| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 416213000 | Welded, cemented or fused | 46 |
| 20080206059 | Method Of Manufacturing A Wind Turbine Blade Shell Member With A Fastening Member And A Wind Turbine Blade With A Fastening Member - A method of manufacturing a wind turbine blade shell member ( | 08-28-2008 |
| 20090028711 | METHOD FOR THE INDUCTIVE HIGH-FREQUENCY PRESSURE WELDING OF METALLIC STRUCTURAL ELEMENTS USING AT LEAST TWO DIFFERENT FREQUENCIES AND COMPONENT PRODUCED BY SAID METHOD - The present technology relates to a method for connecting metallic structural components, especially structural components of a gas turbine, wherein the connection of corresponding connecting surfaces of the construction elements occurs by means of an inductive high-frequency pressure welding with heating of at least one connecting surface. According to the present technology, at least two different frequencies induced by at least one inductor are used for heating the at least one connecting surface. The present technology also relates to a component, especially a component of a gas turbine consisting of a first structural element and a second structural element, whereby the first and the second structural elements are welded by means of inductive high-frequency pressure welding. According to the present technology, at least two different frequencies induced by at least one inductor are used for heating at least one connecting surface of the structural elements. | 01-29-2009 |
| 20090068016 | SHROUDED SINGLE CRYSTAL DUAL ALLOY TURBINE DISK - A turbine engine component for a gas turbine engine includes an inner disk, an outer shroud, and a plurality of blades. Each blade comprises a blade root and an airfoil body. The blade root is plated at least in part with a noble metal, and is coupled to the inner disk. The airfoil body extends at least partially between the blade root and the outer shroud. | 03-12-2009 |
| 20090185908 | LINEAR FRICTION WELDED BLISK AND METHOD OF FABRICATION - The present invention provides a linear friction welded blisk of a gas turbine engine and method of fabricating the blisk. The blisk includes a blisk hub having a curved periphery and having a central axis formed therethrough. At least one blade joining stub including a planar weld joint surface to which at least one airfoil blade may be welded by linear friction welding is formed about the periphery of the blisk hub. The planar weld joint surface is formed in a plane parallel to the central axis of the blisk hub thereby providing for linear friction welding of the airfoil blade to the planar weld joint surface in a tangential, chordal, or axial direction. The planar weld joint surface reduces the complexity of the linear friction welding machines and tooling, and further provides for an increase in blade count and leading edge accessibility. | 07-23-2009 |
| 20090290985 | PROCESS FOR CONNECTING METALLIC STRUCTURAL ELEMENTS AND COMPONENTS PRODUCED THEREBY - A process for connecting metallic structural elements, in particular structural elements of a gas turbine, and a component made by the process, is disclosed. The connecting of corresponding connecting surfaces of the structural elements is performed by inductive high-frequency pressure welding and the structural elements consist of different or similar metallic materials with different permeabilities and/or thermal conductivities. During the inductive high-frequency pressure welding, at least one process-specific parameter is controlled in such a way that at least the connecting surfaces are respectively heated essentially simultaneously up to at least near the respective melting point of the metallic materials. | 11-26-2009 |
| 20090304514 | Method of manufacturing a turbine rotor - A method for joining a cast metal material blade ring having therein an initial interior ring passageway formed by a ring interior wall thereabout and a metal material hub structure, having therein a disk part thereof with a disk side configured such that at least a portion of a disk side is positionable against a portion of the ring interior wall so as to be assembleable into an assembled structure for a turbine rotor through mounting one of the blade ring and the hub structure in a holder and also mounting the remaining one of the blade ring and the hub structure in a rotation holder for being rotated by a rotatable portion of that rotation holder. These mountings are followed by pressing at least the portion of the ring interior wall of the blade ring and the portion of the disk side of the hub structure disk part together with a selected force while the rotatable portion of the rotation holder is rotating for a sufficient time to friction weld together the ring interior wall and the disk side to thereby form the assembled structure. | 12-10-2009 |
| 20090304515 | METHOD AND DEVICE FOR JOINING BY WAY OF INDUCTIVE HF PRESSURE WELDING A ROTOR BLADE WITH A ROTOR SUPPORT OF A GAS TURBINE WITH AUTOMATIC SUPPLY OF THE ROTOR BLADE - A method and a device for joining at least one rotor blade or at least one part of a rotor blade with a rotor support of a gas turbine, in particular a rotor blade connection of the rotor support, is disclosed. Corresponding connecting surfaces of the rotor blade, the rotor blade part, the rotor support or the rotor blade connection of the rotor support are joined by inductive high-frequency pressure welding. In this case, at least one rotor blade or rotor blade part is automatically supplied from at least one rotor blade reservoir and/or rotor blade part reservoir and, in addition, the rotor support is automatically positioned in such a way that the connecting surfaces to be joined are positioned precisely with respect to one another for the joining process. | 12-10-2009 |
| 20100008781 | Method and Apparatus for Creating Seal Slots for Turbine Components - A sealing slot system for a turbine dovetail. The sealing slot system may include a dovetail tab with a first leg and a second leg, an insert positioned between the first leg and the second leg so as to define a sealing slot, and a pin extending through the dovetail tab and the slot insert. | 01-14-2010 |
