MTU AERO ENGINES AG Patent applications |
Patent application number | Title | Published |
20160061116 | SHAFT SEAL SYSTEM AND A COMPRESSOR HAVING A CORRESPONDING SHAFT SEAL SYSTEM - A shaft seal system which is disposed axially between a first chamber and a second chamber is disclosed. The shaft seal system includes a shaft, a casing that surrounds the shaft, and a seal which is disposed axially closer to the second chamber where the first chamber has a fluid and the second chamber is to be protected from the fluid. In this arrangement, the seal includes a pressure booster. | 03-03-2016 |
20160040713 | ROLLER BEARINGS, IN PARTICULAR NEEDLE BEARINGS, FOR ARRANGING ON A PIVOT PIN OF A VARIABLE GUIDE VANE OF A TURBOMACHINE - A roller bearing, particularly a needle bearing, for arranging on a pivot pin of a variable guide vane of a turbomachine, is disclosed. The roller bearing includes at least one radially elastic needle which has two opposing end regions and at least one roller region arranged between the end regions and constructed in a cross-sectionally thickened manner. The end regions roll off at associated raceways of a bearing housing of the roller bearing and the roller region is arranged in the region of an associated groove of the bearing housing. A variable guide vane with at least one such roller bearing, a housing of a turbomachine with such a guide vane, as well as a turbomachine, is also disclosed. | 02-11-2016 |
20160032760 | HOUSING FOR A GAS TURBINE, AIRCRAFT ENGINE, AND A PROCESS FOR OPERATING A GAS TURBINE - A housing for a gas turbine is disclosed. At least one wall element is housed on the housing so as to move, which limits a flow channel of the housing in the radial direction from a rotational axis of a rotor of the gas turbine toward the exterior. The housing includes at least one variably adjustable guide blade which extends through the wall element into the flow channel. The wall element can be moved between a sealing setting, in which the wall element makes contact at least in a partial area of a side of a blade leaf of the guide blade facing toward the wall element, and an open setting, in which the blade leaf and the wall element are spaced some distance apart from one another. A gas turbine as well as a process for operating a gas turbine is also disclosed. | 02-04-2016 |
20160032749 | Leaf Seal for Sealing Off a Shaft Rotating Around an Axis - A leaf seal for sealing off a shaft rotating around an axis, particularly in a gas turbine, is disclosed. The leaf seal includes a plurality of leaves arranged spaced apart from one another, where the leaves are produced integrally with a basic element supporting the leaves by a generative production process. A process for producing a leaf seal for sealing off a shaft rotating around an axis is also disclosed. | 02-04-2016 |
20160032748 | GUIDE BLADE FOR A GAS TURBINE - A guide blade for a gas turbine is disclosed. The guide blade includes a blade leaf having a receptacle in which at least one sealing element is arranged, where the sealing element is movable relative to the blade leaf between a sealing setting, in which the sealing element is at least partially moved out of the receptacle, and a storage setting, in which the sealing element is moved back into the receptacle. The guide blade further includes at least one fluid channel by which fluid under pressure can be routed into the receptacle in order to move the sealing element from the storage setting into the sealing setting. An inlet opening of the fluid channel is formed on a pressure-side surface of the blade leaf. A housing as well as a gas turbine having at least one guide blade is also disclosed. | 02-04-2016 |
20160003360 | BRUSH SEAL - A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure. | 01-07-2016 |
20150377049 | BRUSH SEAL SYSTEM FOR SEALING A CLEARANCE BETWEEN COMPONENTS OF A TURBO ENGINE THAT ARE MOVABLE IN RELATION TO ONE ANOTHER - A brush seal system for sealing a clearance between components of a turbo engine that are movable in relation to one another, in particular of a thermal gas turbine, is disclosed. The brush seal system includes a brush seal housing, which accommodates at least one brush head of a brush seal, where the brush seal housing includes a first component having a cover plate section and a second component having a support plate section. The first component includes an axial flange forming a fish mouth seal on an end opposite the cover plate section. A thermal gas turbine having such a brush seal system is also disclosed. | 12-31-2015 |
