengthened is decomposed with the aid of a laser beam provided by a processing laser through evaporation or pyrolysis under creation of a plasma in such a way that a shock wave induced by interaction of the plasma with the metallic surface deforms the surface plastically and with the laser shock processing being monitored by means of recording light emission values of the plasma. In accordance with the invention, the light emission values are recorded with the aid of a measuring laser in time-delayed fashion relative to the decomposition of the coating with the aid of the processing laser. | 01-14-2010 |
| 20100003122 | TURBO ENGINE - The invention concerns a turbo engine, especially a gas turbine, with a stator and a rotor, wherein the rotor has rotating blades and the stator has a housing ( | 01-07-2010 |
| 20090324384 | GAS TURBINE HAVING A PERIPHERAL RING SEGMENT INCLUDING A RECIRCULATION CHANNEL - A gas turbine having at least one compressor, at least one combustion chamber, and at least one turbine, the or each compressor and/or the or each turbine having a rotor that includes rotor blades surrounded by a stationary housing, and a run-in coating being assigned to the housing is disclosed. The gas turbine includes at least one channel which is configured to apply a pressure prevailing on the high-pressure side of the blades of a rotor to a low-pressure side of the same in the area of a gap between the radially outer ends of the blades and the housing and thereby prevent a flow through the gap. | 12-31-2009 |
| 20090317228 | APPARATUS AND METHOD FOR CONTROLLING A BLADE TIP CLEARANCE FOR A COMPRESSOR - An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained. | 12-24-2009 |
| 20090304515 | METHOD AND DEVICE FOR JOINING BY WAY OF INDUCTIVE HF PRESSURE WELDING A ROTOR BLADE WITH A ROTOR SUPPORT OF A GAS TURBINE WITH AUTOMATIC SUPPLY OF THE ROTOR BLADE - A method and a device for joining at least one rotor blade or at least one part of a rotor blade with a rotor support of a gas turbine, in particular a rotor blade connection of the rotor support, is disclosed. Corresponding connecting surfaces of the rotor blade, the rotor blade part, the rotor support or the rotor blade connection of the rotor support are joined by inductive high-frequency pressure welding. In this case, at least one rotor blade or rotor blade part is automatically supplied from at least one rotor blade reservoir and/or rotor blade part reservoir and, in addition, the rotor support is automatically positioned in such a way that the connecting surfaces to be joined are positioned precisely with respect to one another for the joining process. | 12-10-2009 |
| 20090304497 | GUIDE BLADE SEGMENT OF A GAS TURBINE AND METHOD FOR ITS PRODUCTION - A guide blade segment of a gas turbine, having at least one guide blade and having an inner cover band assigned to the radially inner end of the or each guide blade, is disclosed. An integral constituent part of the inner cover band of the guide blade segment is a sealing element, which serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor. | 12-10-2009 |
| 20090301152 | COVER ELEMENT FOR A SONOTRODE AND PEENING CHAMBER ARRANGEMENT FOR THE SURFACE PEENING OF COMPONENTS - A cover element for a sonotrode which is to be configured, in particular, for accelerating peening material within a peening chamber for the surface peening of components and is to be operated by a vibration exciter of the sonotrode, at least one wall, in particular a wall portion of a chamber wall of the peening chamber, being provided, which is mounted in a predefined position on the cover element and is to be moved together with the same is disclosed. In addition, a peening chamber arrangement for the surface peening of components, in particular for ultrasonic shot peening, including a peening chamber that is bounded by at least one chamber wall; and at least one sonotrode having a cover element which includes at least one wall portion of the chamber wall that is to be moved together with the same is disclosed. | 12-10-2009 |
| 20090301053 | Gas Turbine and Method of Operating a Gas Turbine - A gas turbine including at least one compressor, one combustion chamber, and at least one turbine including at least one rotor and at least one generator coupled to the at least one rotor is provided. The at least one turbine is coupled to the at least one compressor. Once the gas turbine is shut down, the at least one generator can be used as a motor in order to drive the at least one rotor for a predetermined time period following shutdown of the gas turbine and thereby effect a uniform cooling of the rotor. A method of operating a gas turbine is also provided. | 12-10-2009 |
| 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 |
| 20090290985 | PROCESS FOR CONNECTING METALLIC STRUCTURAL ELEMENTS AND COMPONENTS PRODUCED THEREBY - A process for connecting metallic structural elements, in particular structural elements of a gas turbine, and a component made by the process, is disclosed. The connecting of corresponding connecting surfaces of the structural elements is performed by inductive high-frequency pressure welding and the structural elements consist of different or similar metallic materials with different permeabilities and/or thermal conductivities. During the inductive high-frequency pressure welding, at least one process-specific parameter is controlled in such a way that at least the connecting surfaces are respectively heated essentially simultaneously up to at least near the respective melting point of the metallic materials. | 11-26-2009 |