| 20100040473 | TURBOCHARGER - The invention relates to an exhaust gas turbocharger ( | 02-18-2010 |
| 20100098546 | Gas turbine engine centrifugal impeller - In one embodiment a centrifugal impeller has an axis of rotation, a plurality of blades, and a plurality of pitches defined between the blades. A cavity may be formed in a back side of the impeller, opposite with at least one of the plurality of pitches. In one form the cavity may not extend below a radius determined according to a stress criteria or stress limitation. | 04-22-2010 |
| 20100158690 | One-Piece Bladed Drum of an Axial Turbomachine Compressor - A compressor drum for an axial turbo-machine includes a hollow body generally symmetrical in revolution about its axis of rotation and forming a shell at the periphery of which are arranged a plurality of parallel rows of vanes, each row corresponding to one stage of the compressor. Each vane includes at its root an attachment platform housed in a corresponding opening made in the shell of the hollow body. The outer surface of each platform is flush with the outer surface of the shell at the edge of the opening and each platform is attached to the hollow body by welding between the outer edge of the platform and the inner edge of the corresponding opening. The platform has the general shape of a parallelogram, a bisector of which corresponds approximately to the main axis of the profile of the vane at the platform. | 06-24-2010 |
| 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 |
| 20110064581 | Connection of a Shaft to a Rotating Component - For connecting a shaft to a rotating component, especially of a shaft to a turbine wheel of an exhaust gas turbocharger, an intermediate component is provided by means of which the shaft is connected indirectly to the rotating component. The connection between the rotating component and the intermediate component is a form-locking and/or force-locking connection, especially a riveted connection. The invention further relates to a method for producing said connection. | 03-17-2011 |
| 20110123340 | FAN BLADE STRUCTURE - A fan blade structure includes a case, a rotor and a fan blade unit. The case has a top portion and a sidewall portion connected to an outer periphery of the top portion to thereby define a receiving space therein. The rotor is mounted in the receiving space to contact with an inner wall surface of the sidewall portion in a tight-fit relation. The fan blade unit is formed by stamping a metal material, and includes an annular top face bearing on the top portion of the case, and a plurality of blades equally spaced along the annular top face. The annular top face defines a large-area central opening, which effectively reduces an overall weight of the fan blade unit and thereby lowers the load of the rotor and allows a fan motor in operation to reach its high limit of rotary speed and enable an upgraded fan rotating speed. | 05-26-2011 |
| 20110150656 | BLADE ASSEMBLY WITH IMPROVED JOINT STRENGTH - A blade assembly for a torque converter including a shell with an inner surface and a plurality of blades attached to the shell by brazing. Each blade has a first surface for guiding a fluid in the torque converter and a second surface substantially parallel to the inner surface. The blades may include sheet steel and may be made by stamping. In an example embodiment of the invention, each blade includes at least one tab, the shell comprises a plurality of slots or indents, and the at least one tab is disposed in a respective slot or indent. The shell may be an outer shell or a core ring for a pump or turbine for the torque converter. | 06-23-2011 |
| 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 |
| 20110206523 | WELDING PROCESS AND COMPONENT FORMED THEREBY - A process of fabricating a rotating component and a rotating component formed thereby. The rotating component has a rotational axis, at least one rim member, at least one disk member, and at least one airfoil member. The rim and disk members are welded together to define a first solid-state weld joint lying in a first plane that is not parallel to the rotational axis of the rotating component. The airfoil member is welded to the rim member to define a second solid-state weld joint lying in a second plane that is not parallel to the rotational axis of the rotating component. The rim member is located in a radially outward direction from the disk member, and the airfoil member is located in a radially outward direction from the rim member. | 08-25-2011 |
| 20110255981 | METHOD FOR THE PRODUCTION OF AN INTEGRALLY BLADED ROTOR, AND ROTOR - A method for manufacturing an integrally bladed rotor ( | 10-20-2011 |
| 20110262277 | GAS TURBINE COMPOSITE WORKPIECE TO BE USED IN GAS TURBINE ENGINE - A gas turbine composite workpiece, such as a workpiece forming a part of a gas turbine casing, is provided. The workpiece includes at least two components joined by at least one weld seam. In order to reduce thermal stresses of the workpiece during operation, the weld seam is interrupted by at least one aperture. In order to reduce the exchange of gases between the workpiece's sides, the workpiece may be equipped with an arrangement for preventing gas flow through the aperture. | 10-27-2011 |
| 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 |
| 20120099998 | SUPPORT COLLAR GEOMETRY FOR LINEAR FRICTION WELDING - An example method of attaching an airfoil for an integrally bladed rotor includes placing a support collar in an installed position around at least a leading edge and trailing edge of an airfoil stub to be repaired in an integrally bladed rotor. The support collar and the airfoil stub together have a midline that is positioned between opposing, laterally outer surfaces of the airfoil stub when the support collar is in the installed position. The method performs linear friction welding to add a replacement airfoil to the airfoil stub. | 04-26-2012 |
