MTU Aero Engines GmbH Patent applications |
Patent application number | Title | Published |
20160116442 | DESTRUCTION-FREE AND CONTACTLESS INSPECTION METHOD AND INSPECTION APPARATUS FOR SURFACES OF COMPONENTS WITH ULTRASOUND WAVES - The invention relates to a method of nondestructive and contactless testing of components ( | 04-28-2016 |
20160074969 | PROCESS FOR PRODUCING HOLES - A method of producing holes in a component, in particular of turbomachines, wherein each hole extends from a first, outer surface to a second, inner surface of the component and wherein the method has, for example, the following steps: (i) producing a 3D model of the actual geometry of the component, at least for the region of the holes; (ii) adapting each hole on the basis of the actual geometry of the component; and (iii) generating a production program for each individual hole. In this way, the process quality and with it the quality of the holes increases, because the offset of holes caused by component tolerances is avoided and the drilling funnels are formed according to specification. Furthermore, drilling defects on account of the offset of holes and/or cores can be avoided. Overlapping holes caused by component tolerances are likewise avoided. | 03-17-2016 |
20140154085 | GAS TURBINE AND GUIDE BLADE FOR A HOUSING OF A GAS TURBINE - A gas turbine, in particular an aircraft engine, having a housing in which at least one guide blade ( | 06-05-2014 |
20140147286 | TURBOMACHINE ROTOR DISK - A rotor disk for a turbomachine, which is connectable to at least one rotor blade and/or a shaft of the turbomachine, having at least one borehole, which has an elliptical inlet opening having a first passage cross-sectional area and an elliptical outlet opening having a second passage cross-sectional area, so that the second passage cross-sectional area is smaller than the first passage cross-sectional area. | 05-29-2014 |
20140143991 | METHOD AND DEVICE FOR MACHINING ROBOT-GUIDED COMPONENTS - A method for machining a robot-guided component with a tool which is fastened in an articulated manner to a tool holder is disclosed. The method includes detecting a deflection of the tool with respect to the tool holder from a desired position and changing a pose of a robot that is guiding the robot-guided component on a basis of the detected deflection. | 05-29-2014 |
20140072432 | BLADE ARRANGEMENT FOR A TURBO ENGINE - A blade arrangement for a turbo engine, in particular a gas turbine, with a rotor and several blades fastened thereto, which are configured to be systematically different, wherein at least two adjacent blades have systematically different shrouds ( | 03-13-2014 |
20130343900 | PROCESS FOR PRODUCING A RUN-IN COATING - Disclosed is a process for producing a run-in coating ( | 12-26-2013 |
20130318988 | AIRCRAFT ENGINE WITH TURBINE HEAT EXCHANGER BYPASS - An aircraft engine, in particular a helicopter engine, having a one or multi-stage compressor system (V), a combustion chamber (BK) connected downstream therefrom, and a one- or multi-stage turbine system (HT, NT) connected downstream therefrom, a compressor heat exchanger system (WV), a turbine heat exchanger system (WT), and a bypass means for optionally guiding the working medium through or past at least one turbine heat exchanger (WT) of the turbine heat exchanger system. | 12-05-2013 |
20130287583 | Damping means for damping a blade movement of a turbomachine | 10-31-2013 |
20130280083 | ROTOR BLADE ARRANGEMENT FOR A TURBO MACHINE - In a moving blade system for a turbomachine, in particular a gas turbine, having at least one moving blade ( | 10-24-2013 |
20130270325 | NICKEL-BASED SOLDER ALLOY - Solder alloy based on nickel is composed of a mixture with a first soldering material, a second soldering material, and a base material, wherein the base material is a nickel-based material which corresponds to the material to be soldered and is present in a proportion of 45-70% by weight in the mixture, the first soldering material is a nickel-based material including chromium, cobalt, tantalum, aluminum and boron, and is present in a proportion of 15-30% by weight in the mixture, and the second soldering material is a nickel-based material including chromium, cobalt, molybdenum, tungsten, boron and hafnium, and is present in a proportion of 15-25% by weight in the mixture. | 10-17-2013 |
