Entries |
Document | Title | Date |
20080209727 | FILLET MACHINING WITHOUT ADAPTIVE PROBING AND PARTS FINISHED THEREBY - A method for finishing a part having excess material includes generating one or more surfaces on a model of the part to be machined, creating a machining tool path drive geometry, using the machine tool path drive geometry and one or more surfaces on the model to be machined to generate machining tool paths on the surfaces; and running tool paths on the part in a fixture. | 09-04-2008 |
20080313899 | BIMATERIAL TURBINE BLADE DAMPER - A turbine blade damper includes an outer part for damping vibration of the blade airfoil and a supporting inner part. The two parts are formed of different materials for the different performance required thereof in the blade. | 12-25-2008 |
20090013532 | AIRFOILS FOR USE IN ROTARY MACHINES AND METHOD FOR FABRICATING SAME - A method of fabricating an airfoil is provided. The method includes fabricating at least one airfoil including a suction side and a pressure side coupled together at a leading edge and a trailing edge, wherein the airfoil includes a plurality of first and second chord sections each extending between the trailing and leading edges, wherein at least one of the first chord sections extends outward from the pressure side of the airfoil at the trailing edge, and at least one of the second chord sections extends outward from the suction side of the airfoil at the trailing edge. | 01-15-2009 |
20090025220 | Method and device for machining components of a gas turbine and composite material and its use in methods for machining or joining components of a gas turbine - A method for machining components of a gas turbine, in particular for machining turbine blades, is described. The method includes the following steps: a) providing at least one component carrier having at least one component receptacle for detachable accommodation and fastening component to be machined, the component receptacle being designed with a contour similar to at least one contour of subarea of component to be accommodated; b) introducing at least one subarea of the component into component receptacle and form-fitting and/or substance-to-substance bonding of the subarea of the component to component receptacle; c) machining the component, which is attached to the component carrier; and d) releasing the machined component from the component carrier. In addition, a device for machining turbine blades is described having at least one component carrier, the component carrier having at least one component receptacle for detachable accommodation and fastening of the component that is to be machined, and the component receptacle being designed with a contour resembling at least one contour of a subarea of the component that is to be accommodated, as well as a composite material for machining or bonding components of a gas turbine, in particular for machining turbine blades, the composite material including a woven or nonwoven fiber material and an adhesive, an adhesive support or individual adhesive components, such that the adhesive, the adhesive support or the adhesive components of the fiber material at least partially surrounds the fiber material. The use of the composite material in methods for machining or bonding components of a gas turbine is also described. | 01-29-2009 |
20090044406 | METHOD FOR PRODUCING METALLIC COMPONENTS, PARTICULARLY FOR TURBO MACHINES, HAVING SMALL EDGE RADII, AND COMPONENT PRODUCED THEREWITH - A method for producing metallic components, and metallic components produced by the method, particularly for turbo machines, having small edge radii, is disclosed. The method includes mechanical and/or electrochemical machining of a component while producing a small edge radius and solidifying the small edge radius by ultrasonic shot peening. As a result of the method, the disadvantages of the prior art are avoided and a machine process that can be automated has been provided, the method permitting considerable savings of time and labor and leading to reproducible results. | 02-19-2009 |
20090056127 | BLADE STRUCTURE FOR TORQUE CONVERTER AND PROCESS FOR PRODUCING THE SAME - A blade structure for a torque converter, produced by a process including the steps of: stamping a flat blank into a first annular plate that includes a first connecting ring portion, a second connecting ring portion, and a plurality of blades spaced from each other in a circumferential direction of the first and second connecting ring portions; bending the blades into a curved shape curved with respect to the first annular plate; bending the blades to be inclined by a predetermined angle with respect to the first and second connecting ring portions; and expanding the first annular plate outwardly in a radial direction thereof to thereby form a predetermined annular shape that has a larger radial dimension than the first annular shape and a larger circumferential distance between respective adjacent two of the blades than that in the first annular plate. | 03-05-2009 |
20090077801 | METHOD FOR THE SURFACE TREATMENT OF CR STEELS - A method for the surface treatment of ferritic/martensitic 9-12% Cr steels and of austenitic Cr steels for the purpose of achieving increased resistance to oxidation and solid particle erosion at application temperatures of above 500° C., in particular of approximately 650° C., in steam, includes that the surface of the steel is shot-peened with particles of aluminum or of an aluminum alloy; optionally, in a subsequent step, the surface of the steel is smoothed to a roughness of <0.5 μm, preferably <0.3 μm. Following additional heat treatment is not necessary, and the parts thus treated may be employed, for example, as blades in steam turbines. | 03-26-2009 |