| 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 |
| 20120156044 | BI-CAST TURBINE ROTOR DISKS AND METHODS OF FORMING SAME - A bi-cast turbine rotor disk and method of forming the same are provided. The disk includes a ring and a blade. The ring comprises a superalloy that includes a plurality of elements, and the blade extends from the ring. The blade comprises a non-metallic ceramic matrix composite, and at least one element from the superalloy of the ring is diffused into the non-metallic ceramic matrix composite of the blade. | 06-21-2012 |
| 20120183404 | METHOD FOR INTEGRALLY CONNECTING BLADES AND DISKS IN ORDER TO FORM A BLADE-DISK UNIT, AS WELL AS CORRESPONDINGLY PRODUCED BLADE-DISK UNIT - A blade-disk unit for a turbine engine includes a disk and a plurality of blades which are integrally connected to the disk, a welding seam being disposed in the joining region between the blade and the disk, which welding seam is situated entirely either in the blade or in the disk. | 07-19-2012 |
| 20120201684 | MATE FACE BRAZING FOR TURBINE COMPONENTS - A turbine component is formed of at least a plurality of adjacent turbine subcomponents. Each turbine component has a mate face secured to the mate face of an opposed turbine subcomponent. A wedge member is positioned between the mate faces of the turbine subcomponents, and a braze material between outer faces of the wedge and the mate faces of each of the turbine subcomponents. | 08-09-2012 |
| 20120301307 | Friction Welding of Titanium Aluminide Turbine to Titanium Alloy Shaft - A frictional welding process for joining a titanium aluminide turbine to a titanium alloy shaft is disclosed. The disclosed process includes preheating the turbine to a designated temperature, providing a specially-designed joining interface geometry at the distal end of the shaft and optimizing the frictional welding parameters. The frictional welding is carried out in multiple steps but, while the shaft is being spun by a rotating chuck, two different pressures and two different time periods are used until the narrower portions of the distal end of the shaft have been fused onto the welding surface of the turbine. Then, an additional forging step with yet another engagement pressure between the shaft and the turbine is carried out without rotation of the shaft. | 11-29-2012 |
| 20130089427 | Method for Welding Metallic Blades - A rotating device comprising a blade ( | 04-11-2013 |
| 20130115089 | ROTATABLE COMPONENT WITH CONTROLLED LOAD INTERFACE - A rotatable component includes a first section and a second section that is located radially outwards of the first section with regard to an axis of rotation about which the sections are co-rotatable. These sections are attached together at a bonded interface. At a perimeter region of the bonded interface a perimeter portion of the first section has a first stiffness and a perimeter portion of the second section has a second stiffness that is greater than the first stiffness. | 05-09-2013 |
| 20130156586 | METHOD FOR CONNECTING A TURBINE BLADE OR VANE TO A TURBINE DISC OR A TURBINE RING - The present invention provides a method for connecting a turbine blade or vane to a turbine disk or to a turbine ring. First, a connecting body is formed on the turbine blade or vane by supplying an additive suitable for fusion welding to a surface of the turbine blade or vane, melting the additive on the surface, with incipient melting of the surface, and allowing the additive and the surface to solidify. Then, the connecting body is connected to the turbine disk or to the turbine ring by means of a fusion welding process. | 06-20-2013 |
| 20130209261 | Assembly of a Blade and a Composite Carrier, Obtained by Sealing - The invention relates to a mechanical assembly ( | 08-15-2013 |
| 20140064975 | IMPELLER AND ROTARY MACHINE PROVIDED WITH THE SAME - The present invention is related to an impeller and a rotary machine including an inner diameter portion, a disk portion, a blade portion, and a cover portion. The disk portion includes a main body portion provided the blade portion, and a fixing portion disposed at an inner side in a radial direction of the rotor than the main body portion and fitted at the outside of an outer peripheral surface of the inner diameter portion. The fixing portion is formed so as to protrude toward the other side in the axial direction from the main body portion. | 03-06-2014 |
| 20140241890 | GAS TURBINE ENGINE BLADE AND DISK - In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface. | 08-28-2014 |
| 20150037160 | TURBINE ROTOR - To provide a turbine rotor which enables mass production with a low-cost apparatus and which capable of suppressing leaning of the rotor shaft after welding to improve the yield, while a turbine blade rotor | 02-05-2015 |
| 20150044053 | Steam Turbine Rotor - It is an objective of the invention to provide a steam turbine rotor that is capable of both reducing SCC susceptibility and improving LCF life thereof. There is provided a steam turbine rotor, comprising a rotor disk in a low pressure final stage L-0, and another rotor disk in a plurality of stages including a stage L-1 positioned closer to a high pressure side than the low pressure final stage L-0, the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 being joined by welding, wherein a material of both the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 is a 12Cr steel and has a tensile strength of 900 to 1200 MPa. | 02-12-2015 |
| 20150078904 | REPAIRED TURBINE ROTOR WHEEL DOVETAIL AND RELATED METHOD - A method of repairing a damaged dovetail on a peripheral portion of a turbine wheel includes the steps of removing buckets from the dovetail; removing a damaged dovetail from the peripheral portion of the turbine wheel, leaving a rotor wheel body having a peripheral rim; disposing a replacement ring about the peripheral rim, the replacement ring and the rim defining therebetween a pair of end grooves and a center section; and welding the replacement ring to the peripheral rim, with weld material applied only within the end grooves, leaving a void in the center section. | 03-19-2015 |