| 20090277541 | METHOD AND APPARATUS FOR HARDENING A SURFACE OF A COMPONENT - A method and apparatus for surface hardening parts is disclosed. To harden a surface of a part, a relative movement, or advancing motion, is established between the part and at least one sonotrode-like tool which is excited in the ultrasonic frequency range. The tool is aligned during the surface hardening in such a way to the surface of the part to be hardened that a tool axis running in the effective direction of the tool runs at an angle to the surface of the part to be hardened. | 11-12-2009 |
| 20090276139 | Engine regulation system and method for qualifying the components of the engine regulation system - An engine control system is provided having a control unit and a monitoring module. The monitoring module, together with the control unit, forms one structural unit and is designed as a detachable module having an independent electromagnetic shielding. | 11-05-2009 |
| 20090271985 | REPAIR METHOD - The invention relates to a method of repairing moving blades of a gas turbine, with at least the following steps: a) preparation of a moving blade to be repaired; b) removal of at least one damaged section of a damaged blade tip of the moving blade to be repaired, forming a parting surface; c) successive building up of the, or each, removed section or the entire blade tip on the parting surface of the moving blade by means of a rapid manufacturing process, using three-dimensional CAD structural data on the moving blade. | 11-05-2009 |
| 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 |
| 20090263239 | Ring structure with a metal design having a run-in lining - A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt. | 10-22-2009 |
| 20090248356 | METHOD AND MEASURING SYSTEM FOR CHARACTERIZING A DEVIATION OF AN ACTUAL DIMENSION OF A COMPONENT FROM A NOMINAL DIMENSION OF THE COMPONENT - A method and a measuring system for characterizing a deviation of an actual dimension of a component from a nominal dimension of the component, is disclosed. In an embodiment, the method includes a) determining at least one measured value characterizing the actual dimension at a position of the component by a measuring device; b) making a nominal value available with which the nominal dimension is characterized as a function of the position of the measured value; c) determining a spatial distance between the measured value and the nominal value; d) making a limiting criterion available with which a permissible deviation from the nominal value is characterized as a function of the position of the measured value; and e) determining a tolerance utilization value characterizing the deviation for the measured value as a function of the spatial distance and of the limiting criterion. | 10-01-2009 |
| 20090238402 | DEVICE AND METHOD FOR VISUALIZING POSITIONS ON A SURFACE - A device and a method are disclosed for visualizing positions on a surface by means of a marking which is produced by an optically detectable radiation. In order to permit a residue-free marking which can be observed with a camera from partly extremely oblique observation directions, the device has an optical waveguide, which is coupled to a radiation source and whose light output region can be located at a desired position of the surface in order to emit optically detectable radiation at the desired position of the surface through the optical waveguide. As a result, the radiation is emitted at the desired position of the surface in various spatial directions. | 09-24-2009 |
| 20090235763 | Chuck-integrated force-measuring system - A chuck-integrated force-measuring system for determining cutting forces at the cutting tool tip of a rotating tool, for example a drill or milling cutter having at least one measuring sensor, as well as a measured-value processing station. The at least one measuring sensor is designed as a strain sensor which is placeable on a tool holder of a machine tool. A measuring hub assembly is also provided which is insertable as an adapter piece into the chuck of the machine tool and is designed with its own chuck for receiving the tool, the at least one measuring sensor being integrated in the adapter piece. | 09-24-2009 |
| 20090232975 | METHOD FOR REPAIRING TURBINE VANES - A method for repairing turbine vanes for a gas turbine is disclosed. In an embodiment, the method includes the following steps: a) a turbine vane is provided which, at least in sections, has a PtAl coating to be repaired, b) the turbine vane is cleaned at least in the area of the PtAl coating to be repaired, and c) the turbine vane is alitized only in the area of the cleaned PtAl coating. | 09-17-2009 |