20150323318 | DEVICE AND METHOD FOR GENERATIVE PRODUCTION OF AT LEAST ONE COMPONENT AREA OF A COMPONENT - A device for generative production of at least one component area of a component, in particular a component of a turbine or a compressor, is disclosed. The device includes at least one powder feed for application of at least one powder layer to a build-up and joining zone of a component platform that can be lowered and at least one radiation source for generating at least one high-energy beam by which the powder layer can be fused and/or sintered locally in the area of the build-up and joining zone to form a component layer. The device further includes a camera system which can produce at least one stereoscopic image for three-dimensional detection of at least one area of the component layer. A method for producing at least one component region of a component, in particular a component of a turbine or a compressor, is also disclosed. | 11-12-2015 |
20150276683 | METHOD AND DEVICE FOR ASCERTAINING AN EDGE LAYER CHARACTERISTIC OF A COMPONENT - The invention relates to a method and device for ascertaining an edge layer characteristic of a component ( | 10-01-2015 |
20150252691 | Gas Turbine Duct Casing - A gas turbine duct casing, in particular for an aircraft engine, is disclosed. The duct casing has a first wall segment and a second wall segment which is connected to the first wall segment by a clamp arrangement. The clamp arrangement has at least one clamp and one bolt which passes through a hole in the clamp and is screwed to a nut on a side of the clamp facing away from the wall segments. The nut braces at least one first leg of the clamp against the first wall segment, in particular by an intermediate element, and braces at least one second leg of the clamp against the second wall segment. The bolt has a head which is guided in a form-fitting manner in a groove on the outside of the first wall segment facing away from the gas duct. | 09-10-2015 |
20150204238 | LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE - A gas turbine engine includes a fan, a turbine having a fan drive rotor, and a speed reduction device effecting a reduction in the speed of the fan relative to an input speed from the fan drive rotor. The fan drive rotor has a number of turbine blades in at least one of a plurality of rows of the fan drive rotor, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row and the rotational speed being such that the following formula holds true for the at least one row of the fan drive turbine (the number of blades×the rotational speed)/(60 seconds/minute)>4000 Hz. The rotational speed being in revolutions per minute. A method is also disclosed. | 07-23-2015 |
20150147220 | MATERIAL OF LAVES PHASE AND FERRITIC Fe-Al PHASE - A material for components of a gas turbine, in particular a jet aircraft engine, is disclosed. The material contains an amount of a ferritic phase with Fe and Al and an amount of at least one Laves phase, where the amount of the at least one Laves phase constitutes the largest amount of the material. | 05-28-2015 |
20150071769 | METHOD FOR DISASSEMBLY AND ASSEMBLY OF A ROTOR OF A GAS TURBINE - A method for disassembly of a rotor, in particular the front rotor of a gas turbine with a housing and a channel which diverges in a direction of flow and in which the rotor is arranged, is disclosed. An embodiment of the method includes axially displacing an outer sealing ring that is radially opposite the rotor, and whose minimum inside diameter is smaller than the maximum outside diameter of the rotor, against the direction of flow. Then, the rotor is axially displaced against the direction of flow, in particular out of the housing. A method for assembly of such a rotor, as well as a tool for the same, is also disclosed. | 03-12-2015 |
20150064050 | MULTIPLE COIL ARRANGEMENT FOR A DEVICE FOR GENERATIVE PRODUCTION OF COMPONENTS AND CORRESPONDING PRODUCTION METHOD - A device for additive manufacturing of components by selective irradiation of a powder bed, having a processing chamber -in which at least one powder bed chamber and at least one radiation source are arranged such that the radiation source can irradiate a powder in the powder bed chamber, and wherein the device includes at least one induction coil, so that a component which is produced by irradiation of the powder bed can be at least partially inductively heated, and wherein the induction coil is movable relative to one or more powder bed chambers. A method for additive manufacturing of components by selective irradiation of a powder bed, in which method the component being manufactured is inductively heated at the same time, wherein the position of one or more induction coils for inductive heating is determined and adjusted based on the geometry of the component to be produced. | 03-05-2015 |