| 20150078905 | TURBINE ROTOR FOR AN EXHAUST GAS TURBINE AND METHOD FOR PRODUCING THE TURBINE ROTOR - A turbine rotor for an exhaust gas turbine has a turbine rotor wheel made of a highly heat-resistant metal alloy and a rotor shaft made of steel. A rotor wheel hub and a rotor shaft end are connected to each other in a metallurgical bond by way of a solder connection. The rotor shaft end and/or the rotor wheel hub is formed with a central recess, which acts as a thermal choke. A closing plug is arranged in the respective recess, forming a closed cavity with the recess and closing off the recess toward the respective end face. The solder connection is formed between the end faces of the rotor wheel hub and the rotor shaft, between the closing plug and the rotor wheel hub, and between the closing plug and the rotor shaft. | 03-19-2015 |
| 20150104318 | TURBINE ROTOR FOR AN EXHAUST-GAS TURBINE AND METHOD FOR PRODUCING THE TURBINE ROTOR - A turbine rotor as a turbine impeller made of a high-temperature-resistant metal alloy and a rotor shaft made of steel. The impeller hub and the rotor shaft end are connected together in a metallurgically bonded manner by way of a brazed connection. Between the end faces of the impeller hub and of the rotor shaft end, a brazing gap filled with brazing alloy is arranged concentrically with the rotation axis of the turbine rotor. A width of the soldering gap is previously determined by circularly peripheral removal of material on the end face of the impeller hub or the end face of the rotor shaft end, and the brazing connection is produced by an electron beam soldering process. | 04-16-2015 |
| 20150139810 | NOISE REDUCING EXTENSION PLATE FOR ROTOR BLADE IN WIND TURBINE - Rotor blade assemblies and methods for constructing rotor blade assemblies are provided. A rotor blade assembly may include a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge and a trailing edge each extending between a tip and a root, the rotor blade defining a span and a chord. The rotor blade assembly further includes an extension plate mounted to one of the pressure side or the suction side, the extension plate extending in the chord-wise direction between a first end and a second end, the second end extending beyond the trailing edge. The rotor blade assembly further includes a filler substrate provided on an inner surface of the extension plate and the trailing edge, the filler substrate tapering from the trailing edge towards the second end. | 05-21-2015 |
| 20150300182 | METHOD FOR FRICTION WELDING A BLADE ONTO A TURBINE ENGINE ROTOR DISC; CORRESPONDING INTEGRAL BLADE DISC - A method of friction welding an airfoil ( | 10-22-2015 |
| 20150354379 | DUAL ALLOY TURBINE ROTORS AND METHODS FOR MANUFACTURING THE SAME - Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step. | 12-10-2015 |
| 20160115794 | COMPOSITE ANNULUS FILLER - A composite annulus filler adapted to bridge the gap between two adjacent rotor blades attached to a rim of a rotor disc of a gas turbine engine. The annulus filler includes a unitary body portion having a platform which extends between the adjacent rotor blades and defines an airflow surface for air being drawn through the engine and a support body extending beneath the platform and terminating in a root which, in use, extends along a groove provided in the rim of the rotor disc. | 04-28-2016 |
| 20160146023 | Rotor With Blades Secured by Woven Fiber Attachment System - A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor. | 05-26-2016 |
| 20170234322 | Arrangement of an Impeller Wheel on an Electric Motor and Method for Producing the Same | 08-17-2017 |
| 20090047133 | IMPELLER BLADE FOR CENTRIFUGAL BLOWER, BLADE-SUPPORTING ROTATOR, IMPELLER FOR CENTRIFUGAL BLOWER, AND METHOD FOR MANUFACTURING IMPELLER FOR CENTRIFUGAL BLOWER - Blades of an impeller for a centrifugal blower are resinous hollow blades having hollow spaces formed in the blade interiors, and having first blade weld parts welded to plate weld surfaces of an end plate, wherein first blade weld surfaces inclined with respect to the plate weld surfaces are formed on the first blade weld parts in a state in which the first blade weld parts are disposed to face the plate weld surfaces in the axial direction. | 02-19-2009 |
| 20100158689 | CROSS-FLOW FAN MADE OF RESIN AND METHOD OF MANUFACTURING THE SAME - A resin cross flow fan and a method for manufacturing a resin cross flow fan are provided in which an annealing step can be omitted and the number of circular disks can be reduced, and which provides improved fan strength and air blowing performance. A resin cross flow fan is disposed with a plurality of blades and a plurality of plates. The plurality of blades are annually disposed about a rotation axis. Insertion portions each constituted by a hole or a groove into which each blade is inserted and projecting portions that projects from the periphery of the insertion portions in a direction of the rotation axis are formed on each of the plurality of plates disposed spaced apart in the direction of the rotation axis. Each blade is fixed to the projecting portions by laser welding. | 06-24-2010 |
| 20140154086 | FRONT FAN RETENTION IN DUAL INTERNAL FAN ALTERNATOR - An alternator has a pole segment with a collar, an axially outward surface, and at least one key extending radially outward from the collar along the surface. A fan has a keying slot extending radially outward from a center ring, and a fan body including protrusions. The fan is mounted to the segment whereby the collar fits inside the ring and the key fits inside the keying slot, and the fan is welded to the segment at the protrusions. A method includes securing a fan to a pole segment by mating a radially-extending key formed on the segment to a keying slot of the fan and by welding the fan to the segment. | 06-05-2014 |