| 20090218232 | Method for the Pre-Treatment of Titanium Components for the Subsequent Coating Thereof - A method for the pre-treatment of titanium components for the subsequent coating thereof is provided. The method includes at least the following steps: a) etching of the component in an acidic solution containing fluoride and nitric acid (HNO3); b) activation pickling of the etched component in a solution containing at least sodium nitrate (NaNO3) and tetrafluoroboric acid (HBF4); and c) activation of the activation-pickled component in a bath containing acid or in an acidic bath containing nickel. | 09-03-2009 |
| 20090215361 | Method for near-net-shape machining of curved contours - A method relating to near-net-shape machining of curved contours such as those occurring, for example, in the fabrication of blades for propulsion engines and the like is described. Accordingly, the shape error in curve grinding is minimized by suitable compensation functions, in particular by interpolating and approximating cubic splines. The present method minimizes the number of tests required to set up a grinding machining operation and thus the number of semifinished products required to do so. At the same time, rejects in fabrication of curved workpieces are reduced by increasing the machining quality. The use of complex chucking devices is avoided and cutting performance is maximized. | 08-27-2009 |
| 20090214824 | Apparatus and method for coating a compressor housing - A running-in coating for a compressor housing is disclosed. The running-in coating has at least two layers where a first layer is dimensionally stable and at least one additional layer has run-in capability. | 08-27-2009 |
| 20090214312 | METHOD FOR OPTIMIZED MILLING CLOSE TO THE FINAL CONTOUR - A method for optimized milling of workpieces close to the final contour, in particular chamfers on turbine blades, is disclosed. The method is characterized in that a numeric optimization method is provided for the automatic control of the kinematic sequences of motion, wherein an additional rotation around an axis parallel to the tool axis is optimized in terms of kinematic and/or kinetic and/or workpiece-specific manufacturing criteria. With the method, it is possible to achieve optimum results in the milling of chamfers close to the final contour or in the deburring of workpiece edges. In this case, the method makes it possible in particular to make available a path optimization that is required in order to achieve an optimum processing result, wherein this optimization is preferably automated and can take place within a short time. In addition, the inventive method achieves a high level of series stability in manufacturing. | 08-27-2009 |
| 20090212032 | Optimized machining of a contour using a pulsed tool - A pulsed machining method for the optimized machining of a contour which is characterized in that the instantaneous frequency ratio of φ of the pulse frequency of tool f | 08-27-2009 |
| 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 |
| 20090200361 | Method for joining components using a brazing technique - A method for joining components using a brazing technique, namely relatively thin-walled components, in particular sheet-metal panels, which are not inherently stable and thus are susceptible to deformation, comprising at least the following steps:
| 08-13-2009 |
| 20090194247 | Method for repair of a metallic hollow body - A method for repairing a metallic hollow body including at least one damaged portion to be repaired in a wall enclosing at least one cavity of the hollow body, the wall being a metallic material, is provided. The method includes the steps of filling a settable filling compound into at least one partial area of the at least one cavity; setting the filling compound; removing a predefined partial surface of the wall in an area of the at least one damaged portion; sealing the wall in an area of the removed partial surface by producing a covering element by welding, soldering, or casting-on; and removing the filling compound. | 08-06-2009 |
| 20090186157 | Method for at least selectively removing a first layer from an engine component - A method for selectively removing a first layer from an engine component including the first layer, a base material and a second layer forming a bond connecting the first layer to the base material is provided. The method includes applying a salt melt to at least one section of the engine component including at least one portion of the second layer so the bond formed by the second layer between the base material and the first layer is at least weakened. | 07-23-2009 |
| 20090184153 | Method of Producing a Welded Joint - A method of producing a welded joint between components of a turbomachine is described, in particular for the repair of components, wherein components are welded to one another along common edges in such a way that a pocket-like recess is incorporated in a first component, in particular in a replacement part, with which recess the first component is slipped onto a second component, in particular a component to be repaired, such that the second component bears with an end edge on a base of the pocket-like recess, and that the first component and the second component are then welded to one another. According to the invention, at least one cutout is incorporated in the first component in addition to the pocket-like recess in order to minimize heat transfer and the formation of component deformations during the subsequent welding of the components. | 07-23-2009 |