20090119919 | COMPONENTS FOR GAS TURBINE ENGINES AND METHODS FOR MANUFACTURING COMPONENTS FOR GAS TURBINE ENGINES - A method of manufacturing a turbine engine component comprises the steps of fabricating an inner hub, casting a plurality of blades, forming a blade ring, and bonding the blade ring to the inner hub. Each blade comprises a blade root and an airfoil body extending from the blade root. The blade ring comprises, at least in part, the plurality of blades coupled by a first bonding technique. The blade ring is bonded to the inner hub using a second bonding technique. | 05-14-2009 |
20090119920 | METHOD OF PRODUCING A COMPONENT - The present technology relates to a method for producing a component, especially a gas turbine component, with at least the following steps: a) production of a component with several component surfaces, in which at least one transitional area between two component surfaces has a transition radius that is greater than 0.05 mm and less than 0.30 mm; b) strengthening of the component, at least on the transitional area or each transitional area, by ultrasonic shot peening. | 05-14-2009 |
20090165299 | Method of Manufacturing a Turbine Fan Blade - A metal leading edge of a turbine fan blade is manufactured by cutting and shaping an elongated metal part. The metal part has front and rear edges extending lengthwise of the part, and has a generally wedge-shaped transverse cross-section with opposite sides diverging from the front edge toward the rear edge. A cavity is cut inward from the rear edge toward the front edge. This provides the part with a generally V-shaped transverse cross-section having opposite side walls diverging rearwardly from the front edge. A mandrel is inserted into the cavity, and the side walls of the V-shaped part are deflected toward each other to constrict the cavity into the configuration of the mandrel. The part is then mounted as a metal leading edge by inserting a turbine fan blade component into the constricted cavity and fastening the part to the component. | 07-02-2009 |
20090211092 | METHOD OF MANUFACTURING VANE - A method is provided which manufactures a vane used for an oil-sealed rotary vacuum pump and having at least a part formed of a resin material, the method including: an oil impregnating process of immersing the vane into oil used for the oil-sealed rotary vacuum pump under a depressurized condition, the oil impregnating process being carried out before a finishing process of finishing the vane into a final shape. | 08-27-2009 |
20090235526 | Method for the manufacture of a welded blisk drum - When manufacturing welded blisk drums for gas-turbine engines, two or more integrally bladed blisks are joined to a blisk drum by welding, with this drum being subsequently heat-treated. In the final processing step, the blisk blades are polished, with the blisk drum as a whole being immerged into a flowable, pasty abrasive medium, and with a relative movement between the blisk drum and the abrasive medium being generated by translation and/or vibration and/or rotation of the blisk drum or a tub containing the abrasive medium. In order to avoid changes in shape of the blade edges during polishing, relative movement in these areas is prevented by guiding elements. The blade edges may also be masked, or surplus material may be provided on the blade edges, which afterwards is removed during grinding. | 09-24-2009 |
20090249623 | Method for aerodynamically shaping the leading edge of blisk blades - For shaping the leading edge ( | 10-08-2009 |
20100024215 | Jig for manufacturing components of aerodynes and wing turbines and manufacturing process for these components - The invention relates to a jig for manufacturing components of aerodynes and wind turbines and a manufacturing process for these components, the jig comprising a base ( | 02-04-2010 |
20100071209 | Surface Finishing of Rotor Blades for Wind Turbine - The present invention relates to a method for surface treatment of a wind turbine rotor blade ( | 03-25-2010 |
20100122459 | METHOD OF MAKING WIND TURBINE BLADE - A method of making a wind turbine blade is provided. The method includes the steps of providing a mold generally conforming to a shape of at least a portion of a wind turbine blade. A filling step fills the mold with a thermoplastic material. A heating step heats the mold, and at least a portion of the heating step includes a rotating step that rotates the mold. A cooling step cools the mold, and is followed by a removing step, which removes at least a portion of the wind turbine blade from the mold. | 05-20-2010 |
20100132194 | Method and an apparatus for prestressing components - A method of pre-stressing a component such as a turbine blade ( | 06-03-2010 |
20100175256 | METHOD FOR THE MANUFACTURE OF THE BLADE TIPS OF ROTOR WHEELS MADE IN BLISK DESIGN - With a method for finish-machining the blade tips of rotor wheels made in BLISK design, the rotor wheel or multi-stage compressor rotor ( | 07-15-2010 |
20100212157 | Method and apparatus for controlled shot-peening blisk blades - A controlled shot-peening of blisk blades ( | 08-26-2010 |
20100236068 | Manufacturing method of blower fan wheel - A manufacturing method of a blower fan wheel includes manufacturing a fixing disc having an installing ring formed and extended outwardly from the periphery of the fixing disc, arc insert slots formed on a circumferential surface of the installing ring and not intersected with the external periphery of the installing ring, and an insertion portion disposed at a central position of the fixing disc for installing a motor transmission shaft; and then inserting a vane into each insert slot by a close-packing implantation method, such that an end of each vane is passed out of each insert slot, and each vane is divided into a first side and a second side by the installing ring to produce the blower fan wheel of the present invention. | 09-23-2010 |