20130266427 | SEALING SYSTEM FOR A TURBOMACHINE - A sealing system for a turbomachine, in particular, for a gas turbine, having an annular space between a flow-restricting wall and at least one series of rotor blades including a plurality of rotor blades. The sealing system comprises at least one first sealing fin disposed on an end of the rotor blade facing the wall, at least one second abradable lining disposed following the first sealing fin in the flow direction on the end of the rotor blade facing the wall, at least one first abradable lining disposed on the inside of the wall and opposite the first sealing fin, and at least one second sealing fin disposed in the flow direction following the first abradable lining on the inside of the wall and opposite the second abradable lining. The invention furthermore relates to a gas turbine comprising at least one sealing system. | 10-10-2013 |
20130266426 | SEALING SYSTEM FOR A TURBOMACHINE - Disclosed is a sealing system for a turbomachine, in particular for a gas turbine, the sealing system being formed in an annular space between a flow-limiting wall of the turbomachine and at least one rotor blade tip of a rotor blade or an outer shroud arranged on the rotor blade tip, and comprising at least one sealing point. The sealing point comprises at least one run-in coating arranged on the rotor blade tip or on the outer shroud in the direction of the flow-limiting wall of the turbomachine. The invention furthermore encompasses a gas turbine comprising the sealing system. | 10-10-2013 |
20130259690 | ALUMINIDE OR CHROMIDE COATINGS OF CAVITIES - Disclosed is a process for producing an alloyed, in particular multiple-alloyed aluminide or chromide layer on a component by alitizing or chromizing. First a green compact layer ( | 10-03-2013 |
20130251532 | SECURING DEVICE FOR AXIALLY SECURING A BLADE ROOT OF A TURBOMACHINE BLADE - A securing device ( | 09-26-2013 |
20130243602 | BLADE RING SEGMENT HAVING AN ANNULAR SPACE DELIMITING SURFACE HAVING A WAVY HEIGHT PROFILE AND A METHOD FOR MANUFACTURING SAME - A method for machining a workpiece. An electrode is moved linearly in the direction of the workpiece to cause material to be removed from the workpiece, at least one end of a surface of the workpiece running obliquely to a guide edge of the electrode machining this surface. The electrode is moved at least partially with the electrode surface parallel to the surface, so that during the approach to the workpiece, areas of the workpiece having an irregular edge machined at a different intensity are formed, the difference in intensity of machining on the edge of the surface to be machined being compensated in that the surface to be machined is provided with a height profile adapted to the shape of the end of the surface to be machined. A blade ring segment and blade ring is also disclosed. | 09-19-2013 |
20130236300 | HOUSING AND TURBOMACHINE - A housing for a turbomachine includes a peripheral wall delimiting an annular space and a fluid conveying system for redirecting a partial flow of a main flow, which has an axial channel, a front annular channel and a rear annular channel in fluid connection with the axial channel and having a front annular space opening and a rear annular space opening. The fluid conveying system has a front valve device and a rear valve device controllable independently of the front valve device, for opening and closing the annular space openings, and an outlet opening for tapping the partial flow from the fluid conveying system. In the closed state of the rear annular space opening, the partial flow is directable through the rear annular channel and, in the closed state of the front annular space opening, the partial flow is directable through the front annular channel. | 09-12-2013 |
20130230388 | COMPRESSOR - A compressor having a stator vane assembly having an inner ring and a seal carrier secured thereto, the seal carrier having two opposite seal carrier end faces and the inner ring having two inner ring end faces which face said seal carrier end faces and are received between said seal carrier end faces with an axial gap therebetween, at least one clamping element bearing axially with a first clamping element end face against the inner ring and with a second clamping element end face against the seal carrier and being axially resiliently clamped between the inner ring and the seal carrier. A compressor with a clamping element for radial clamping is also provided. | 09-05-2013 |