| 20090153877 | Optical Measurement of Metallic Surfaces - A method for optically measuring a surface is described, in particular, for a surface having a spherical form and a high reflection of radiation. The surface is illuminated by at least one radiation source, as well as by at least one structured light source, in order to produce an illumination structure on the surface to be measured, and to then record the illumination structure using a camera; prior to measuring the surface, a coating being applied thereto in order to reduce the reflected radiation, the electrostatic coating principle being followed when applying the coating to the spherical surface. Thus, a method for optically measuring a surface is described, which provides for a coating to be uniformly deposited on the entire surface of the test object and to have a thickness of less than 0.01 mm. | 06-18-2009 |
| 20090133380 | Gas Turbine Engine - A gas turbine engine is described having at least one compressor, at least one combustion chamber, at least one turbine, and having an exhaust heat exchanger, which is used for returning waste heat of the exhaust emissions to the compressed combustion air prior to entry of the same into a combustion chamber. The exhaust heat exchanger is used as a substrate for catalysts for use in the catalytic aftertreatment of the exhaust emissions, in order to thereby reduce the pollutant emissions, in particular NOx emissions, of the gas turbine engine. | 05-28-2009 |
| 20090127254 | Induction coil, method and device for inductive heating of metallic components - An induction coil for inductive heating of at least one metallic component having at least one lateral face and at least one face to be heated is provided. The induction coil includes a meandering pattern section shaped around the at least one component in such a way that the section extends over at least a partial area of the at least one lateral face of the at least one component to be heated in the area of the at least one face to be heated. A device and method for inductive heating of at least one metallic component are also provided. | 05-21-2009 |
| 20090111639 | Planetary Gear - A planetary gear train is described which includes a sun gear, three or more planet gears, an annulus as well as a planet gear carrier, whereby the input is provided via the sun gear and the output is provided via the annulus or via the planet gear carrier, whereby each planet gear is mounted on both sides in a roller bearing, and whereby the planet gear carrier includes two axially spaced bearing washers as well as at least three webs that connect the bearing washers. Each roller bearing is configured as a single-row or multi-row cylindrical roller bearing, each planet gear has a flexurally elastic axis projecting axially on both sides beyond the gear body of the planet gear, and the connection between each roller bearing and the appertaining axis is configured to be spherically moveable. | 04-30-2009 |
| 20090108051 | Method for joining components - A method for joining components is described, in particular, for joining a rotor blade to a rotor base member when manufacturing and/or repairing an integrally bladed gas turbine rotor. The method includes the following steps: providing two components to be assembled, respectively joined to one another; providing a joining part; mutually aligning the two components to be assembled and the joining part such that the joining part is positioned as an insert between the two components to be assembled; driving the two components being assembled with the joining part being interposed therebetween in that the joining part to execute a linear, reciprocating motion in opposition to the two stationary components to be assembled in order to generate the frictional motion, further comprising exerting an upsetting force via the joining part on the joint zones between the two stationary components and the joining part, namely in a direction that extends essentially perpendicularly to the frictional motion. | 04-30-2009 |
| 20090107968 | Method For Heating Components - The invention relates to a method for heating a machining area of a structural component, particularly a gas turbine component, prior to and/or during and/or after a machining or processing of the component on the machining area. According to the invention, the machining area ( | 04-30-2009 |
| 20090101634 | Joining Method - A joining method, in particular for gas turbine components, is provided wherein applying inductive heating, using at least one inductor, to a joining zone of a first component section and a second component section; following and/or during the step of applying inductive heating, exerting a press force on the first component second and the second component section to weld the first and second component section together, additionally heating by a capacitor discharge of the joining zone of the first and second component sections. | 04-23-2009 |
| 20090101521 | Electrode for electrochemical reduction - An electrode ( | 04-23-2009 |