20100242280 | Method for manufacturing closed impeller - The present invention provides a method for manufacturing a closed impeller that has a simple configuration and enables fusion in a very accurate position. The method includes: forming a frustum-shaped front plate and a disk-shaped base plate formed therebelow, upper surfaces of a plurality of unit impeller blade plates made from a synthetic resin extending in radial directions which are formed as impeller blade tip surfaces, with sharp-pointed ridge-like protrusions having an acute upper end and a width less than a width of the impeller blade tip surface being integrally formed on the impeller blade tip surfaces. In the method, an inner surface of the front plate and the plurality of impeller blade tip surfaces are formed as parts of conical surfaces and formed so that the cone apex angles of the two conical surfaces are equal to each other. Then, the front plate is placed on the impeller blade and the ends of the sharp-pointed ridge-like protrusions and the inner surface of the front plate are brought into contact with each other. Small vibrations are then provided while applying an appropriate pressurizing force between the front plate and the impeller blade having the base plate attached thereto, the sharp-pointed ridge-like protrusions are melted, and the front plate is fused to the tip surfaces of the impeller blade. | 09-30-2010 |
20100242281 | ATTACHMENT METHOD FOR FAN COMPONENT ASSEMBLIES - A fan attachment is provided to attach a fan assembly to a cap of a heat exchanger. The fan attachment includes a feature to manage wires going to the fan motor, a notch for a thermister to sense temperature, snap hooks to be engaged by receiving tabs of the cap, a keying shear load feature to radially align the fan attachment and cap, and Z-height tolerance springs to bias the fan attachment away from the cap. The cap has features to interact with those of the fan attachment, including receiving tabs. The fan attachment may be manually aligned and forced so that the snap hooks are received and engaged by the receiving tabs. Additionally, the snap hooks and keying feature are, in combination, capable of supporting fan and attach mechanism in an undamaged condition during 25 g-force shock to the heat exchanger. | 09-30-2010 |
20100251546 | SYSTEM AND METHOD FOR ADJUSTING PERFORMANCE OF MANAUFACTURING OPERATIONS OR STEPS - A manufacturing system and manufacturing method for adjusting the performance of manufacturing operations or steps in manufacturing components having three-dimensional external structural characteristics. An embodiment of the system broadly comprises: (a) a plurality of manufacturing operations for processing a component having three-dimensional external structural characteristics; (b) at least one analytical device for analyzing at least one characteristic of the component after the performance of one or more manufacturing operations to generate a component data set; (c) at least one data storage device for storing the generated component data sets and for providing at least a relevant portion of accumulated component data; and (d) a communication mechanism for transmitting at least a relevant portion of accumulated component data to one or more manufacturing operations so that the performance thereof can be adjusted in response to the transmitted portion of accumulated component data. An embodiment of the method broadly comprises the following steps: (a) providing a component having three-dimensional external structural characteristics; (b) providing at least a relevant portion of accumulated component data comprising at least two different component data sets; and (c) performing a manufacturing step on the component to provide a processed component, wherein the at least relevant portion of accumulated component data is used to adjust the manner in which the manufacturing step is performed. | 10-07-2010 |
20110010937 | METHOD OF MANUFACTURING A TURBINE FAN BLADE - A metal leading edge of a turbine fan blade is manufactured by cutting and shaping an elongated metal part. The metal part has front and rear edges extending lengthwise of the part, and has a generally wedge-shaped transverse cross-section with opposite sides diverging from the front edge toward the rear edge. A cavity is cut inward from the rear edge toward the front edge. This provides the part with a generally V-shaped transverse cross-section having opposite side walls diverging rearwardly from the front edge. A mandrel is inserted into the cavity, and the side walls of the V-shaped part are deflected toward each other to constrict the cavity into the configuration of the mandrel. The part is then mounted as a metal leading edge by inserting a turbine fan blade component into the constricted cavity and fastening the part to the component. | 01-20-2011 |
20110056078 | METHOD OF PRODUCING A ROTOR COMPONENT OR A STATOR COMPONENT - A method of producing a rotor component or a stator component includes the steps of providing a disc-shaped element with a plurality of radially projecting and circumferentially spaced blades, an intermediate ring with an inner surface adapted for contacting tips of the blades, and an external ring with an inner surface adapted for contacting an outer surface of the intermediate ring, moving the intermediate ring co-axially in relation to the disc-shaped element to an operative position in which it is located radially outside the blades, and moving the external ring co-axially in relation to the intermediate ring to an operative position in which it is located radially outside the intermediate ring. | 03-10-2011 |
20110088261 | METHOD OF MAKING AND JOINING AN AEROFOIL AND ROOT - A ducted fan gas turbine engine aerofoil is made by electron beam welding together at least two metal sheets ( | 04-21-2011 |
