Blade Making Patents (Class 29/889.7)
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Patent number: 10066492Abstract: A turbomachine blade having a metal coupling root, and a metal airfoil-shaped oblong member cantilevered projecting from the coupling root; the airfoil-shaped oblong member being divided into: a lower connecting fin cantilevered projecting from and formed in one piece with the coupling root; an upper connecting fin cantilevered projecting from a coupling head towards the coupling root and formed in one piece with the coupling head; and a main plate-like body which is shaped and positioned between the two connecting fins to form an extension of the fins, and is butt-welded to the same connecting fins to form one piece with the fins.Type: GrantFiled: March 7, 2017Date of Patent: September 4, 2018Assignee: Pietro Rosa T.B.M. S.r.l.Inventor: Andrea Maurizio
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Patent number: 10060277Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly to couple the blades to the rotor disk.Type: GrantFiled: December 18, 2015Date of Patent: August 28, 2018Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce CorporationInventors: Todd Z. Engel, Ted J. Freeman, Robert J. Shinavski, Ian Thomson
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Patent number: 10046482Abstract: A method of fabricating a turbine engine blade out of composite material including fiber reinforcement densified by a matrix, the method including using multilayer weaving to make a first fiber that has a first portion forming a blade root preform and extended by a second portion, the second portion forming a tenon preform; using multilayer weaving to make a second fiber preform, the second preform including a first portion made up of two skins defining between them an internal housing, the first portion forming an airfoil preform, and a second portion extending from an outside surface of the skins, the second portion forming a platform preform; assembling the first preform with the second preform in the non-consolidated state by engaging the second portion of the first preform in the internal housing; and co-densifying the first and second preforms as assembled together in this way to obtain a turbine engine blade.Type: GrantFiled: February 9, 2016Date of Patent: August 14, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: David Marsal, Clément Roussille, Jérémy Blachier
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Patent number: 10047612Abstract: A method and device for manufacturing turbine blades (5; 7; 28; 33) made of a metal alloy. Starting with aluminum and titanium alloy bar (10; 34) having a simple and/or axisymmetric shape, at least two mutually interlocking blanks (2; 3; 4; 8; 11) are produced in the bar (10; 34) by waterjet cutting (16) and then each one of the blanks (2; 3; 4; 8; 11) thus obtained is machined separately in order to obtain the blades (5; 7; 28; 33) having a final profile.Type: GrantFiled: November 8, 2013Date of Patent: August 14, 2018Assignee: Mechachrome FranceInventors: Arnaud De Ponnat, Olivier Martin
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Patent number: 10012976Abstract: A method for manufacturing a turbine engine blade including an airfoil with a profile defined by a theoretical digital model, the method including: manufacturing a blank having a thickened portion along a trailing edge of the airfoil relative to the theoretical profile; removing the thickened portion by adaptive machining, including: positioning the blank in a reference frame; acquiring, by probing at a predetermined number of points on a first surface of the blank along the trailing edge, positions of the points in the reference frame; determining differences, in one direction, in position from corresponding points of the theoretical model; producing machining grids on the blank surface, peaks of the grids determined from the points; determining an amount of material to be removed from the surface of the grids, based on the position of the points relative to the peaks and the deviations in position; and machining the airfoil.Type: GrantFiled: April 22, 2013Date of Patent: July 3, 2018Assignee: SNECMAInventors: Yvon Marie-Joseph Louesdon, Florian Le Merdi, Joseph Tami, Daniel Quach, Fadoua Cisse, Sabine Maltaverne, Damien Alquier
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Patent number: 9938833Abstract: Methods, systems, and devices for designing and manufacturing flank millable components. In one embodiment, devices, systems, and methods for designing a flank millable component are provided, in which a user is notified when a component geometry option is selected that will result in the component not being flank millable. In another embodiment, the user is prevented from selecting a geometry option that would result in the component not being flank millable. In yet another embodiment, devices, systems, and methods are provided for manufacturing a component with a flank milling process, in which optimized machine instructions are determined that minimize milling machine motion.Type: GrantFiled: September 29, 2016Date of Patent: April 10, 2018Assignee: Concepts NREC, LLCInventors: Derek J. Cooper, Alexander Plomp, David Japikse