| 20090095042 | Method for Surface Blasting Cavities, Particularly Cavities in Gas Turbines - The invention relates to a method for the surface blasting of hollow spaces or cavities, especially of cavities of gas turbines. According to the invention, shot balls are accelerated with the aid of at least one vibrator, whereby the shot balls accelerated in the ultrasonic range are directed onto surfaces of a cavity that is to be blasted. In that regard, the vibrator is preferably positioned with a small spacing distance, preferably with a spacing distance on the order of magnitude of the diameter of the shot balls utilized for the blasting, from the cavity to be blasted. | 04-16-2009 |
| 20090092497 | Securing element for fastening moving blades - A securing element for securing the position of moving blades in slots, running at least mainly in the axial direction, of a rotor parent body of a turbomachine rotor is described, comprising a plate-shaped parent body, wherein the parent body has an approximately central recess which is formed between two end sections of the parent body and defines a center section, running between the two end sections, of the parent body, wherein the two end sections have bearing surfaces running parallel to one another. | 04-09-2009 |
| 20090075024 | METHOD FOR PRODUCING A THERMAL BARRIER COATING AND THERMAL BARRIER COATING FOR A COMPONENT PART - A method for producing a ceramic thermal barrier coating on a component part for use in compressor and turbine components by a vapor depositing process, and a ceramic thermal barrier coating, is disclosed. The method includes: a) provision of a ceramic vapor for depositing on the component part; b) depositing of the ceramic vapor on the component part to form a thermal barrier coating having a columnar structure, the columns being oriented substantially perpendicular to a surface of the component part; and c) varying of at least one method parameter during method step b) such that the resultant thermal barrier coating has columns of alternating decreasing and increasing diameters. The ceramic thermal barrier coating has a columnar structure and the columns are oriented substantially perpendicular to a surface of the corresponding part. The columns have alternately decreasing and increasing diameters. | 03-19-2009 |
| 20090075023 | METHOD FOR PRODUCING THERMAL BARRIER COATING AND A THERMAL BARRIER COATING - A method for producing a ceramic thermal barrier coating on a component part for use in compressor and turbine components by a vapor depositing process is disclosed. The method includes: a) provision of a ceramic vapor for depositing on the component part; b) depositing of the ceramic vapor on the component part to form a thermal barrier coating having a columnar structure, the columns being oriented substantially perpendicular to a surface of the component part; and c) varying of at least one method parameter during method step b) in such a way that the resultant thermal barrier coating has columns of alternating decreasing and increasing diameters. A thermal barrier coating is also disclosed. The thermal barrier coating has a ceramic thermal barrier coating having a columnar structure and the columns are oriented substantially perpendicular to a surface of the corresponding part. The columns have alternately decreasing and increasing diameters. | 03-19-2009 |
| 20090074582 | METHOD FOR JOINING METAL COMPONENTS AND DEVICE FOR EXECUTION OF AN INDUCTIVE LOW OR HIGH-FREQUENCY PRESSURE WELDING METHOD - The present technology concerns one or more methods for joining of metal components especially components of a gas turbine, in which joining of the corresponding joining surfaces of the components occurs by means of an inductive low or high-frequency pressure welding and in which, before heating and joining of the components by means of inductive low or high-frequency pressure welding, sputter etching of the joining surfaces is carried out. The present technology also concerns a device for execution of an inductive low or high-frequency pressure welding method for joining the metal components, especially components of a gas turbine, with at least one induction generator and at least one inductor, as well as a component produced with the method according to the present technology. | 03-19-2009 |
| 20090044406 | METHOD FOR PRODUCING METALLIC COMPONENTS, PARTICULARLY FOR TURBO MACHINES, HAVING SMALL EDGE RADII, AND COMPONENT PRODUCED THEREWITH - A method for producing metallic components, and metallic components produced by the method, particularly for turbo machines, having small edge radii, is disclosed. The method includes mechanical and/or electrochemical machining of a component while producing a small edge radius and solidifying the small edge radius by ultrasonic shot peening. As a result of the method, the disadvantages of the prior art are avoided and a machine process that can be automated has been provided, the method permitting considerable savings of time and labor and leading to reproducible results. | 02-19-2009 |
| 20090041610 | GAS TURBINE HONEYCOMB SEAL - A honeycomb seal which is manufactured by powder metallurgical injection molding is disclosed. The honeycomb seal is composed preferably of several segments. Each segment is embodied as a single piece and has a base element as well as honeycomb elements that are embodied as a single piece with the base element. | 02-12-2009 |