20110113627 | METHOD OF MANUFACTURING A BLADING COMPONENT - A method of manufacturing a metal blading sector for low-pressure guide vanes of a turbomachine of which at least one blade includes an internal cavity configured to accept or communicate with a gas detection probe and at least one hole formed in the wall constituting a passage for gas from a low-pressure zone of the turbomachine toward the cavity and the probe through the fitting, into a casting mold, of a core corresponding to the cavity and the casting of a molten metal in the cavity of the casting mold. The core includes, for each hole for communication with the cavity, a protrusion penetrating the internal surface of the mold and constituting the only element holding the core in position in the casting mold. | 05-19-2011 |
20110138626 | METHOD AND APPARATUS FOR MOUNTING A ROTOR BLADE ON A WIND TURBINE - An installation system and a method for mounting a rotor blade to a hub on a wind turbine are disclosed. The method includes coupling a rotor and a stator together, the rotor rotatably connected to the hub. The method further includes rotating the stator in a first direction, wherein rotation of the stator causes the rotor and the hub to rotate in the first direction. The method further includes securing the hub to prevent rotation of the hub. The installation system includes a coupling device configured to releasably couple a stator and a rotor together and a securing device configured to releasably secure the hub. The installation system further includes at least one stator drive device operably connected to the stator, the stator drive device configured to rotate the stator between a first position and a second position. | 06-16-2011 |
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 |
20120124833 | SYSTEMS AND METHODS FOR TRANSPORTING AND ASSEMBLING SEGMENTED WIND TURBINE BLADES - Systems and methods for transporting and assembling segmented wind turbine blades are disclosed. A system in accordance with a particular embodiment includes multiple transport devices that are each moveable as a unit from a blade fabrication site to a blade assembly site, and that have corresponding carriers positioned to carry corresponding spanwise segments of a wind turbine blade. The system can still further include a guide structure carried by at least one of the transport devices and coupled to a corresponding one of the carriers, with a motion path aligned with a corresponding blade axis. The guide structure can be positioned to guide the corresponding carrier along the motion path toward the other transport devices, e.g., to facilitate assembly of the blade segments. | 05-24-2012 |
20120124834 | METHOD FOR MANUFACTURING A FORGED PART WITH ADAPTIVE POLISHING - A method for manufacturing a part by forging, including producing a semifinished part by precision forging and polishing the part by an abrasive strip, compliant geometric characteristics of the part to be obtained being predetermined in a theoretical model. The method includes: measuring the geometrical characteristics of the semifinished part after the forging operations and comparing the characteristics with the theoretical model; determining noncompliant areas on the surface of the part; determining the amount of material to be removed from each noncompliant area to make the area compliant; and polishing the part using the abrasive strip, controlling the strip so as to remove the amount of material from each noncompliant area. The method can be used for example for polishing turbine engine fan blades. | 05-24-2012 |
20120159785 | AUTOMATED PROCESSES FOR THE PRODUCTION OF POLYURETHANE WIND TURBINE BLADES - The present invention provides processes for the production of polyurethane wind turbine blades and other large objects. The inventive process involves forming a mold for the polyurethane wind turbine blade at a wind farm site, injecting an isocyanate and an isocyanate-reactive component with an automated reaction injection molding (“RIM”) machine into the mold, closing, pressing and heating the mold to cure the resulting polyurethane and installing the polyurethane blade in the wind turbine. Alternatively, the process involves forming a mold for polyurethane wind turbine blade at a wind farm site, injecting an isocyanate, an isocyanate-reactive component and long fibers with an automated long fiber injection (“LFI”) machine, closing, pressing and heating the mold to cure the resulting polyurethane and installing the polyurethane blade in the wind turbine. Because the inventive manufacturing process occurs at the wind farm site, transportation problems are obviated. | 06-28-2012 |
20120186082 | METHOD FOR MANUFACTURING A TURBINE BLADE - A turbine blade growth pocket provides a feature to measure blade growth due to engine operation while maintaining dynamic characteristics of the turbine blade within acceptable limits by providing a variable radius fillet between the pocket and a side rail of the pocket. | 07-26-2012 |
20120233859 | METHOD FOR PRODUCING A METAL REINFORCEMENT FOR A TURBINE ENGINE BLADE - A method for making a metal reinforcement for the leading edge or trailing edge of a turbine engine blade, including: positioning a preform using an equipment positioning the preform in a position such that the preform, at one end thereof, has an area which is capable of receiving a filler metal; and, after the positioning, constructing a base for the metal reinforcement by hard-surfacing with filler metal in the area, in the form of metal beads. | 09-20-2012 |
20120240399 | TURBOMACHINE ROTOR ASSEMBLY AND METHOD - Disclosed is a rotor assembly for a turbomachine includes a disk having a first axial face and a second axial face. The disk includes at least one circumferential dovetail extending around an outer surface of the disk and a plurality of axial dovetails extending from the first axial face to the second axial face. Each blade of a plurality of blades is installed into an axial dovetail of the plurality of axial dovetails and each platform of a plurality of platforms is installed adjacent to a blade of the plurality of blades via the at least one circumferential dovetail. Further disclosed is a method of assembly of a rotor for a turbomachine. | 09-27-2012 |