20150063986 | APPARATUS FOR ENERGY ABSORPTION, A TURBO-MACHINE AND A METHOD FOR ENERGY ABSORPTION - An apparatus for absorption of an impact energy from at least one blade fragment is disclosed. The impact energy acts on an element that is inserted into an opening in a turbo-machine. The opening passes radially through a housing section in a region of a row of rotating blades. The apparatus has a holder for holding the element in an ideal position and releasing the element beyond a preset maximum load and has a cage at a rear to secure the element in a radially outward-directed displacement. A turbo-machine having such an apparatus, as well as a method for multistage energy absorption, is also disclosed. | 03-05-2015 |
20140360664 | Method for Coating Components - A method for coating a component of a turbomachine is disclosed. The method includes covering a first surface of the component with a covering device, where the covering device is profiled in a zigzag shape. The method further includes applying a coating material via cold kinetic compaction or kinetic cold gas spraying on the component such that a second surface of the component is coated with the coating material and such that particles of the coating material are deflected off of the covering device so that the particles do not adhere to the covering device. | 12-11-2014 |
20140356644 | TiAl BLADE WITH SURFACE MODIFICATION - A component for a turbomachine having at least one region made of an intermetallic material which is formed from an intermetallic compound or comprises an intermetallic phase as the largest constituent. The intermetallic material is compacted and/or modified in microstructure by microplasticization at least partially at a surface or interface in a region close to the surface or interface. | 12-04-2014 |
20140356183 | RHENIUM-FREE OR RHENIUM-REDUCED NICKEL-BASE SUPERALLOY - A nickel-base superalloy is disclosed. The superally includes aluminium, cobalt, chromium, molybdenum, tantalum, titanium and tungsten, in addition to nickel, as alloy constituents, wherein rhenium can additionally be contained and the rhenium content is less than or equal to 2 wt. % and wherein the titanium content is greater than or equal to 1.5 wt. %. Further disclosed is a component made of the nickel-base superalloy. | 12-04-2014 |
20140348661 | BLADE ROW, BLADE AND TURBOMACHINE - A blade row for a turbomachine is disclosed. The blade row has an inner lateral wall and an outer lateral wall for bordering a hot gas channel in the turbomachine through which hot gas passes. At least one of the lateral walls has a rounded lateral wall front edge, which is provided with a circumferentially asymmetrical edge contouring that is elliptical or is comprised of one or more segments of a circle. | 11-27-2014 |
20140348660 | BLADE CASCADE AND CONTINUOUS-FLOW MACHINE - A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed. | 11-27-2014 |
20140348655 | BALANCING BODY FOR A CONTINUOUS BLADE ARRANGEMENT - The present invention relates to a balancing body ( | 11-27-2014 |
20140348633 | TURBINE STAGE WITH A BLOW-OUT ARRANGEMENT AND METHOD FOR BLOWING OUT A SEALING GAS FLOW - A turbine stage having a gas channel in which at least one rotor assembly is disposed, is disclosed. A cavity communicates with the gas channel and is delimited by a front side of a rotor element and by a rotor element-mounted seal. A blow-out arrangement with at least one gas passage for blowing out a sealing gas flow into the cavity is provided, where the gas passage for blowing out the sealing gas flow is configured with a swirl in the circumferential direction and has an outlet opening that is offset radially outwardly from the rotor element-mounted seal. | 11-27-2014 |
20140348632 | TURBOMACHINE STAGE AND METHOD FOR DETECTING A SEALING GAP OF SUCH A TURBOMACHINE STAGE - A turbomachine stage, in particular a turbine stage or compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, in particular conical, housing in which a rotor blade arrangement having a plurality of rotor blades is disposed which have an outer shroud having at least one radial sealing flange. The sealing flange has a recess arrangement having at least one radial recess in which a radial projection is disposed, in particular centrally. A sensor arrangement having at least one capacitive sensor for detecting a radial distance from a circumferential surface of the sealing flange is disposed on the housing. | 11-27-2014 |