| 20090041607 | Method for the production of a sealing segment, and sealing segment to be use in compressor and turbine components - A method is provided for producing a sealing segment for use in compressor and turbine components, by powder injection molding, the method comprising the following steps: a) preparing a first homogeneous mixture of a metal powder or a mixture of metal powders or a ceramic powder or a mixture of ceramic powders and at least one binding agent; b) producing a first molded article by injection molding the first mixture; c) preparing a second homogeneous mixture of a metal powder or a mixture of metal powders or a ceramic powder or a mixture of ceramic powders and at least one binding agent, the second mixture being selected to exhibit a lower abrasion resistance than the first mixture following a subsequent joint sintering process; d) producing a second molded article as a rub strip by injection molding the second mixture; and e) joining the first and second molded articles to produce the sealing segment. A sealing segment is also provided for use in compressor and turbine components, composed of at least one first molded article as a base element and at least one second molded article having lower abrasion resistance than the first molded article, as a rub strip, the first and the second molded articles each being produced by powder injection molding. | 02-12-2009 |
| 20090039604 | APPARATUS AND METHOD FOR SEALING OFF COMPONENTS WITH RESPECT TO A PRESSURE DIFFERENCE REVERSAL - A brush seal for sealing off components movable relative to one another with respect to a pressure difference is disclosed. The brush seal having bristles which are arranged in a bristle housing which consists of two housing halves having free ends of legs which project into the area of the ends of the bristles, which legs carry mutually facing supporting surfaces for the bristles. | 02-12-2009 |
| 20090028712 | TURBOMACHINE HAVING AXIAL ROTOR BLADE SECURING - A rotor of a turbine machine having several rotor blade rings positioned in succession in the axial direction, is disclosed. Each rotor blade ring has a rotor base body with several rotor blades anchored by blade footings in axial grooves of the rotor base body that extend essentially in the axial direction and, in their anchored position in the rotor base body, are secured against displacement in the axial direction. The rotor blades of at least one rotor blade ring have hook-like securing elements, which, in the anchored position on a low-pressure side of the rotor blade ring, abut the rotor base body. The hook-like securing elements, between the rotor base body and a sealing element, which extends between the rotor base body and a rotor base body of a rotor blade ring that connects on the low-pressure side, are fixed in the axial direction on both sides. | 01-29-2009 |
| 20090025220 | Method and device for machining components of a gas turbine and composite material and its use in methods for machining or joining components of a gas turbine - A method for machining components of a gas turbine, in particular for machining turbine blades, is described. The method includes the following steps: a) providing at least one component carrier having at least one component receptacle for detachable accommodation and fastening component to be machined, the component receptacle being designed with a contour similar to at least one contour of subarea of component to be accommodated; b) introducing at least one subarea of the component into component receptacle and form-fitting and/or substance-to-substance bonding of the subarea of the component to component receptacle; c) machining the component, which is attached to the component carrier; and d) releasing the machined component from the component carrier. In addition, a device for machining turbine blades is described having at least one component carrier, the component carrier having at least one component receptacle for detachable accommodation and fastening of the component that is to be machined, and the component receptacle being designed with a contour resembling at least one contour of a subarea of the component that is to be accommodated, as well as a composite material for machining or bonding components of a gas turbine, in particular for machining turbine blades, the composite material including a woven or nonwoven fiber material and an adhesive, an adhesive support or individual adhesive components, such that the adhesive, the adhesive support or the adhesive components of the fiber material at least partially surrounds the fiber material. The use of the composite material in methods for machining or bonding components of a gas turbine is also described. | 01-29-2009 |
| 20090017201 | METHOD FOR COATING OR DECOATING A COMPONENT - The invention relates to a method for coating or decoating a component, in particular a gas turbine component, wherein, in order to regionally or partially coat or decoat a component, the component is preferably completely covered with a covering medium, and wherein the covering medium is removed from only those surface regions of the component in which the coating or decoating of the component is supposed to take place, so that a surface region of the component which is not to be coated or decoated is covered by the covering medium. According to the invention, the covering medium is removed by means of water jet machining. | 01-15-2009 |