20130014387 | METHOD OF FORGING TURBINE BLADEAANM KIMURA; KojiAACI AichiAACO JPAAGP KIMURA; Koji Aichi JPAANM OKAJIMA; TakumaAACI AichiAACO JPAAGP OKAJIMA; Takuma Aichi JP - The present invention relates to a method of forging turbine blade, which comprises forging a plurality of turbine blades as an integrally connected body in a longitudinal direction, and then separating the integrally connected body into said respective turbine blades. According to the method of the invention, a yield of material can be improved as compared with the conventional art and the number of processes for forging work can be reduced. In addition, the turbine blades cab be forged into a favorable shape without occurring cracks. Further, it is possible to effectively reduce the cost for the die required for the forging work. | 01-17-2013 |
20130014388 | METHOD OF PRODUCING TURBINE BLADEAANM KIMURA; KojiAACI AichiAACO JPAAGP KIMURA; Koji Aichi JPAANM ASANO; HiroshiAACI HyogoAACO JPAAGP ASANO; Hiroshi Hyogo JPAANM KUMAZAWA; IkunoAACI HyogoAACO JPAAGP KUMAZAWA; Ikuno Hyogo JP - The present invention relates to a method of producing turbine blade, which comprises, (a) forging a plurality of turbine blades in a state where the plurality of turbine blades are integrally connected in a longitudinal direction, (b) heat treating the plurality of turbine blades in the integrally connected state, (c) machining the plurality of turbine blades in the integrally connected state, and (d) separating the plurality of turbine blades into individual turbine blades. According to the method, the number of processes for the forging work can be decreased, and forging efficiency can be enhanced. Moreover, an amount of burr which occurs during the forging work can be reduced, and hence, a yield of material can be improved, as compared with a case where the turbine blade is forged as a single body. | 01-17-2013 |
20130019477 | METHOD OF MACHINING USING AN AUTOMATIC TOOL PATH GENERATOR ADAPTED TO INDIVIDUAL BLADE SURFACES ON AN INTEGRALLY BLADED ROTOR - A method of flank and/or point milling an integrally bladed rotor is conducted with an automatic tool path generator which generates a new created tool path including smooth transitions merging between an actual finished surface and a nominal surface of the integrally bladed rotor. The actual finished surface is presented in a mathematical transformation matrix which may be obtained in a 3-D scanning process. | 01-24-2013 |
20130091705 | METHOD FOR ASSEMBLING A MULTI-SEGMENT WIND TURBINE ROTOR BLADE WITH SPAN-WISE OFFSET JOINTS - A method provides for assembling a wind turbine blade from at least two blade segments, with each of the blade segments having a pressure side shell member, a suction side shell member, internal support structure, and ends with joint sections that are offset span-wise from the pressure side shell member to the suction side shell member. The blade segments are aligned in an end-to-end orientation and moved into a mating configuration with relative movement that includes overlapping the respective joint sections of adjacent blade segments. The overlapped joint sections are subsequently moved into engagement with each other and joined along respective joint profiles at a chord-wise joint. | 04-18-2013 |
20130111751 | COOLED TURBINE BLADE SHROUD - A process for forming a turbine blade comprises the step of forming an as-cast turbine blade having an airfoil portion and a tip shroud, wherein the forming step comprises forming at least one as-cast cooling circuit within the tip shroud. | 05-09-2013 |
20130111752 | MANUFACTURE OF A ROOT SECTION - A method of manufacturing a root section of a rotor blade of a wind turbine is disclosed. The method includes assembling a plurality of supporting rods with an interface section to a hub interface of the wind turbine in an essentially circular shape such that there are gaps between the supporting rods; arranging first fibres in the gaps which first fibres are physically and/or chemically compatible with an injection material; placing a first molding tool along an outer surface of the circular shape and a second molding tool along an inner surface of the circular shape, treating the injection material so that it bonds with the first fibres. The invention also concerns a supporting rod holding arrangement for such purpose and a root section of a rotor blade manufactured by such method. | 05-09-2013 |
20130174420 | EQUIPMENT COMPRISING A ROTATABLE CRADLE AND INTENDED FOR ENCASING THE AIRFOIL OF A TURBINE BLADE IN ORDER TO MACHINE THE ROOT - An equipment for coating an airfoil of a turbine blade of a turbine engine in a coating block, including a base on which a molding block is positioned for flow of the coating metal, the molding block including a cavity defining a reference plane on the block for positioning the block in space, wherein the base also includes a cradle supporting the blade via six bearing points defining an orientation plane representative of an angular position of the airfoil relative to a root of the blade. The cradle is rotatably movable relative to the base about an axis oriented so as to be substantially parallel to a direction of a leading edge of the blade, to enable a modification in an angle formed between the reference and orientation planes. | 07-11-2013 |