20130209259 | BLADE GROUP ARRANGEMENT AS WELL AS TURBOMACHINE - A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade. | 08-15-2013 |
20130209241 | TURBOMACHINE - A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge distance which varies starting from a main flow path center in the direction of at least one main flow limitation, the periphery-side edge distance increasing or decreasing on both sides. | 08-15-2013 |
20130209224 | TURBOMACHINE - A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades ( | 08-15-2013 |
20130209223 | TURBOMACHINE - A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades, whereby the trailing edges of the blades of the upstream row of blades and the leading edges of the blades of the downstream row of blades are arranged at an axial edge distance that decreases from the center of the main flow path in the direction of at least one main flow limiter. | 08-15-2013 |
20130202444 | BLADE CASCADE AND TURBOMACHINE - A blade cascade for a turbomachine having a plurality of blades arranged next to one another in the peripheral direction, at least two blades having a variation for generating an asymmetric outflow in the rear area, as well as a turbomachine having an asymmetric blade cascade, which is connected upstream from another blade cascade, are disclosed. | 08-08-2013 |
20130195611 | Unknown - A method for vibration damping of at least one blade of a turbomachine, wherein initially at least one damping element is arranged on the blade such that it can move in the axial direction, employs a damping element having a larger permeability constant than the blade (μ | 08-01-2013 |
20130193000 | ELECTRODE AND INSTALLATION FOR ELECTROCHEMICAL MACHINING AND METHOD THEREFOR - Disclosed is an electrode arrangement for the defined rounding or deburring of edges of electrically conductive components, in particular turbine components, by means of electrochemical machining with at least one working electrode ( | 08-01-2013 |
20130189429 | Method for Producing a Locally Limited Diffusion Coat and Reactor for it - A method for producing a locally limited diffusion coat on a metallic component is disclosed. In an embodiment, the method includes arranging the component and at least one dispenser pack containing the material to be diffused, making available at least one protective gas stream, which flows around the at least one region of the component that is not to be provided with a diffusion coat, and heating the component and the dispenser pack to a temperature for carrying out the diffusion and maintaining the temperature for a specific time. A reactor for producing a locally limited diffusion coat on a metallic component is also disclosed. | 07-25-2013 |
20130189111 | ROTOR FOR A TURBOMACHINE - A rotor for a turbomachine, in particular for a jet engine, having a blade ring which includes multiple differently designed rotor blades ( | 07-25-2013 |
20130189108 | BLADE RIM SEGMENT FOR A TURBOMACHINE AND METHOD FOR MANUFACTURE - The present invention relates to a blade rim segment for a turbomachine with at least one shroud band which extends along a segment of a circle and is connected in single-piece fashion with at least three blades, which extend radially from the shroud band and are configured to be hollow with at least one channel, wherein the blade rim segment is manufactured in a single piece by casting and directional solidification, and wherein at the outlet openings of the channels of the blades, the shroud band exhibits first reinforcement ribs that surround the opening and run axially, as well as at least one second reinforcement rib between at least the first reinforcement ribs, as well as a corresponding method for manufacturing a blade rim segment. | 07-25-2013 |
20130189086 | SEAL ASSEMBLY, METHOD AND TURBOMACHINE - A sealing arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, with a plurality of sealing segments each comprising a honeycomb element and a base body for holding the honeycomb element, and with at least one support for arranging the sealing segments on a rotor section or stator section, wherein the base bodies can be arranged on the at least one support by a radial movement and by a plastic deformation of at least one body section, a generative method for the integral production of the sealing segments, and a turbomachine are disclosed. | 07-25-2013 |