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Patent number: 9932661Abstract: Disclosed is a process for producing a high-temperature protective coating for metallic components, in particular components of turbomachines which are subjected to thermal loading. The process comprises producing a slip from MCrAlY powder, in which M is at least one metal, and from a Cr powder, applying the slip to the component to be coated and subsequently alitizing the component provided with the slip.Type: GrantFiled: April 23, 2014Date of Patent: April 3, 2018Assignee: MTU AERO ENGINES AGInventor: Heinrich Walter
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Patent number: 9919457Abstract: A method for forming a preform for a hollow turbomachine component is provided. The method includes positioning a sheet made of woven fibers on a base equipped with a longitudinal impression; positioning a mandrel in the longitudinal impression to clamp the sheet between the base and the mandrel, the mandrel having a thickness that increases between a proximal end and a distal end; locking the distal end of the mandrel into position; placing a proximal block resting on the base; forming two flaps of the sheet around the flanks of the mandrel; resting two lateral blocks on the base on either side of the mandrel; locking the lateral blocks into position to form an assembly; drying the assembly to form a preform including a flat base, from which two flaps extend perpendicularly; and adjusting the flaps to the dimensions of the mandrel by trimming excess material.Type: GrantFiled: August 14, 2013Date of Patent: March 20, 2018Assignee: SNECMAInventors: Richard Mathon, Dominique Magnaudeix, Noemie Souhaite, Yann Marchal, Matthieu Gimat
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Patent number: 9863254Abstract: A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion; and a film cooling hole having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion.Type: GrantFiled: April 23, 2013Date of Patent: January 9, 2018Assignee: General Electric CompanyInventors: Christopher Michael Ceglio, Randall Charles Bauer, Stephen Mark Molter, Mark Edward Stegemiller
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Patent number: 9835114Abstract: A method is provided for fabricating a coolant channel closeout jacket on a structure having coolant channels formed in an outer surface thereof. A line of tangency relative to the outer surface is defined for each point on the outer surface. Linear rows of a metal feedstock are directed towards and deposited on the outer surface of the structure as a beam of weld energy is directed to the metal feedstock so-deposited. A first angle between the metal feedstock so-directed and the line of tangency is maintained in a range of 20-90°. The beam is directed towards a portion of the linear rows such that less than 30% of the cross-sectional area of the beam impinges on a currently-deposited one of the linear rows. A second angle between the beam and the line of tangency is maintained in a range of 5-65°.Type: GrantFiled: June 6, 2017Date of Patent: December 5, 2017Assignee: The United States of America as Represented by the Administrator of NASAInventors: Paul R. Gradl, David Christopher Reynolds, Bryant H. Walker
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Patent number: 9752445Abstract: Coupled turbine vanes having an axis are produced by arranging a plurality of first fabrics of ceramic fibers in radial directions relative to the axis to constitute a plurality of vane sections, arranging a second fabric of the ceramic fibers in a circumferential direction relative to the axis, connecting the first fabrics with the second fabric by bending first ends of the first fabrics to lay them on the second fabric in parallel, and impregnating the plurality of first fabrics connected with the second fabric with the matrix.Type: GrantFiled: September 8, 2014Date of Patent: September 5, 2017Assignee: IHI CorporationInventor: Fumiaki Watanabe
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Patent number: 9624783Abstract: A turbomachine blade of the type having a metal lower coupling root, a metal upper coupling head, and a metal airfoil-shaped oblong member designed to connect the coupling root rigidly to the coupling head; the airfoil-shaped oblong member having a substantially airfoil-shaped main plate-like element connected to the coupling root and to the coupling head, and which is divided into: a lower connecting fin cantilevered from and formed in one piece with the coupling root; an upper connecting fin cantilevered from and formed in one piece with the coupling head; and a center plate-like body, which is located between the lower and upper connecting fins, is shaped/designed to form an extension of the lower and upper connecting fins, and is butt-welded to, to form one piece with, the lower and upper connecting fins.Type: GrantFiled: February 28, 2014Date of Patent: April 18, 2017Assignee: PIETRO ROSA T.B.M. S.R.L.Inventor: Andrea Maurizio