20130219717 | METHOD FOR PRODUCING A METAL REINFORCEMENT FOR A TURBOMACHINE BLADE - A method for producing a metal reinforcement for the leading edge or trailing edge of a turbomachine blade, the method including cutting a plurality of metal foils from a flexible metal sheet, corresponding substantially to the developed length of the leading or trailing edge metal reinforcement; producing a plurality of metal pockets, each pocket being produced from two of the metal foils obtained during the cutting; stacking the metal pockets one inside the other, such as to form a preform of the leading or trailing edge metal reinforcement; and hot isostatic pressing the preform, causing the metal pockets to bond to one another, so as to produce the leading or trailing edge metal reinforcement. | 08-29-2013 |
20130269189 | Method and Device for Machining Elongate Workpieces that are not Rotationally Symmetrical in the Form of Tubine Blades - In a method and a device for machining an elongate workpiece that is not rotationally symmetrical in the form of turbine blades, the workpiece is supported by a steady rest that has clamping elements for clamping the workpiece on the cross-section thereof that is not rotationally symmetrical. After clamping the workpiece, the steady rest moves with its open clamping elements along the longitudinal axis of the workpiece into a supporting position. During movement of the steady rest into the supporting position and/or while the supporting position of the steady rest is being changed, a collision between the open clamping elements of the steady rest and the workpiece is prevented by a program-controlled rotation of a rotary part of the steady rest. | 10-17-2013 |
20130276303 | METHOD OF MANUFACTURING IMPELLER FOR CENTRIFUGAL BLOWER - A resinous blade-supporting rotator is prepared to rotate around a rotational axis. The blade-supporting rotator has rotator weld parts including rotator weld surfaces formed on one side surface in the axial direction. A plurality of resinous blades are disposed annularly around the axis. The plurality of resinous blades have hollow spaces formed in the blade interiors, and blade weld parts with blade weld surfaces. The blade weld surfaces and the rotator weld surfaces are inclined with respect to each other when facing each other in the axial direction. An axial pressure load is applied to opposite axial ends of the blade-supporting rotator so as to compress the blades in the axial direction such that the blade weld surfaces and the rotator weld surfaces are no longer inclined with respect to each other. The blade weld surfaces are fixed to the rotator weld surfaces by laser welding. | 10-24-2013 |
20130298401 | MANUFACTURING METHOD FOR BLADE MATERIAL AND MANUFACTURING DEVICE FOR BLADE MATERIAL - Provided are a manufacturing method for a blade material and a manufacturing device for a blade material, by which a long blade material can be manufactured without using a large-sized press forging machine. A manufacturing method for a blade material, in which hot forging is sequentially performed by molds from the root side to a blade (vane) tip, wherein when a root-side portion is grasped and a material to be forged is restrained by a mold, twisting is performed on a region between the grasped portion and the restrained portion. A manufacturing method for a blade material, in which hot forging and twisting are repeated, is preferable, and a manufacturing method for a blade material, in which hot forging is performed while molds are sequentially changed, is more preferable. | 11-14-2013 |
20130318787 | MANUFACTURING A FAMILY OF AIRFOILS - A method of manufacturing a family of airfoils includes providing a plurality of airfoil blanks of identical geometry, selecting a first airfoil geometry from a family of airfoil geometries, selecting a second, different airfoil geometry from the family of airfoil geometries, machining a first one of the plurality of airfoil blanks to the first airfoil geometry to produce a first airfoil of the family of airfoil geometries, and machining a second, different one of the plurality of airfoil blanks to the second airfoil geometry to produce a second, different airfoil of the family of airfoil geometries | 12-05-2013 |
20130318788 | MANUFACTURING METHOD OF A COMPONENT OF A SPLIT BLADE OF A WIND TURBINE - The invention provides a manufacturing method of a component of a split blade of a wind turbine (such as an inboard shell or an inboard spar) having joining elements with its complementary component (i.e. an outboard shell or an outboard spar). The method comprises the following steps: a) manufacturing a joint laminate of a composite material having embedded into it the joining elements, said joint laminate being configured for becoming a part of the component; b) manufacturing the component using as a preform said joint laminate. The invention also refers to a split blade comprising components manufactured by said manufacturing method. | 12-05-2013 |
20130318789 | SYSTEM AND METHOD FOR ASSEMBLING AND DISASSEMBLING COMPONENTS FROM A WIND POWER TURBINE - A method and system is provided for assembling or disassembling a blade of a wind turbine. The wind turbine includes a tower resting on a base, a rotor including at least one rotor blade having a blade connection flange and a nacelle mounted atop the tower, a hub rotatably connected to the nacelle and including a hub connection flange adapted to be detachably connected to a blade connection flange of a rotor blade. Thy wind turbine further includes a first positioning element adapted to be attached to the nacelle or to the tower in a top area and a second positioning element adapted to be joined to the blade in a root blade area, where the first and second positioning elements are configured to cooperate to provide an accurate position of the blade connection flange prior to connection to the hub connection flange. | 12-05-2013 |