| 416213000 | Non-turbo machine | 3 |
| 20080206059 | Method Of Manufacturing A Wind Turbine Blade Shell Member With A Fastening Member And A Wind Turbine Blade With A Fastening Member - A method of manufacturing a wind turbine blade shell member ( | 08-28-2008 |
| 20090028711 | METHOD FOR THE INDUCTIVE HIGH-FREQUENCY PRESSURE WELDING OF METALLIC STRUCTURAL ELEMENTS USING AT LEAST TWO DIFFERENT FREQUENCIES AND COMPONENT PRODUCED BY SAID METHOD - The present technology relates to a method for connecting metallic structural components, especially structural components of a gas turbine, wherein the connection of corresponding connecting surfaces of the construction elements occurs by means of an inductive high-frequency pressure welding with heating of at least one connecting surface. According to the present technology, at least two different frequencies induced by at least one inductor are used for heating the at least one connecting surface. The present technology also relates to a component, especially a component of a gas turbine consisting of a first structural element and a second structural element, whereby the first and the second structural elements are welded by means of inductive high-frequency pressure welding. According to the present technology, at least two different frequencies induced by at least one inductor are used for heating at least one connecting surface of the structural elements. | 01-29-2009 |
| 20090068016 | SHROUDED SINGLE CRYSTAL DUAL ALLOY TURBINE DISK - A turbine engine component for a gas turbine engine includes an inner disk, an outer shroud, and a plurality of blades. Each blade comprises a blade root and an airfoil body. The blade root is plated at least in part with a noble metal, and is coupled to the inner disk. The airfoil body extends at least partially between the blade root and the outer shroud. | 03-12-2009 |
| 20090185908 | LINEAR FRICTION WELDED BLISK AND METHOD OF FABRICATION - The present invention provides a linear friction welded blisk of a gas turbine engine and method of fabricating the blisk. The blisk includes a blisk hub having a curved periphery and having a central axis formed therethrough. At least one blade joining stub including a planar weld joint surface to which at least one airfoil blade may be welded by linear friction welding is formed about the periphery of the blisk hub. The planar weld joint surface is formed in a plane parallel to the central axis of the blisk hub thereby providing for linear friction welding of the airfoil blade to the planar weld joint surface in a tangential, chordal, or axial direction. The planar weld joint surface reduces the complexity of the linear friction welding machines and tooling, and further provides for an increase in blade count and leading edge accessibility. | 07-23-2009 |
| 20090290985 | PROCESS FOR CONNECTING METALLIC STRUCTURAL ELEMENTS AND COMPONENTS PRODUCED THEREBY - A process for connecting metallic structural elements, in particular structural elements of a gas turbine, and a component made by the process, is disclosed. The connecting of corresponding connecting surfaces of the structural elements is performed by inductive high-frequency pressure welding and the structural elements consist of different or similar metallic materials with different permeabilities and/or thermal conductivities. During the inductive high-frequency pressure welding, at least one process-specific parameter is controlled in such a way that at least the connecting surfaces are respectively heated essentially simultaneously up to at least near the respective melting point of the metallic materials. | 11-26-2009 |
| 20090304514 | Method of manufacturing a turbine rotor - A method for joining a cast metal material blade ring having therein an initial interior ring passageway formed by a ring interior wall thereabout and a metal material hub structure, having therein a disk part thereof with a disk side configured such that at least a portion of a disk side is positionable against a portion of the ring interior wall so as to be assembleable into an assembled structure for a turbine rotor through mounting one of the blade ring and the hub structure in a holder and also mounting the remaining one of the blade ring and the hub structure in a rotation holder for being rotated by a rotatable portion of that rotation holder. These mountings are followed by pressing at least the portion of the ring interior wall of the blade ring and the portion of the disk side of the hub structure disk part together with a selected force while the rotatable portion of the rotation holder is rotating for a sufficient time to friction weld together the ring interior wall and the disk side to thereby form the assembled structure. | 12-10-2009 |
| 20090304515 | METHOD AND DEVICE FOR JOINING BY WAY OF INDUCTIVE HF PRESSURE WELDING A ROTOR BLADE WITH A ROTOR SUPPORT OF A GAS TURBINE WITH AUTOMATIC SUPPLY OF THE ROTOR BLADE - A method and a device for joining at least one rotor blade or at least one part of a rotor blade with a rotor support of a gas turbine, in particular a rotor blade connection of the rotor support, is disclosed. Corresponding connecting surfaces of the rotor blade, the rotor blade part, the rotor support or the rotor blade connection of the rotor support are joined by inductive high-frequency pressure welding. In this case, at least one rotor blade or rotor blade part is automatically supplied from at least one rotor blade reservoir and/or rotor blade part reservoir and, in addition, the rotor support is automatically positioned in such a way that the connecting surfaces to be joined are positioned precisely with respect to one another for the joining process. | 12-10-2009 |
| 20100008781 | Method and Apparatus for Creating Seal Slots for Turbine Components - A sealing slot system for a turbine dovetail. The sealing slot system may include a dovetail tab with a first leg and a second leg, an insert positioned between the first leg and the second leg so as to define a sealing slot, and a pin extending through the dovetail tab and the slot insert. | 01-14-2010 |