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Patent number: 9556745Abstract: A plate closes the main part of a vane in two parts. An internal cavity is closed by the plate. Around a bearing surface of the plate, a groove receives an elastic seal, and the outer edge of the plate extends over the groove to compress the seal and to establish excellent leak proofing. The position of the plate may be guaranteed by centring pins penetrating into holes adjacent to the seal and which it fills when the pins have been removed, which completes the closing of the cavity. The plate has application in particular to stationary gas guide vanes in turbine engines.Type: GrantFiled: July 17, 2012Date of Patent: January 31, 2017Assignee: SNECMAInventors: Thierry Georges Paul Papin, Lise Lacroix, Dominique Raulin
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Patent number: 9534498Abstract: A vane includes a platform with a fixture overmolded by a sheath.Type: GrantFiled: December 14, 2012Date of Patent: January 3, 2017Assignee: United Technologies CorporationInventor: David R. Lyders
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Patent number: 9479028Abstract: An automotive rotary electric machine has a cooling fan including a flat ring-shaped mounting base plate fixed to a rotor, and a plurality of fan blades arranged in a row circumferentially such that each stands on a surface of the mounting base plate, the fan blades having an S-shaped cross-sectional shape that displaces gradually forward in a direction of rotation from a trailing edge that is an outer circumferential edge toward a leading edge that is an inner circumferential edge, and in which an arc shape near the trailing edge that is convex forward in the direction of rotation and an arc shape near the leading edge that is convex rearward in the direction of rotation are connected smoothly.Type: GrantFiled: June 26, 2013Date of Patent: October 25, 2016Assignee: Mitsubishi Electric CorporationInventors: Masao Akiyoshi, Yuzuru Kobayashi, Kazunori Tanaka, Yoshihiro Shinosaka, Yoshiro Imazawa
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Patent number: 9346141Abstract: A joining device for arranging a component on a component carrier is disclosed. The joining device includes an application system for positioning the component in the joining device and a receptacle for clamping the component carrier in the joining device. The component is arranged on the component carrier by an adapter. A method for arranging the component on the component carrier is also disclosed.Type: GrantFiled: July 7, 2010Date of Patent: May 24, 2016Assignee: MTU Aero Engines GmbHInventors: Martin Fessler-Knobel, Roland Huttner
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Patent number: 9291151Abstract: The present invention provides a wind turbine blade of hybrid material composition, wherein the blade comprises a structural box mainly made of a epoxy based prepreg and a shell manufactured by resin infusion technique using polyester or vinylester, and the box and the shell are bonded using an adhesive that is not a polyester, a vinylester and an epoxy. The present invention also provides a method for producing such a blade.Type: GrantFiled: September 20, 2010Date of Patent: March 22, 2016Assignee: SUZHOU RED MAPLE WIND BLADE MOULD CO., LTD.Inventor: Gabriel Mironov
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Patent number: 9266166Abstract: Plural saddle shape patches are formed on a blank material for forming a blade using a manufacturing apparatus provided with a punch support having punches each with a holder attached to be opposite with one another at a predetermined interval corresponding to a thickness of the blank material. The punch support is mounted to a second ram via a second rotational mechanism which is rotatable in a direction in which the ram moves. The die is attached to the first ram via the first rotational mechanism. The actuator controls the rotating angles of both the rotational mechanisms.Type: GrantFiled: December 13, 2012Date of Patent: February 23, 2016Assignee: HITACHI, LTD.Inventors: Tetsuya Yagami, Toshiya Teramae, Koji Hayashi, Kazutoshi Yanagihara, Ryouichi Kataoka
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Patent number: 9228445Abstract: Hybrid turbine airfoil components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials. The components include a first component formed of a ceramic-based material and a second component formed of a metallic material. The first component comprises an airfoil portion and a nub, and the second component is separately formed and attached to the first component by casting the metallic material around the nub of the first component. The second component includes a platform portion between the airfoil portion and the nub of the first component and a dovetail portion on the nub of the first component. Each of the platform and dovetail portions has at least one off-axis geometric feature that results in the second component having a more complex geometry than the first component.Type: GrantFiled: December 23, 2010Date of Patent: January 5, 2016Assignee: General Electric CompanyInventors: Toby George Darkins, Jr., John Peter Heyward, Eric Alan Estill, Joshua Brian Jamison, James Herbert Deines, Mark Willard Marusko, James Thomas Hawkins