20130189085 | TURBOMACHINE SEAL ARRANGEMENT - The present invention relates to a seal arrangement for a turbomachine, in particular a gas turbine, having a plurality of rows, arranged in succession in the axial direction (A), of shells ( | 07-25-2013 |
20130187061 | METHOD FOR NONDESTRUCTIVE TESTING OF WORKPIECE SURFACES - A method for nondestructive testing of workpiece surfaces by a fluorescent penetration test is disclosed. An embodiment of the method includes a) cleaning the area of the workpiece surface that is to be inspected; b) applying a fluorescent liquid penetrant to the area of the workpiece surface that is to be inspected, where the penetrant penetrates into possible recesses in the workpiece surface; c) removing the excess penetrant from the workpiece surface; d) applying a developer to the area of the workpiece surface that is to be inspected; e) bleaching the fluorescent penetrant by a beam of light in the layer formed by applying the developer to the workpiece surface; and 0 visual evaluation of the fluorescent penetrant remaining in the recesses present in the workpiece surface. | 07-25-2013 |
20130183149 | HOUSING-SIDE STRUCTURE OF A TURBOMACHINE - A housing-side structure of a turbomachine, in particular of a gas turbine, including an in particular segmented jacket ring ( | 07-18-2013 |
20130180249 | SYSTEM FOR INJECTING A FLUID, COMPRESSOR AND TURBOMACHINE - A system for injecting a fluid into a wall boundary layer of a flow in a turbomachine is disclosed. The system has a plurality of nozzles which are disposed in a side wall limiting the flow and are oriented diagonally in the direction of flow. The nozzles each have a rectangular, flat nozzle cross-section. A compressor having such a system, as well as a turbomachine having such a compressor, are also disclosed. | 07-18-2013 |
20130174869 | CLEANING OF A TURBO-MACHINE STAGE - The invention relates to a method for cleaning a turbo-machine stage ( | 07-11-2013 |
20130171343 | Method for repair of a component of a turbomachine and a component repaired according to this method - A method is disclosed for the repair of a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with blades taken up in at least one groove and with at least one support region for limiting a blade tilt angle, whereby at least one segment, which has been subjected to wear, of the support region of the component is removed, and a coating that can be introduced in the unit on at least one supporting surface of at least one blade is formed on the component for limiting the blade tilt angle. In addition, a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with at least one such repair site is disclosed. | 07-04-2013 |
20130167375 | APPARATUS AND METHOD FOR PROCESSING A SEALING ELEMENT LOCATED WITHIN THE HOUSING OF A GAS TURBINE - A machining or processing apparatus ( | 07-04-2013 |
20130160940 | MOUNTING DEVICE AND METHOD FOR MOUNTING A COMPONENT ON A COMPONENT CARRIER USING AN ADHESIVE - A mounting device and method for mounting a component is disclosed. The mounting device includes a component carrier and an adapter. The adapter is insertable into a guide of the component carrier. The method uses the mounting device to mount a component on the mounting device. | 06-27-2013 |
20130156563 | TURBOMACHINE AND TURBOMACHINE STAGE - A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference. A maximum extent of this contour in the radial direction toward the spoke-like pattern is circumferentially spaced from an airfoil edge of this cascade by no more than 50% of the cascade pitch, a maximum variation in the radial direction being no more than 50% of the cascade pitch and/or a maximum extent in the axial direction away from the spoke-like pattern is circumferentially spaced from an airfoil edge of this cascade by no more than 50% of the cascade pitch, a maximum variation in the axial direction being no more than 50% of the cascade pitch. | 06-20-2013 |