| 20100040473 | TURBOCHARGER - The invention relates to an exhaust gas turbocharger ( | 02-18-2010 |
| 20100098546 | Gas turbine engine centrifugal impeller - In one embodiment a centrifugal impeller has an axis of rotation, a plurality of blades, and a plurality of pitches defined between the blades. A cavity may be formed in a back side of the impeller, opposite with at least one of the plurality of pitches. In one form the cavity may not extend below a radius determined according to a stress criteria or stress limitation. | 04-22-2010 |
| 20100158690 | One-Piece Bladed Drum of an Axial Turbomachine Compressor - A compressor drum for an axial turbo-machine includes a hollow body generally symmetrical in revolution about its axis of rotation and forming a shell at the periphery of which are arranged a plurality of parallel rows of vanes, each row corresponding to one stage of the compressor. Each vane includes at its root an attachment platform housed in a corresponding opening made in the shell of the hollow body. The outer surface of each platform is flush with the outer surface of the shell at the edge of the opening and each platform is attached to the hollow body by welding between the outer edge of the platform and the inner edge of the corresponding opening. The platform has the general shape of a parallelogram, a bisector of which corresponds approximately to the main axis of the profile of the vane at the platform. | 06-24-2010 |
| 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 |
| 20110064581 | Connection of a Shaft to a Rotating Component - For connecting a shaft to a rotating component, especially of a shaft to a turbine wheel of an exhaust gas turbocharger, an intermediate component is provided by means of which the shaft is connected indirectly to the rotating component. The connection between the rotating component and the intermediate component is a form-locking and/or force-locking connection, especially a riveted connection. The invention further relates to a method for producing said connection. | 03-17-2011 |
| 20110123340 | FAN BLADE STRUCTURE - A fan blade structure includes a case, a rotor and a fan blade unit. The case has a top portion and a sidewall portion connected to an outer periphery of the top portion to thereby define a receiving space therein. The rotor is mounted in the receiving space to contact with an inner wall surface of the sidewall portion in a tight-fit relation. The fan blade unit is formed by stamping a metal material, and includes an annular top face bearing on the top portion of the case, and a plurality of blades equally spaced along the annular top face. The annular top face defines a large-area central opening, which effectively reduces an overall weight of the fan blade unit and thereby lowers the load of the rotor and allows a fan motor in operation to reach its high limit of rotary speed and enable an upgraded fan rotating speed. | 05-26-2011 |
| 20110150656 | BLADE ASSEMBLY WITH IMPROVED JOINT STRENGTH - A blade assembly for a torque converter including a shell with an inner surface and a plurality of blades attached to the shell by brazing. Each blade has a first surface for guiding a fluid in the torque converter and a second surface substantially parallel to the inner surface. The blades may include sheet steel and may be made by stamping. In an example embodiment of the invention, each blade includes at least one tab, the shell comprises a plurality of slots or indents, and the at least one tab is disposed in a respective slot or indent. The shell may be an outer shell or a core ring for a pump or turbine for the torque converter. | 06-23-2011 |
| 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 |
| 20110206523 | WELDING PROCESS AND COMPONENT FORMED THEREBY - A process of fabricating a rotating component and a rotating component formed thereby. The rotating component has a rotational axis, at least one rim member, at least one disk member, and at least one airfoil member. The rim and disk members are welded together to define a first solid-state weld joint lying in a first plane that is not parallel to the rotational axis of the rotating component. The airfoil member is welded to the rim member to define a second solid-state weld joint lying in a second plane that is not parallel to the rotational axis of the rotating component. The rim member is located in a radially outward direction from the disk member, and the airfoil member is located in a radially outward direction from the rim member. | 08-25-2011 |
| 20110255981 | METHOD FOR THE PRODUCTION OF AN INTEGRALLY BLADED ROTOR, AND ROTOR - A method for manufacturing an integrally bladed rotor ( | 10-20-2011 |
| 20110262277 | GAS TURBINE COMPOSITE WORKPIECE TO BE USED IN GAS TURBINE ENGINE - A gas turbine composite workpiece, such as a workpiece forming a part of a gas turbine casing, is provided. The workpiece includes at least two components joined by at least one weld seam. In order to reduce thermal stresses of the workpiece during operation, the weld seam is interrupted by at least one aperture. In order to reduce the exchange of gases between the workpiece's sides, the workpiece may be equipped with an arrangement for preventing gas flow through the aperture. | 10-27-2011 |
| 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 |
| 20120099998 | SUPPORT COLLAR GEOMETRY FOR LINEAR FRICTION WELDING - An example method of attaching an airfoil for an integrally bladed rotor includes placing a support collar in an installed position around at least a leading edge and trailing edge of an airfoil stub to be repaired in an integrally bladed rotor. The support collar and the airfoil stub together have a midline that is positioned between opposing, laterally outer surfaces of the airfoil stub when the support collar is in the installed position. The method performs linear friction welding to add a replacement airfoil to the airfoil stub. | 04-26-2012 |