20130333213 | METHOD OF USING LASER SHOCK IMPACTS TO PRODUCE RAISED ELEMENTS ON A WALL SURFACE CAPABLE OF BEING SWEPT BY A FLUID IN ORDER TO CONTROL THE INTENSITY OF TURBULENCE IN A TRANSITION ZONE - A method for producing, on the surface of a wall capable of being swept by a fluid, raised elements forming disruptions of the boundary layer is disclosed. The method includes applying laser shocks to the surface so as to create peaks on the edge of the impact zones such that the peaks form the disruptive raised elements. | 12-19-2013 |
20130333214 | PROCESS FOR MANUFACTURING A METAL PART, SUCH AS TURBINE ENGINE BLADE REINFORCEMENT - A method for producing a metal component such as a metal turbomachine blade reinforcement, includes positioning a plurality of metal staples in a forming tool having a die and a punch; and hot isostatic pressing the plurality of metal staples causing the agglomeration of the metal staples so as to obtain a solid component. | 12-19-2013 |
20140041224 | POST PROCESSING OF COMPONENTS THAT ARE LASER PEENED - A method of post processing a laser peened component to remove a laser remelt layer is proposed. The post processing includes a series of steps including grit blasting, chemical etching and mechanical finishing the component. This will ensure that the mechanical property (i.e., damage tolerance) benefit of laser peening is restored to the surface of the component. | 02-13-2014 |
20140059856 | MACHINING PROCESS AND APPARATUS FOR MACHINING - A method of determining a tool path to machine a component, the method comprising the steps of: securing the component to a fixture having a zero point alignment datum, the component and the fixture having respective mobile reference points; aligning the fixture mobile reference points to target reference points on the machine tool; aligning a digitised model of the component to the component mobile reference points; determining the position of the component on the fixture from the component mobile reference points and the fixture mobile reference points; and adjusting a nominal tool path for the machine tool dependent on the position of the component. | 03-06-2014 |
20140068939 | METHOD FOR MANUFACTURING AN AIRFOIL - A method for manufacturing an airfoil includes casting the airfoil around a core and creating a hole through a surface of the airfoil with a water jet. The method further includes striking at least a portion of the core inside the airfoil with the water jet and removing the core from inside the airfoil. | 03-13-2014 |
20140130353 | COMPONENTS FOR GAS TURBINE ENGINES AND METHODS FOR MANUFACTURING COMPONENTS FOR GAS TURBINE ENGINES - A method of manufacturing a turbine engine component comprises the steps of fabricating an inner hub, casting a plurality of blades, forming a blade ring, and bonding the blade ring to the inner hub. Each blade comprises a blade root and an airfoil body extending from the blade root. The blade ring comprises, at least in part, the plurality of blades coupled by a first bonding technique. The blade ring is bonded to the inner hub using a second bonding technique. | 05-15-2014 |
20140137409 | ADAPTIVE MACHINING METHOD FOR SMELTED BLADES - A method for finishing a shape of a component by machining, in which one area is produced by smelting with a thickened portion forming a first surface with a surrounding profile and a theoretical profile defined by a second surface, the method including: defining, on the second surface, a grid forming nodes and squares; defining each point over which the machining tool is to pass according to weighting coefficients equal to weight to be given to the nodes of the square in which the tool is located, to be the barycenter of assigned nodes of the coefficients; measuring, for each node located outside an outer limit, the delta between the first surface at the node and the theoretical position of the node; calculating deltas for each node within the outer limit by interpolation from already known deltas; using the weighting coefficients, defining the delta to be applied at each point. | 05-22-2014 |
20140182131 | METHOD OF FABRICATING A PART BY FORGING - A method of fabricating a part by forging, the method including: measuring geometrical characteristics of the forged part; comparing a measured shape with a theoretical shape that is to be obtained for the part; deducing therefrom zones that are not in compliance with the theoretical shape and also thicknesses of material that need to be removed from the zones that are not in compliance; and polishing the zones of the forged part that are not in compliance to remove the deduced thicknesses of material by using a controlled abrasive band. The control of the abrasive band takes account of at least one parameter representative of wear of the abrasive band during polishing of zones that are not in compliance. | 07-03-2014 |
20140298651 | Method For Making A Shaped Turbine Aerofoil - According to the method, a turbine aerofoil is made starting from a reference aerofoil, locally reducing the metallic exit angle at the trailing edge in two areas which substantially correspond, in use, to the position of the peaks of the secondary flows in the boundary layer. | 10-09-2014 |
20140325841 | METHOD FOR RESHAPING A TURBOMACHINE BLADE THAT HAS AT LEAST ONE ZONE THAT HAS BECOME DEFORMED USING PEENING - A method of reshaping a turbine engine blade including at least one deformed zone, the method including peening the deformed zone to be able to restore a shape of the at least one deformed zone. | 11-06-2014 |
20140352148 | METHOD OF ULTRASONIC INSPECTION OF AS-CAST TITANIUM ALLOY ARTICLES - A method is provided of non-destructively inspecting titanium alloy articles in the as-cast condition using ultrasonic waves to detect internal flaws, comprising modification of grain structure in the as-solidified ingot structure by the addition of trace boron to various titanium alloys. The ability to ultrasonically inspect as-cast billets combined with improved hot workability provided by trace boron enhancement permits an economical method of manufacture of titanium alloy articles destined for high performance applications. | 12-04-2014 |