20130156562 | TURBOMACHINE AND TURBOMACHINE STAGE - A turbomachine stage including guide vanes, radially inner and/or radially outer airfoil platforms, which together form a guide vane cascade, and further including rotor blades, radially inner and/or radially outer airfoil platforms, which together form a rotor blade cascade adjacent to the guide vane cascade. Radially outer airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies, in particular periodically, in the radial and/or axial direction around the circumference. | 06-20-2013 |
20130149165 | ROTATING BLADE HAVING A RIB ARRANGEMENT WITH A COATING - The present invention relates to a rotating blade ( | 06-13-2013 |
20130143068 | PROCESS AND APPARATUS FOR APPLYING LAYERS OF MATERIAL TO A WORKPIECE MADE OF TIAL - A method for depositing material layers on a workpiece made of a material which contains a titanium aluminide includes the steps of preparing the workpiece; heating the workpiece in a localized region by induction to a predefined preheating temperature; and depositing an additive, preferably in powder form, on the heated surface of the workpiece by build-up welding, in particular laser build-up welding, plasma build-up welding, micro-plasma build-up welding, TIG build-up welding or micro-TIG build-up welding; said additive including a titanium aluminide. | 06-06-2013 |
20130139852 | METHOD AND DEVICE FOR REMOVING A LAYER FROM A SURFACE OF A BODY - A method for removing a layer made of a first material from a surface of a body made of a second material is disclosed. The body is subjected to a pressurized jet containing a blasting medium composed of particles, where the pressurized jet at least intermittently has an Almen intensity of at most 0.35 Almen A, preferably at most 0.3 Almen A and particularly preferably at most 0.25 Almen A. | 06-06-2013 |
20130136621 | BLADING - A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades. | 05-30-2013 |
20130136619 | BLADING - A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades. | 05-30-2013 |
20130129976 | COATING PLASTIC COMPONENTS BY MEANS OF KINETIC COLD GAS SPRAYING - A method for coating a plastic surface and a plastic component is disclosed. The method includes applying a base layer to a plastic surface. A layer of a coating is applied by kinetic cold gas spraying on the base layer. The base layer is applied by a method that is different from the kinetic cold gas spraying. The base layer adheres to the plastic surface and the layer of the coating applied by kinetic cold gas spraying is deposited on the base layer by the kinetic cold gas spraying. | 05-23-2013 |
20130089424 | BLADE ROW FOR A TURBOMACHINE - A blade row for a turbomachine, in particular a gas turbine, is disclosed. The blade row has a number of first blade arrangements each having at least one first blade and a first shroud with a first extension in the circumferential and/or axial direction and at least a number of additional blade arrangements each having at least one additional blade and one additional shroud with an additional extension in the same direction, which is different from the first extension. | 04-11-2013 |
20130064657 | INTERMEDIATE HOUSING OF A GAS TURBINE HAVING AN OUTER BOUNDING WALL HAVING A CONTOUR THAT CHANGES IN THE CIRCUMFERENTIAL DIRECTION UPSTREAM OF A SUPPORTING RIB TO REDUCE SECONDARY FLOW LOSSES - Intermediate housing ( | 03-14-2013 |
20130056365 | METHOD AND ELECTRODE FOR ELECTROCHEMICALLY PROCESSING A WORKPIECE - A method for electrochemically processing a workpiece surface using an electrode, which has at least one effective surface for processing the workpiece surface, and using an electrolyte, wherein the electrolyte is suctioned away from the effective surface. The invention further relates to an electrode, which has at least one electrolyte feed for supplying the electrolyte to the effective area and an electrolyte suctioning system for suctioning the electrolyte away from the effective area. | 03-07-2013 |
20130055568 | METHOD AND DEVICE FOR PRODUCING A COMPONENT - A method for manufacturing a component, in particular a component of a turbine or a compressor, in which at least these steps are carried out: application in layers of at least one powdered component material to a component platform in the area of a buildup and joining zone; melting and/or sintering locally in layers of the component material by supplying energy with the aid of at least one electron beam in the area of the buildup and joining zone; lowering of the component platform in layers by a predefined layer thickness; and repeating steps a) through c) until completion of the component. During the manufacturing, electrons emitted due to the interaction of the electron beam with the component material are detected, after which material information, characterizing the topography of the melted and/or sintered component material, is ascertained on the basis of the emitted electrons. Alternatively or additionally, the component material is melted and/or sintered by at least two, preferably at least four electron beams. | 03-07-2013 |