| 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 |
| 20120156044 | BI-CAST TURBINE ROTOR DISKS AND METHODS OF FORMING SAME - A bi-cast turbine rotor disk and method of forming the same are provided. The disk includes a ring and a blade. The ring comprises a superalloy that includes a plurality of elements, and the blade extends from the ring. The blade comprises a non-metallic ceramic matrix composite, and at least one element from the superalloy of the ring is diffused into the non-metallic ceramic matrix composite of the blade. | 06-21-2012 |
| 20120183404 | METHOD FOR INTEGRALLY CONNECTING BLADES AND DISKS IN ORDER TO FORM A BLADE-DISK UNIT, AS WELL AS CORRESPONDINGLY PRODUCED BLADE-DISK UNIT - A blade-disk unit for a turbine engine includes a disk and a plurality of blades which are integrally connected to the disk, a welding seam being disposed in the joining region between the blade and the disk, which welding seam is situated entirely either in the blade or in the disk. | 07-19-2012 |
| 20120201684 | MATE FACE BRAZING FOR TURBINE COMPONENTS - A turbine component is formed of at least a plurality of adjacent turbine subcomponents. Each turbine component has a mate face secured to the mate face of an opposed turbine subcomponent. A wedge member is positioned between the mate faces of the turbine subcomponents, and a braze material between outer faces of the wedge and the mate faces of each of the turbine subcomponents. | 08-09-2012 |
| 20120301307 | Friction Welding of Titanium Aluminide Turbine to Titanium Alloy Shaft - A frictional welding process for joining a titanium aluminide turbine to a titanium alloy shaft is disclosed. The disclosed process includes preheating the turbine to a designated temperature, providing a specially-designed joining interface geometry at the distal end of the shaft and optimizing the frictional welding parameters. The frictional welding is carried out in multiple steps but, while the shaft is being spun by a rotating chuck, two different pressures and two different time periods are used until the narrower portions of the distal end of the shaft have been fused onto the welding surface of the turbine. Then, an additional forging step with yet another engagement pressure between the shaft and the turbine is carried out without rotation of the shaft. | 11-29-2012 |
| 20130089427 | Method for Welding Metallic Blades - A rotating device comprising a blade ( | 04-11-2013 |
| 20130115089 | ROTATABLE COMPONENT WITH CONTROLLED LOAD INTERFACE - A rotatable component includes a first section and a second section that is located radially outwards of the first section with regard to an axis of rotation about which the sections are co-rotatable. These sections are attached together at a bonded interface. At a perimeter region of the bonded interface a perimeter portion of the first section has a first stiffness and a perimeter portion of the second section has a second stiffness that is greater than the first stiffness. | 05-09-2013 |
| 20130156586 | METHOD FOR CONNECTING A TURBINE BLADE OR VANE TO A TURBINE DISC OR A TURBINE RING - The present invention provides a method for connecting a turbine blade or vane to a turbine disk or to a turbine ring. First, a connecting body is formed on the turbine blade or vane by supplying an additive suitable for fusion welding to a surface of the turbine blade or vane, melting the additive on the surface, with incipient melting of the surface, and allowing the additive and the surface to solidify. Then, the connecting body is connected to the turbine disk or to the turbine ring by means of a fusion welding process. | 06-20-2013 |
| 20130209261 | Assembly of a Blade and a Composite Carrier, Obtained by Sealing - The invention relates to a mechanical assembly ( | 08-15-2013 |
| 20140064975 | IMPELLER AND ROTARY MACHINE PROVIDED WITH THE SAME - The present invention is related to an impeller and a rotary machine including an inner diameter portion, a disk portion, a blade portion, and a cover portion. The disk portion includes a main body portion provided the blade portion, and a fixing portion disposed at an inner side in a radial direction of the rotor than the main body portion and fitted at the outside of an outer peripheral surface of the inner diameter portion. The fixing portion is formed so as to protrude toward the other side in the axial direction from the main body portion. | 03-06-2014 |
| 20140241890 | GAS TURBINE ENGINE BLADE AND DISK - In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface. | 08-28-2014 |
| 20150037160 | TURBINE ROTOR - To provide a turbine rotor which enables mass production with a low-cost apparatus and which capable of suppressing leaning of the rotor shaft after welding to improve the yield, while a turbine blade rotor | 02-05-2015 |
| 20150044053 | Steam Turbine Rotor - It is an objective of the invention to provide a steam turbine rotor that is capable of both reducing SCC susceptibility and improving LCF life thereof. There is provided a steam turbine rotor, comprising a rotor disk in a low pressure final stage L-0, and another rotor disk in a plurality of stages including a stage L-1 positioned closer to a high pressure side than the low pressure final stage L-0, the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 being joined by welding, wherein a material of both the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 is a 12Cr steel and has a tensile strength of 900 to 1200 MPa. | 02-12-2015 |
| 20150078904 | REPAIRED TURBINE ROTOR WHEEL DOVETAIL AND RELATED METHOD - A method of repairing a damaged dovetail on a peripheral portion of a turbine wheel includes the steps of removing buckets from the dovetail; removing a damaged dovetail from the peripheral portion of the turbine wheel, leaving a rotor wheel body having a peripheral rim; disposing a replacement ring about the peripheral rim, the replacement ring and the rim defining therebetween a pair of end grooves and a center section; and welding the replacement ring to the peripheral rim, with weld material applied only within the end grooves, leaving a void in the center section. | 03-19-2015 |