| 20090011686 | Peening Chamber for Surface Peening, in Particular for Ultrasonic Shot Peening of Gas Turbine Components - The invention relates to a peening chamber for surface peening, in particular for ultrasonic shot peening of gas turbine components ( | 01-08-2009 |
| 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 |
| 20090001136 | Apparatus and Method for Rotational Friction Welding - A rotational friction welding apparatus and method for joining two components is disclosed. The apparatus includes a first spindle which turns and a second spindle which does not turn. A first component of the components that are to be connected together is mounted on the first, turning spindle, and a second component of the components that are to be connected together is mounted on the second, non-turning spindle, respectively, by way of a clamping device. Associated at least with the clamping device that is used to mount the first component on the first, turning spindle there is a planar toothing which for centering purposes and torque-transfer engages into a corresponding planar toothing associated with the first component. | 01-01-2009 |
| 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 |
| 20080298976 | Blade of a Turbomachine - A blade of a turbomachine, in particular of a gas turbine, is disclosed. The blade includes at least one fastening section for fastening the same in a locating section of a rotor-side or stator-side component of the turbomachine. The, or each, fastening section has a core region which is made of a relatively brittle and relatively light material and is embedded in an encasing region made of a material having relatively high ductility. | 12-04-2008 |
| 20080292457 | Device for Suspending Guide Blades | 11-27-2008 |
| 20080283416 | Process for Electrochemical Stripping of Components - A process for electrochemical stripping of components is disclosed. An operating point of the electrochemical stripping is determined under actual process conditions prior to the actual electrochemical stripping and is determined anew continuously, i.e., monitored and optionally adjusted during the electrochemical stripping. | 11-20-2008 |
| 20080282933 | Running-In Coating for Gas Turbines and Method for Production Thereof - A running-in coating for gas turbines and a method for production of a running-in coating are provided. The running-in coating serves to seal a radial gap between a housing ( | 11-20-2008 |
| 20080258404 | Seal Arrangement and Method for Manufacturing a Sealing Body for a Seal Arrangement - A seal arrangement and a method for manufacturing a sealing body for a seal arrangement for a turbine engine is disclosed. The seal arrangement seals a gap between a rotor and a stator, and has at least one first seal body preferably assigned to the stator and at least one blade-shaped second seal body preferably assigned to the rotor which co-acts with the or each first seal body. The or each first seal body has a main body and a porous wear component, where the main body and the wear component have a graduated material composition. | 10-23-2008 |
| 20080258403 | Seal Arrangement - A seal arrangement for a turbo-engine, for sealing a peripheral gap between a rotor and a stator is provided. The stator a seal holder provided with at least one groove for respectively receiving a segmented, dynamic seal. Segments of the dynamic seal are made up of a plurality of brush seal segments, and free ends of bristles of the brush seal segments extend in the radial direction project from the respective groove and lie on the rotor. The or every groove for receiving the brush-type seal segments is designed without an undercut, the brush-type seal segments being received in the respective groove without an undercut in a positive manner. | 10-23-2008 |
| 20080249722 | Method for Determination of Strain Distribution in Components - A method for determination of strain distribution in components, in particular in gas turbine components, is disclosed. In an embodiment, the method includes: a) vibrational excitation of the component and measured recording of a vibrational amplitude distribution of the component for a number of measured points by means of a vibrometer, each measuring point being determined by three coordinates and the measured vibrational amplitude distribution of each measuring point being a vectorial parameter; b) smoothing of the vibrational amplitude distribution recorded by measurement for each measuring point; c) definition of polygonal elements, wherein each measuring point forms a corner of at least one element; d) calculation of a tensor strain condition for each of the polygonal elements from the tensor vibrational amplitude distributions present in the corners of the elements; and e) calculation of the strain distribution in the corners of the elements from the strain conditions of the elements. | 10-09-2008 |