20130034661 | METHOD FOR PROCESSING A SURFACE OF A COMPONENT - A method for processing a surface of a component, in particular in the aviation sector, including the following steps: spraying the component with a first powder and coating the component with a second powder, the first powder having the same chemical composition as the second powder. | 02-07-2013 |
20130032215 | DEVICE AND METHOD FOR PRESERVING FLUID SYSTEMS AND AN ENGINE - Disclosed is a device for preserving fluid systems, for example of a fuel system and an oil system of a turbine engine, with at least one drive for driving at least one fuel pump and at least one oil pump, wherein a valve arrangement is provided, which makes transfer-pumping a fluid between the fluid systems possible, an engine having such a device as well as a method for triggering such a device or for preserving fluid systems. | 02-07-2013 |
20130028749 | GUIDE BLADE OF A TURBOMACHINE - A guide blade of a turbomachine, in particular of a compressor, a blade of the guide blade without an inner shroud having a flow inlet edge, a flow outlet edge, a suction side, and a pressure side. The blade is formed by a plurality of blade sections stacked one on top of the other in the radial direction, and the centers of gravity of the blade sections extend along a stacking axis. The blade sections are stacked one on top of the other in the radial direction in such a way that, in a radially inner section of the blade adjacent to a radially outer section of the blade, the stacking axis has its single inflection point in its radial curvature, namely, between a first, radially inner subsection of the radially inner section in which the stacking axis has a concave curvature toward the pressure side, and a second, radially outer subsection of the radially inner section in which the stacking axis has a concave curvature toward the suction side. | 01-31-2013 |
20120315148 | BLADE COMPRISING PRE-WIRED SECTIONS - The invention relates to a method for wiring suctions ((i), (i+1)) of a blade ( | 12-13-2012 |
20120301279 | HOUSING SYSTEM FOR AN AXIAL TURBOMACHINE - The English-language Abstract from the international application is to be retained and is therefore not duplicated in the specification. | 11-29-2012 |
20120288639 | COMBINED HEATING FOR SOLDERING AN ARMOR CLADDING ONTO A TIP BY MEANS OF INDUCTION AND LASER - The present invention relates to a method for coating a component ( | 11-15-2012 |
20120288616 | MEASUREMENT METHOD AND DEVICE FOR MEASURING LAYER THICKNESSES AS WELL AS PRODUCTION METHOD AND COATING SYSTEM - A method for measuring the thickness of a coating on a component section of a rotating component, wherein a heat expansion of the component section is determined by detecting a component core temperature and an actual coating thickness is produced, a device for conducting a method of this type having a temperature detecting system and having an evaluating device, as well as a production process and a coating system, are disclosed. | 11-15-2012 |
20120282109 | Blade, Integrally Bladed Rotor Base Body and Turbomachine - A blade for a turbomachine is disclosed. At least one cooling channel is configured in the blade neck, whose inlet is disposed near a platform projection on the high-pressure side and whose outlet is disposed in the region of a platform projection on the low-pressure side. An integrally bladed rotor base body having a plurality of these types of blades as well as turbomachine with such a rotor base body is also disclosed. | 11-08-2012 |
20120282098 | SEALING DEVICE, INTEGRALLY BLADED ROTOR BASIC BODY, AND TURBOMACHINE - A sealing device for an integrally bladed rotor basic body of a turbomachine to suppress a gas exchange between a hot gas stream and a cooling air stream in the radial direction in contact areas of adjacent moving blades, including a plurality of sealing elements activatable by centrifugal force, which may be situated in the area of channels which extend from a high-pressure side to a low-pressure side and are peripherally delimited by the moving blades, an integrally bladed rotor basic body having such a sealing device, and a turbomachine having such an integrally bladed rotor basic body. | 11-08-2012 |