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Patent number: 9091277Abstract: Multipart shrouded impellers and methods for manufacturing multi-part shrouded impellers are described. Components of the shrouded impeller include alignment features that, when brought into contact, provide concentric and spatial alignment of the component parts. Upon alignment a gap remains between portions of the components, which permits the introduction of a filler material that joins the components into a unitized whole.Type: GrantFiled: April 25, 2014Date of Patent: July 28, 2015Assignee: Computer Assisted Manufacturing Technology CorporationInventor: Lance A. Young
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Publication number: 20150143696Abstract: An apparatus for assembling blade sections for forming a blade is provided. The apparatus comprises at least two members (1, 2) movable with respect to each other, said members having respective opposing surfaces (2A, 2B) forming a pressing space for pressing outer surfaces of preassembled blade sections in a transition between the sections.Type: ApplicationFiled: May 28, 2013Publication date: May 28, 2015Applicant: youWINenergy GmbHInventor: Rolf Rohden
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Publication number: 20150147180Abstract: Aerodynamic root adapters for rotor blades include an interior support section having a first end that connects to a root end of the rotor blade and a second end that connects to a rotor hub of the wind turbine, and, an aerodynamic exterior section supported by the interior support section. The aerodynamic exterior section thereby extends an aerodynamic profile of the rotor blade beyond the root end of the rotor blade to at least partially between the root end of the rotor blade and the rotor hub when the aerodynamic root adapter is connected thereto.Type: ApplicationFiled: November 22, 2013Publication date: May 28, 2015Applicant: General Electric CompanyInventors: Saravakota Sambamurty, Mohan Muthu Kumar Sivanantham, Afroz Akhtar
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Publication number: 20150139810Abstract: 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.Type: ApplicationFiled: November 20, 2013Publication date: May 21, 2015Applicant: General Electric CompanyInventor: Kevin Wayne Kinzie
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Publication number: 20150139789Abstract: An array of flow-directing elements for a compressor of a gas turbine including at least one first flow-directing element and at least one second flow-directing element different from the first flow-directing element; the flow-directing elements each having a leading edge facing the gas turbine inlet, a trailing edge, a pressure side connecting them and located ahead in the direction of rotation, a suction side located opposite thereof, as well as successive chords along a stacking axis; the flow-directing elements each extending between an airfoil root proximate to the rotor and an airfoil tip remote from the rotor. The trailing edge of the first flow-directing element is, at least in a portion thereof, axially offset from the trailing edge of the second flow-directing element in a direction toward the leading edge at least in a half proximate to the airfoil tip.Type: ApplicationFiled: October 7, 2014Publication date: May 21, 2015Inventor: Harald Schoenenborn
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Patent number: 9032622Abstract: An elongate web is attached to the root end of a spar of a wind turbine rotor blade to provide additional support along the width of the blade. The root end is formed by a winding operation, and a recess is then cut into the surface of the spar. The recess is defined by a relatively large first, cylindrical surface, which is coaxial with the longitudinal axis of the root end, and a relatively small second, conical surface. A tapered end of the elongate web is attached within the recess of the root end using a layer of suitable adhesive and an array of pins. Resilient spacer elements are arranged within the recess so as to surround the pins. The large area of the cylindrical surface causes the tensile and compressive stresses which arise along the elongate web in use to be transmitted to the spar as shear stresses.Type: GrantFiled: December 12, 2011Date of Patent: May 19, 2015Assignee: Vestas Wind Systems A/SInventors: Mark Hancock, Anton Bech, Rens Christiaan Verhoef, Adrian Gill, Karl Gregory
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Patent number: 9032621Abstract: A method for manufacturing a work piece is provided. The method includes preparing fiberglass in a mold, preparing a closed mold cavity around the fiberglass, flushing the closed mold cavity with an oxygen-free gas, injecting resin in the closed mold cavity, and curing the casted work piece. Furthermore, a work piece manufactured by the above method is provided.Type: GrantFiled: June 24, 2011Date of Patent: May 19, 2015Assignee: SIEMENS AKTIENGESELLSCHAFTInventor: Karsten Schibsbye