| 20150078905 | TURBINE ROTOR FOR AN EXHAUST GAS TURBINE AND METHOD FOR PRODUCING THE TURBINE ROTOR - A turbine rotor for an exhaust gas turbine has a turbine rotor wheel made of a highly heat-resistant metal alloy and a rotor shaft made of steel. A rotor wheel hub and a rotor shaft end are connected to each other in a metallurgical bond by way of a solder connection. The rotor shaft end and/or the rotor wheel hub is formed with a central recess, which acts as a thermal choke. A closing plug is arranged in the respective recess, forming a closed cavity with the recess and closing off the recess toward the respective end face. The solder connection is formed between the end faces of the rotor wheel hub and the rotor shaft, between the closing plug and the rotor wheel hub, and between the closing plug and the rotor shaft. | 03-19-2015 |
| 20150104318 | TURBINE ROTOR FOR AN EXHAUST-GAS TURBINE AND METHOD FOR PRODUCING THE TURBINE ROTOR - A turbine rotor as a turbine impeller made of a high-temperature-resistant metal alloy and a rotor shaft made of steel. The impeller hub and the rotor shaft end are connected together in a metallurgically bonded manner by way of a brazed connection. Between the end faces of the impeller hub and of the rotor shaft end, a brazing gap filled with brazing alloy is arranged concentrically with the rotation axis of the turbine rotor. A width of the soldering gap is previously determined by circularly peripheral removal of material on the end face of the impeller hub or the end face of the rotor shaft end, and the brazing connection is produced by an electron beam soldering process. | 04-16-2015 |
| 20150139810 | NOISE REDUCING EXTENSION PLATE FOR ROTOR BLADE IN WIND TURBINE - Rotor blade assemblies and methods for constructing rotor blade assemblies are provided. A rotor blade assembly may include a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge and a trailing edge each extending between a tip and a root, the rotor blade defining a span and a chord. The rotor blade assembly further includes an extension plate mounted to one of the pressure side or the suction side, the extension plate extending in the chord-wise direction between a first end and a second end, the second end extending beyond the trailing edge. The rotor blade assembly further includes a filler substrate provided on an inner surface of the extension plate and the trailing edge, the filler substrate tapering from the trailing edge towards the second end. | 05-21-2015 |
| 20150300182 | METHOD FOR FRICTION WELDING A BLADE ONTO A TURBINE ENGINE ROTOR DISC; CORRESPONDING INTEGRAL BLADE DISC - A method of friction welding an airfoil ( | 10-22-2015 |
| 20150354379 | DUAL ALLOY TURBINE ROTORS AND METHODS FOR MANUFACTURING THE SAME - Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step. | 12-10-2015 |
| 20160115794 | COMPOSITE ANNULUS FILLER - A composite annulus filler adapted to bridge the gap between two adjacent rotor blades attached to a rim of a rotor disc of a gas turbine engine. The annulus filler includes a unitary body portion having a platform which extends between the adjacent rotor blades and defines an airflow surface for air being drawn through the engine and a support body extending beneath the platform and terminating in a root which, in use, extends along a groove provided in the rim of the rotor disc. | 04-28-2016 |
| 20160146023 | Rotor With Blades Secured by Woven Fiber Attachment System - A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor. | 05-26-2016 |
| 20170234322 | Arrangement of an Impeller Wheel on an Electric Motor and Method for Producing the Same | 08-17-2017 |
| 20090047133 | IMPELLER BLADE FOR CENTRIFUGAL BLOWER, BLADE-SUPPORTING ROTATOR, IMPELLER FOR CENTRIFUGAL BLOWER, AND METHOD FOR MANUFACTURING IMPELLER FOR CENTRIFUGAL BLOWER - Blades of an impeller for a centrifugal blower are resinous hollow blades having hollow spaces formed in the blade interiors, and having first blade weld parts welded to plate weld surfaces of an end plate, wherein first blade weld surfaces inclined with respect to the plate weld surfaces are formed on the first blade weld parts in a state in which the first blade weld parts are disposed to face the plate weld surfaces in the axial direction. | 02-19-2009 |
| 20100158689 | CROSS-FLOW FAN MADE OF RESIN AND METHOD OF MANUFACTURING THE SAME - A resin cross flow fan and a method for manufacturing a resin cross flow fan are provided in which an annealing step can be omitted and the number of circular disks can be reduced, and which provides improved fan strength and air blowing performance. A resin cross flow fan is disposed with a plurality of blades and a plurality of plates. The plurality of blades are annually disposed about a rotation axis. Insertion portions each constituted by a hole or a groove into which each blade is inserted and projecting portions that projects from the periphery of the insertion portions in a direction of the rotation axis are formed on each of the plurality of plates disposed spaced apart in the direction of the rotation axis. Each blade is fixed to the projecting portions by laser welding. | 06-24-2010 |
| 20140154086 | FRONT FAN RETENTION IN DUAL INTERNAL FAN ALTERNATOR - An alternator has a pole segment with a collar, an axially outward surface, and at least one key extending radially outward from the collar along the surface. A fan has a keying slot extending radially outward from a center ring, and a fan body including protrusions. The fan is mounted to the segment whereby the collar fits inside the ring and the key fits inside the keying slot, and the fan is welded to the segment at the protrusions. A method includes securing a fan to a pole segment by mating a radially-extending key formed on the segment to a keying slot of the fan and by welding the fan to the segment. | 06-05-2014 |