20140348631 | TURBOMACHINE STAGE AND METHOD FOR DETERMINING A SEAL GAP AND/OR AN AXIAL POSITION OF SUCH A TURBOMACHINE STAGE - A turbomachine stage, particularly a turbine stage or a compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, conical in particular, housing in which is arranged a moving vane arrangement with multiple moving vanes which have an exterior shroud band with at least one radial sealing flange. The sealing flange has a recess arrangement with at least one radial recess in which, centrally in particular, a radial projection is arranged. There is arranged on the housing a sensor arrangement with at least one capacitive sensor for detecting a radial clearance to a peripheral surface of the sealing flange. | 11-27-2014 |
20140348449 | SPLIT INNER RING - The present invention provides a split inner ring for an adjustable guide blade arrangement, having a ring segment arrangement with at least two ring segments ( | 11-27-2014 |
20140346768 | ADAPTER AND TURBOMACHINE - An adapter for connecting a fluid line to a housing section of a turbomachine is disclosed. A lower and an upper pair of flanges are arranged offset from each other about a channel axis of a fluid channel and are arranged without a space between each other in a direction of the channel axis, where the feed-throughs of the upper pair of flanges are open circumferentially. | 11-27-2014 |
20140334924 | METHOD AND DEVICE FOR THE GENERATIVE PRODUCTION OF A COMPONENT USING A LASER BEAM AND CORRESPONDING TURBO-ENGINE COMPONENT - In a method for the generative production of a component ( | 11-13-2014 |
20140322555 | PROCESS FOR PRODUCING A HIGH-TEMPERATURE PROTECTIVE COATING AND CORRESPONDINGLY PRODUCED COMPONENT - Disclosed is a process for producing a high-temperature protective coating for metallic components, in particular components of turbomachines which are subjected to thermal loading. The process comprises producing a slip from MCrAlY powder, in which M is at least one metal, and from a Cr powder, applying the slip to the component to be coated and subsequently alitizing the component provided with the slip. | 10-30-2014 |
20140321998 | HOUSING SECTION OF A TURBINE ENGINE COMPRESSOR STAGE OR TURBINE ENGINE TURBINE STAGE - A housing section of a turbine engine compressor stage or a turbine engine turbine stage that, in particular, has a closed and annular-shaped, radially outer casing. The radially outer casing has radially inwardly extending webs that are angled at a slant relative to the radius. | 10-30-2014 |
20140321969 | SLIDE RING SEAL - A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall ( | 10-30-2014 |
20140308117 | Armoring Sealing Fins of TiAl Vanes by Induction Brazing Hard-Material Particles - A method for armoring TiAl vanes of turbomachines is disclosed. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by an inductive heating process. A TiAl vane for a turbomachine, in particular for an aircraft engine, is also disclosed. The TiAl vane includes a TiAl main part and an armor which consists of a mixture of hard materials and braze material. | 10-16-2014 |
20140301860 | AIRFOIL HAVING A PROFILED TRAILING EDGE FOR A FLUID FLOW MACHINE, BLADE, AND INTEGRALLY BLADE ROTOR - The present invention relates to an airfoil for a fluid flow machine ( | 10-09-2014 |
20140301854 | SECUREMENT SYSTEM AND METHOD FOR SECURING AN ATTACHMENT PORTION OF AT LEAST ONE ROTOR BLADE OR ROTOR BLADE SEGMENT IN A MOUNTING SITE OF A ROTOR BASE - A securement system for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base. The securement system has at least one holder element and a second holder element, each of which has a holding portion and a connecting portion. The connecting portions can be introduced into the mounting site so as to establish a clip connection and can be locked together in the mounting site. The holding portions are configured so as to fasten the attachment portion of the at least one rotor blade or of the rotor blade segment in the mounting site in the locked state of the connecting portions. Further disclosed is a method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base and a rotor having a securement system. | 10-09-2014 |