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Patent number: 9027245Abstract: A method for producing a solid component which in succession includes deforming a metal bar by forging using two dies in order to obtain an intermediate component including two fins one on each side of a solid part capable of forming the base of the metal reinforcement, the two fins being at a divergent angle ?; deforming the two fins of the intermediate component, altering the divergent angle ?, so as to obtain the final shape of the turbomachine blade leading edge or trailing edge metal reinforcement.Type: GrantFiled: June 23, 2011Date of Patent: May 12, 2015Assignee: SnecmaInventors: Christine Hottier, Bertrand Lamaison, Jacques Abousefian
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Publication number: 20150125308Abstract: A method of manufacturing a filled aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a pre-formed filler insert (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. The pre-formed filler insert (400) provides a lightweight core for the finished aerofoil component in use.Type: ApplicationFiled: September 2, 2014Publication date: May 7, 2015Inventor: Steven Aleksy RADOMSKI
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Publication number: 20150113779Abstract: The present invention provides a method for installing at least one sensor device within a rotor blade of a wind turbine. A first substantially planar light beam is emitted in the interior of the rotor blade. Finally, at least one second substantially planar light beam is emitted in the interior of the rotor blade, wherein the plane of the first planar light beam is oriented at a predetermined angle to the plane of the second planar light beam. Further, the planes of the first and second planar light beams are aligned on the blade flange of the rotor blade. At least one sensor device is subsequently aligned in reference to the planar light beams.Type: ApplicationFiled: June 4, 2013Publication date: April 30, 2015Inventors: Thorbjörn Buck, Lars Hoffmann, Mathias Müller, Rolf Wojtech
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Patent number: 9015942Abstract: A method of imparting deep compressive residual stress to an aerofoil, the method involves determining a stress map for the aerofoil for stress generated by Foreign Object (FOD) impact, a stress map for the aerofoil of high cycle fatigue, a stress map for the aerofoil of low cycle fatigue and determining a combined stress map by combining the stress map of FOD impact, the stress map of high cycle fatigue and the stress map of low cycle fatigue. A zone is then defined on the aerofoil from the combined stress map for receiving the deep residual compressive stress, and compressive residual stress imparted to the defined zone.Type: GrantFiled: June 28, 2012Date of Patent: April 28, 2015Assignee: ROLLS-ROYCE plcInventor: Ian C. D. Care
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Publication number: 20150110632Abstract: A blade assembly for a wind turbine rotor is provided, the blade assembly comprising at least two blade sections (1, 2) being longitudinally joinable at respective joining end portions (10, 20) for forming a blade. One of said blade sections has at least one cavity (11) in its joining end portion (10) and the other of said blade sections has at least one protrusion (21) at its joining end portion (20). Said cavity (11) is contractible to a contracted position in a direction which is substantially perpendicular to a longitudinal direction of the blade.Type: ApplicationFiled: May 28, 2013Publication date: April 23, 2015Applicant: youWINenergy GmbHInventor: Rolf Rohden
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Patent number: 9003657Abstract: A manufacturing method includes providing a substrate with an outer surface and at least one interior space and machining the substrate to selectively remove a portion of the substrate and define one or more cooling supply holes therein. Each of the one or more cooling supply holes is in fluid communication with the at least one interior space. The method further includes disposing an open cell porous metallic layer on at least a portion of the substrate. The open cell porous metallic layer is in fluid communication with the one or more cooling supply holes. A coating layer is disposed on the open cell porous metallic layer. The coating layer having formed therein one or more cooling exit holes in fluid communication with the open cell porous metallic layer. The substrate, the one or more cooling supply holes, the open cell porous metallic layer and the cooling exit holes providing a cooling network for a component.Type: GrantFiled: December 18, 2012Date of Patent: April 14, 2015Assignee: General Electric CompanyInventors: Ronald Scott Bunker, Scott Andrew Weaver, Wayne Charles Hasz
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Publication number: 20150098832Abstract: A system for relieving stress on a turbine rotor blade dovetail in a gas turbine is provided. At least one turbine rotor blade includes a dovetail that is axially insertable into a correspondingly-shaped slot defined in a turbine disk. At least one axially-extending tang is defined on the dovetail. At least one stress relief surface is defined in the at least one tang. The at least one stress relief surface extends along a central portion of a length of the tang. Accordingly, contact between the at least one tang and an inner surface of the slot is precluded, along the central portion, such that stresses generated by radially-directed forces along the central portion are reduced.Type: ApplicationFiled: October 9, 2013Publication date: April 9, 2015Applicant: General Electric CompanyInventors: Bradley Scott Carter, Michael Anthony Wondrasek