20120282088 | INNER RING FOR FORMING A GUIDE BLADE RING, AND GUIDE BLADE RING AND TURBOMACHINE - An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring. | 11-08-2012 |
20120280021 | METHOD FOR PRODUCING AN INTEGRALLY BLADED ROTOR USING ARCUATE FRICTION WELDING, DEVICE FOR CARRYING OUT SAID METHOD, AND ROTOR PRODUCED BY MEANS OF SAID METHOD - A method for producing an integrally bladed rotor, in particular a gas turbine rotor, comprises the following steps:—Providing a blade ( | 11-08-2012 |
20120269642 | METHOD FOR FUSION WELDING A MONOCRYSTALLINE WORKPIECE TO A POLYCRYSTALLINE WORKPIECE AND ROTOR - A method for fusion welding a metal workpiece, which has a monocrystalline structure, to a metal workpiece, which has a polycrystalline structure, using a fiber laser and producing an I seam, is disclosed. A rotor produced according to the method is also disclosed. | 10-25-2012 |
20120266439 | METHOD FOR PRODUCING A COMPONENT WITH AT LEAST ONE ELEMENT ARRANGED IN THE COMPONENT - A method for manufacturing a component having at least one element configured in the component, in particular at least one conduit, conduit unit, or supporting element configured within an aerodynamic rib, the component having an element leadthrough for leading through the at least one element, the method including the following step: building up in layers of the component including the element leadthrough, together with the at least one element in a generative production process. | 10-25-2012 |
20120251310 | METHOD FOR PRODUCING AN ABRADABLE COATING ON A TURBOMACHINE - In a method for producing an inlet coating ( | 10-04-2012 |
20120230825 | GAS TURBINE BLADE FOR A TURBOMACHINE - The invention relates to a gas turbine blade ( | 09-13-2012 |
20120225213 | METHOD AND DEVICE FOR COATING COMPONENTS - A method for spraying a coating and a cold gas spray nozzle is disclosed. The method includes spraying a coating by the cold gas spray nozzle. A rinsing gas is fed to the cold gas spray nozzle during an interruption of the spraying or at an end of the spraying. Deposits in the cold gas spray nozzle are cooled and detached by the rinsing gas. | 09-06-2012 |
20120224972 | METHOD AND DEVICE FOR PRODUCING AN INTEGRALLY BLADED ROTOR AND ROTOR PRODUCED BY MEANS OF THE METHOD - A method for producing an integrally bladed rotor, in particular a gas turbine rotor, by means of joining, comprises the following steps:—Providing a blade ( | 09-06-2012 |
20120224969 | COUPLING ELEMENT FOR MECHANICALLY COUPLING BLADES AND A ROTOR - A coupling element | 09-06-2012 |
20120219726 | METHOD AND DEVICE FOR PRODUCING A COMPONENT - The invention relates to a method for producing a component ( | 08-30-2012 |
20120217226 | METHOD AND DEVICE FOR PRODUCING A COMPONENT OF A TURBOMACHINE - The invention relates to a method for producing a component ( | 08-30-2012 |
20120213659 | METHOD AND DEVICE FOR PRODUCING A COMPONENT OF A TURBOMACHINE - A method for producing a component of a turbomachine is disclosed. The method includes a) layer-by-layer deposition of a powder component material onto a component platform in a region of a buildup and joining zone, where the deposition takes place in accordance with layer information of the component to be produced; b) local layer-by-layer fusion or sintering of the powder component material by energy supplied in the region of the buildup and joining zone, where the buildup and joining zone is heated to a temperature just below a melting point of the powder component material; c) layer-by-layer lowering of the component platform by a predefined layer thickness; and d) repetition of steps a) to c) until the component is finished. A device for producing a component of a turbomachine is also disclosed. | 08-23-2012 |
20120211151 | DEVICE FOR FASTENING AND DETACHING A COMPONENT, AND METHOD THEREFOR | 08-23-2012 |
20120201691 | METHOD FOR PRODUCING A ROTOR OR STATOR BLADE AND SUCH A BLADE - The invention relates to a method for producing a rotor or stator blade ( | 08-09-2012 |