20140301853 | SECURING BLADE ASSORTMENT - A securing plate assortment including multiple different securing plates, the securing plates having different geometric codings. A turbine and method is also disclosed. | 10-09-2014 |
20140301852 | BLADE CASCADE FOR TURBO MACHINE - A blade cascade for a turbomachine, in particular a gas turbine, including multiple identical blade groups which are situated next to each other and which each include
| 10-09-2014 |
20140301840 | GUIDE VANE ARRANGEMENT - A guide vane arrangement for a turbomachine, particularly a gas turbine, is disclosed. The guide vane arrangement includes an external shroud band, on which at least two guide vanes protrude radially inward. A pair of axial ribs spaced apart from each other in the peripheral direction and disposed between two adjoining guide vanes in the peripheral direction protrude radially outward from a circumferential surface of the external shroud band and/or axially from a radial flange of the external shroud band. | 10-09-2014 |
20140298772 | MISCHVORRICHTUNG UND TURBOFANTRIEBWERK MIT EINER DERARTIGEN MISCHVORRICHTUNG - The invention relates to a mixing device and a turbofan engine having such a mixing device | 10-09-2014 |
20140294570 | TURBOMACHINE - Disclosed are a turbomachine having at least one radial gap seal which has at least two opposite ceramic coatings which are constructed in each case from a ceramic powder, the particle size of which is smaller than 1.0 μm, and a turbomachine having at least one radial gap seal, wherein the coatings are built up from powder-based individual layers, the outer layer of which has a higher ceramic fraction than a base layer close to the rotor or stator section respectively, wherein the particle size of the powder material is smaller than 1.0 μm. | 10-02-2014 |
20140255183 | TWIST PREVENTION FOR TURBOMACHINERY - A twist prevention system for turbomachinery is disclosed. The twist prevention system has a first ring segment pair with a first radially inner ring segment and a first radially outer ring segment and a second ring segment pair having a second radially inner ring segment and a second radially outer ring segment. The ring segment pairs have mutually facing faces. A portion of the face of the first radially inner ring segment overlaps a portion of the face of the second radially outer ring segment in the radial direction. | 09-11-2014 |
20140246835 | COMPONENT - A component is disclosed. The component includes a base body with a first end section and a second end section. The first end section has a first locking protrusion with a first guide surface and a first guide section with a first support surface. The second end section has a second guide section with a second guide surface and a second locking protrusion with a second support surface. The first guide surface is contactable with the second guide surface with respect to a guide plane and the first support surface is contactable with the second support surface with respect to the guide plane such that the first locking protrusion is engageable with the second locking protrusion in a locked position. | 09-04-2014 |
20140239553 | MULTI-FREQUENCY INDUCTION HEATING OF GENERATIVELY PRODUCED COMPONENTS - The invention relates to a method and device for generatively producing components, said device comprising a radiation device for selectively radiating a powder bed, and an induction device for inductively heating the component produced by radiating the powder bed, Said induction device comprising at least one voltage source which can simultaneously produce alternating voltages with at least two different frequencies. | 08-28-2014 |
20140202601 | FORGED TiAl COMPONENTS, AND METHOD FOR PRODUCING SAME - The present invention relates to a method for producing forged components of a TiAl alloy, in particular turbine blades, wherein the components are forged and undergo a two-stage heat treatment after the forging process, the first stage of the heat treatment comprising a recrystallization annealing process for 50 to 100 minutes at a temperature below the γ/α transition temperature, and the second stage of the heat treatment comprising a stabilization annealing process in the temperature range of from 800° C. to 950° C. for 5 to 7 hrs, and the cooling rate during the first heat treatment stage being greater than or equal to 3° C./sec, in the temperature range between 1300° C. to 900° C. | 07-24-2014 |
20140178201 | TURBINE BLADE HAVING A SHROUD AND A CUTTING TOOTH - A turbine blade ( | 06-26-2014 |