20140373355 | METHOD FOR MANUFACTURING FAN ROTOR - An exemplary method for manufacturing a fan rotor includes the following steps. First, a discoid-shaped metal sheet is provided. Second, the metal sheet is stamped such that the stamped metal sheet includes a hub at a middle thereof, a blade-portion spaced from and surrounding the hub, and supporting bars interconnecting the hub and the blade-portion. The blade-portion includes outer peripheral blades adjacent to each other. Third, a free end of each blade is curled up by force applied along a direction substantially perpendicular to a plane of the blade-portion. Finally, each blade is bent downward about an axis coinciding with a portion of one side of the blade that connects with an inner periphery of the blade-portion. | 12-25-2014 |
20150089809 | SCALING TO CUSTOM-SIZED TURBOMACHINE AIRFOIL METHOD - A method of engineering a turbomachine airfoil may include providing a master airfoil configuration having a preset outer and inner radius relative to an axis of rotation thereof. The master airfoil configuration may be radially scaled to a custom-sized turbomachine airfoil having an outer radius different than the preset outer radius of the master airfoil configuration, and/or an inner radius different than the preset inner radius of the master airfoil configuration. Tuning a frequency of the custom-sized turbomachine airfoil by changing a parameter of at least one of a part span shroud and a tip shroud may then be performed. Axial scaling may also be performed. The custom-sized turbomachine airfoil may be employed in the turbomachine without performing wheel box testing, and may exhibit substantially similar operational characteristics as the master airfoil configuration. | 04-02-2015 |
20150143696 | APPARATUS FOR ASSEMBLING BLADE SECTIONS - An apparatus for assembling blade sections for forming a blade is provided. The apparatus comprises at least two members ( | 05-28-2015 |
20160010461 | METHOD FOR DETUNING A ROTOR-BLADE CASCADE | 01-14-2016 |
20160031049 | METHOD FOR NEW PRODUCTION OF A DIFFUSER IN A LASER SYSTEM - By previous inclusion of a through-hole in a substrate before coating and subsequent removal, the processing times for producing a through-hole with a diffuser are shortened and thereby the intermediate layers are less stressed. | 02-04-2016 |
20160031050 | BACKSTRIKE PROTECTION DURING MACHINING OF COOLING FEATURES - A method of machining a component is provided. The component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one interior space. A core is disposed within each interior space. The method includes forming at least one hole in the substrate while the core is disposed within the respective interior space. Each hole extends through the substrate to provide fluid communication with the respective interior space. The method further includes removing the core from the respective interior space. The core may be a casting core or a subsequently formed core. | 02-04-2016 |
20160089754 | MANUFACTURING SYSTEM AND METHOD FOR FABRICATING A COMPONENT - Provided are a manufacturing system and a method for fabricating a component. The manufacturing system includes a wire delivery assembly arranged and disposed to deliver a wire feed to a fabrication assembly arrangement; the fabrication assembly arrangement includes a wire manipulation assembly, the wire manipulation assembly being arranged and disposed to convert the wire feed into a wire segment and position the wire segment on a workpiece positioner to form a workpiece stack; an energy beam source assembly arranged and disposed to direct one or more energy beams toward one or more aligned surfaces of adjacent wire segments within the workpiece stack, to weld the wire segments together. The method includes delivering a wire feed to a fabrication assembly; cutting and positioning a wire segment; and directing an energy beam toward one or more aligned surfaces of adjacent wire segments to weld the wire segments together. | 03-31-2016 |
20160108505 | METHOD FOR PRODUCING STARTING MATERIAL FOR CUTTING - A method for producing a starting material for cutting capable of sufficiently eliminating residual stress is provided. The present invention is for producing a starting material for cutting which is a starting material for cutting to be cut/machined into a cut/machined product. The present invention includes a step for obtaining a primary molded article ( | 04-21-2016 |
20160138402 | ENGINE AIRFOILS AND METHODS FOR REDUCING AIRFOIL FLUTTER - A method is provided for designing an airfoil. The method includes considering a baseline airfoil having a first camber distribution and a first aerodynamic efficiency; reducing the first camber distribution to result in a reduced camber airfoil with a second camber distribution and a second aerodynamic efficiency such that the second aerodynamic efficiency is approximately equal to the first aerodynamic efficiency; and producing the airfoil with the second camber distribution | 05-19-2016 |
20160201481 | METHOD OF FABRICATING A REINFORCING EDGE FOR A BLADE AND REINFORCING EDGE OBTAINED BY THE METHOD | 07-14-2016 |
20220134493 | ASSEMBLY OF AN OUTLET GUIDE VANE FOR AN AIRCRAFT TURBOMACHINE USING AN INFLATABLE BLADDER - A method of assembling a member and a cap of a vane using a tool which allows the application of a pressing force of the cap against the member during a step of polymerisation by heating a resin for bonding these components. To this end, the tool includes an inflatable bladder and a pocket which surrounds the bladder and the vane so that the inflated bladder applies the pressing force. The heating can be carried out by resistors which are mounted in the bladder and/or using a device for supplying external heat. | 05-05-2022 |