20120201688 | BLADE CHANNEL HAVING AN END WALL CONTOUR AND A TURBOMACHINE - A blade channel having a not-axially-symmetric end wall contour in a turbomachine is disclosed, the end wall contour having at least one individual contour in the form of an elevation, on the pressure side, and at least three individual contours in the form of two recesses and one elevation, on the suction side, the elevation being situated between the recesses in the flow direction; a turbomachine having a plurality of blade channels of this type is also disclosed. | 08-09-2012 |
20120198858 | RING ELEMENT AND TURBOMACHINE HAVING SUCH A RING ELEMENT - A ring element for a turbomachine, in particular for an aircraft gas turbine, is disclosed. The ring element has a ring element main body that has two adjacently arranged ring ends, the ring ends being connected to one another in a form-locking manner with respect to an axial plane. Also disclosed is a turbomachine having at least one such ring element. | 08-09-2012 |
20120171041 | THIN-WALLED STRUCTURAL COMPONENT, AND METHOD FOR THE PRODUCTION THEREOF - A method for producing a thin-walled structural component from a casting material. The casting material is supplied as a powder, and the powder is deposited on a support ( | 07-05-2012 |
20120156630 | METHOD FOR THE LOCAL HEAT TREATMENT OF GAS TURBINE BLADES - A method for heat-treating gas turbine blades, namely for locally heat-treating at least one gas turbine blade in a blade section thereof; a blade root section, which is not to be heat-treated, of the gas turbine blade being positioned in a holding receptacle to prevent an unacceptable heating of the particular blade root section, which is not to be heat-treated, during the heat treatment of the particular blade section. The blade root section of the gas turbine blade is positioned in an interior space in a way that allows a remaining interior space of the holding receptacle, to be filled with a filler material; the holding receptacle, together with the gas turbine blade, being subsequently positioned in a heat treatment chamber to enable the gas turbine blade in the heat treatment chamber to undergo local heat treatment under vacuum. | 06-21-2012 |
20120156047 | AIRCRAFT ENGINE BLADING - A blading for a turbine, in particular a gas turbine, is disclosed. The blades of the blading in a section near the tip have a distribution ratio (t/l) of at least 0.70, in particular at least 0.9, and/or at most 0.97, in particular at most 0.95. A downstream flow angle (α) is at most 167°, in particular at most 165°, and at least 155°, in particular at least 160°. In addition, or alternatively, an acceleration ratio (w | 06-21-2012 |
20120148413 | METHOD FOR REPLACING A BLADE OF A ROTOR HAVING INTEGRATED BLADES AND SUCH A ROTOR - A method for replacing a blade ( | 06-14-2012 |
20120144931 | PRESSURE-MEASURING PROBE - The invention relates to a pressure-measuring probe ( | 06-14-2012 |
20120141822 | ANTI-WEAR COATING AND COMPONENT COMPRISING AN ANTI-WEAR COATING - An anti-wear coating, in particular an anti-erosion coating, which is applied to a surface of a component that is stressed under fluid technology and is to be protected, in particular a gas turbine part, is disclosed. The anti-wear coating includes one or more multilayer systems applied in a repeating order to the surface to be coated, and the/each multilayer system includes at least one relatively soft metallic layer and at least one relatively hard ceramic layer. All the layers of the/each multilayer system are based on chromium, and a diffusion barrier layer is applied between the surface to be protected and the multilayer system(s). | 06-07-2012 |
20120141259 | BLADE SEGMENT AND FLUID FLOW MACHINE - A blade segment ( | 06-07-2012 |
20120141253 | TURBOMACHINE - A turbomachine is disclosed. The turbomachine includes a housing and a guide blade ring. An outer shroud of the guide blade ring is divided into segments by joints, where the outer shroud is fastened to the housing by a first fastening element for absorbing axial force and a second fastening element independent of the first fastening element for absorbing circumferential force. The first fastening element and the second fastening elements enable play in a radial direction for the segments of the outer shroud. | 06-07-2012 |
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 |