20140161624 | METHOD FOR PRODUCING A RUN-IN COATING, A RUN-IN SYSTEM, A TURBOMACHINE, AS WELL AS A GUIDE VANE - A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a generative manufacture of a blade. A run-in system having an abradable ring that is configured circumferentially on a blade row and has a chamber-type material structure. A turbomachine having a run-in system of this kind, as well as a guide vane having such a run-in coating. | 06-12-2014 |
20140161607 | TURBOMACHINE - The turbomachine includes a mid turbine vane frame, with an annular compartment formed between the mid turbine vane frame and a low-pressure turbine casing being sealed by means of at least two ring seals, wherein one ring seal is in contact with the mid turbine vane frame and the other ring seal is in contact with the low-pressure turbine casing and a radial annular overlap is thereby created with the first-mentioned ring seal. | 06-12-2014 |
20140161601 | METHOD FOR PRODUCING, REPAIRING AND/OR EXCHANGING A HOUSING, IN PARTICULAR AN ENGINE HOUSING, AND A CORRESPONDING HOUSING - The invention relates to a method for producing, repairing and/or exchanging a housing, in particular an engine housing of an aircraft engine, comprising at least two shells, between which a structural part is formed, wherein the method comprises the following step: layer-by-layer construction of the at least two shells jointly with the structural part by means of a generative manufacturing system, wherein the structural part comprises at least one porous structure and/or honeycomb structure. The invention relates furthermore to such a housing. | 06-12-2014 |
20140161590 | COVER DEVICE, INTEGRALLY BLADED MAIN ROTOR BODY, METHOD AND TURBOMACHINE - A covering device for an integrally bladed rotor base body of a turbomachine for preventing or reducing a cooling air stream that flows from a high-pressure side to a low-pressure side through channels that are formed between adjacent rotor blades, a plurality of cover elements being provided that are individually insertable into the channels and have at least one peripheral sealing surface. Also an integrally bladed rotor base body having a covering device of this kind, a method for producing such an integrally bladed rotor base body, as well as a turbomachine having such an integrally bladed rotor base body. | 06-12-2014 |
20140159266 | METHOD AND DEVICE FOR THE GENERATIVE PRODUCTION OF A COMPONENT - The invention relates to a method for the generative production of a component ( | 06-12-2014 |
20140119941 | CREEP-RESISTANT, RHENIUM-FREE NICKEL BASE SUPERALLOY - Disclosed is a nickel base alloy which is substantially free of rhenium and has a solidus temperature of more than 1320° C. Precipitates of a γ′-phase are present in a γ-matrix with a fraction of 40 to 50 vol % at 1050° C. to 1100° C., and a γ/γ′ mismatch at 1050° C. to 1100° C. is from −0.15% to −0.25%. The alloy comprises 11 to 13 at % aluminum, 4 to 14 at % cobalt, 6 to 12 at % chromium, 0.1 to 2 at % molybdenum, 0.1 to 3.5 at % tantalum, 0.1 to 3.5 at % titanium, 0.1 to 3 at % tungsten. The tungsten content of the γ-matrix is greater than that in the precipitated γ′-phases. | 05-01-2014 |
20140094950 | METHOD FOR THE PRODUCTION OF AN ABRADABLE SPRAY COATING - A method for producing an abradable spray coating for a component of a turbine engine by a thermal spraying process is disclosed. A process parameter p | 04-03-2014 |
20140076038 | CHECKING A BLADE CONTOUR OF A TURBOMACHINE - A method for checking a blade contour of a turbomachine, in particular a gas turbine, wherein an actual contour (1; 1′) of a blade is detected, wherein a target contour of the blade is scaled and the actual contour is compared with said scaled contour (2). | 03-20-2014 |
20140065343 | DEVICE FOR PRODUCING, REPAIRING AND/OR REPLACING A COMPONENT BY MEANS OF A POWDER THAT CAN BE SOLIDIFIED BY ENERGY RADIATION, METHOD AND COMPONENT PRODUCED ACCORDING TO SAID METHOD - The invention relates to a device for producing, repairing and/or replacing a component, particularly an aircraft component, by means of a powder that can be solidified by energy radiation of an energy radiation source, characterized in that the device comprises an application unit that is designed such that the powder can be applied onto an uneven surface by means of the application unit. | 03-06-2014 |
20140044986 | DUPLEX-PHASE CrAl COATING FOR IMPROVED CORROSION/OXIDATION PROTECTION - Disclosed is a coating for protecting a component against high temperatures and aggressive media, which coating has at least one subregion whose main constituent is chromium. The layer additionally comprises aluminum, the chromium content at least in the subregion in which chromium is the main constituent being greater than 30% by weight and the aluminum content being greater than or equal to 5% by weight. The invention further provides a process for producing such a coating, comprising chromizing the surface to be coated and subsequently alitizing the chromium-rich layer produced during chromizing. | 02-13-2014 |
20140044938 | Process for producing a COMPONENT-MATCHED PROTECTIVE LAYER and component having such a protective layer - Disclosed is process for producing a protective layer for protecting a component against high temperatures and aggressive media. The process comprises forming a surface layer comprising aluminum and chromium on a surface of the component to be provided with the protective layer by chromizing and alitizing. The chromizing and/or the alitizing in different regions of the component surface to be protected is carried out simultaneously but differently to result in a protective layer that has different regions. | 02-13-2014 |
20140044551 | BLADE CASCADE WITH SIDE WALL CONTOURS AND CONTINUOUS-FLOW MACHINE - A blade cascade for a continuous-flow machine having a non-axisymmetrical side wall contour, whereby the side wall contour has at least one pressure-side elevation and one suction-side depression, whose highest section and lowest section are located over an area 30% to 60% of an extension of the blades in the axial direction, and the axial positions of the outermost sections differ from each other at the maximum by 10% in the axial direction. | 02-13-2014 |
20140044550 | Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine - A restraint mechanism for rotor blades of a turbo engine on a rotor disk having blade root receptacles for radial guidance of the rotor blades is disclosed. The restraint mechanism has a plurality of axial securing elements, each having at least one web for positioning in a blade root receptacle, such that each web has a retaining section at one end for establishing a form-fitting design to a mating brace of another axial securing element. A method for axially securing rotor blades on a rotor disk and a turbo engine are also disclosed. | 02-13-2014 |
20140044549 | DUCTILE COMPENSATION LAYER FOR BRITTLE COMPONENTS - Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element ( | 02-13-2014 |
20140044546 | BLADED ROTOR FOR A TURBOMACHINE - A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2). | 02-13-2014 |
20140044537 | GAS TURBINE - A gas turbine stage, in particular a low-pressure compressor stage, for a gas turbine, in particular an aircraft engine gas turbine having a guide vane assembly having at least one guide vane ( | 02-13-2014 |
20140044532 | PROCESS FOR PRODUCING A TiAl GUIDE VANE RING FOR A GAS TURBINE AND A CORRESPONDING GUIDE VANE RING - Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising:
| 02-13-2014 |
20140044526 | STATIONARY BLADE RING, ASSEMBLY METHOD AND TURBOMACHINE - Disclosed is an adjustable stationary blade ring of a turbomachine, whose stationary blades are each supported in a bearing body onto which an inner ring, which is divided into two half rings and acts as a seal carrier, is pushed without deformation, viewed in the circumferential direction, as well as a method for assembling a stationary blade ring of this type and a turbomachine having a stationary blade ring of this type. | 02-13-2014 |
20130343947 | METHOD AND DEVICE FOR PROCESS MONITORING - Disclosed is a method for monitoring a generative production process in real time, wherein a component is at least optically detected and the installation space is thermally detected when applying a layer, as well as a device for carrying out said method. | 12-26-2013 |
20130287590 | GENERATIVELY PRODUCED TURBINE BLADE AND DEVICE AND METHOD FOR PRODUCING SAME - The present invention relates to a method for producing gas turbine components, in particular aircraft turbine components, preferably low-pressure turbine blades, from a powder which is sintered selectively in layers by locally limited introduction of radiant energy, wherein the sintering is carried out in a closed first housing ( | 10-31-2013 |
20130280439 | METHOD FOR THE LAYERED MANUFACTURING OF A STRUCTURAL COMPONENT AND DEVICE - The invention relates to a method for the layered manufacturing of a structural component from powder, comprising the following steps: establishing at least one parameter (t) of a depression ( | 10-24-2013 |