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Publication number: 20150089809Abstract: 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.Type: ApplicationFiled: September 27, 2013Publication date: April 2, 2015Applicant: General Electric CompanyInventors: Tao Guo, Michael Ernest Boisclair, Joseph Anthony Cotroneo, Carl Douglas Hofer, Amir Mujezinovic, Vsevolod Yuriyevich Ostrovskiy
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Patent number: 8991021Abstract: A method for machining at least one aircraft gas turbine engine rotor blade wear indicator is provided. The method includes machining the wear indicator using a laser so as to melt part of the blade, and collecting the molten material of the blade. The method further includes fitting a plug into the bathtub squealer. The plug includes at least one cavity for receiving the molten blade material.Type: GrantFiled: June 1, 2011Date of Patent: March 31, 2015Assignee: SnecmaInventors: Damien Hebuterne, Janvier Lecomte
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Publication number: 20150075178Abstract: A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform. The platform has a leading edge, a trailing edge, a suction side edge, and a pressure side edge. The pressure side edge includes a first concave portion.Type: ApplicationFiled: September 17, 2013Publication date: March 19, 2015Inventors: Steve Halfmann, Mark C. Morris, Jason Smoke, Brandan Wakefield, Bob Mitlin
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Publication number: 20150078913Abstract: An arrangement to reduce noise emission generated by a wind turbine rotor blade is provided. The arrangement includes the rotor blade and a noise reduction device attached thereto. The rotor blade has a suction side and pressure side, leading and trailing edge sections with a trailing edge. The noise reduction device has an inner surface facing the rotor blade trailing edge section, and an outer surface opposite to the inner surface. The noise reduction device has a leading and trailing edge, both connecting the inner and outer surface. The noise reduction device is connected at the rotor blade trailing edge section by a connector. The inner surface has a pre-defined distance to at least one side of the rotor blade chosen so acoustic waves generated at the rotor blade trailing edge section are reflected by the inner surface to reduce noise emission generated by the wind turbine rotor blade.Type: ApplicationFiled: August 11, 2014Publication date: March 19, 2015Applicant: Siemens AktiengesellschaftInventors: Peder Bay Enevoldsen, Stefan Oerlemans
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Patent number: 8978249Abstract: A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10).Type: GrantFiled: October 29, 2010Date of Patent: March 17, 2015Assignee: Alstom Technology Ltd.Inventors: Simone Hövel, Günter Ambrosy, Matthias Höbel
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Patent number: 8955206Abstract: A method for creating a layup of reinforcing fibers comprises mounting a face sheet to a spindle of a mandrel tool support, the face sheet having a layup surface for the reinforcing fibers, and counterbalancing the mounted face sheet for stiffness and center of balance.Type: GrantFiled: October 6, 2011Date of Patent: February 17, 2015Assignee: The Boeing CompanyInventor: Jeffrey L. Miller
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Patent number: 8956487Abstract: A rotor blade of a turbine engine comprising a body made of composite material consisting of a fiber-reinforced thermosetting resin and a connecting yoke designed to be attached to a fastener of a rotor disc of the said turbine engine, the said blade characterized in that the connecting yoke comprises a metal reinforcement and a casing made of composite material encasing the said reinforcement.Type: GrantFiled: July 20, 2011Date of Patent: February 17, 2015Assignee: SNECMAInventor: Francois Gallet
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Publication number: 20150044048Abstract: Provided is a method of manufacturing an impeller assembly, the method including providing an impeller including: a rotary shaft; a base portion radially extending outward from the rotary shaft; and a plurality of blades extending radially outward from the rotary shaft and disposed on the base portion, each of the plurality of blades provided apart from one another in a circumferential direction around the rotary shaft; providing a mold in an area between the plurality of blades; and forming a shroud covering upper portions of the plurality of blades and an upper portion of the mold, wherein the forming the shroud comprises applying a melted metal on the upper portions of the plurality of blades and the upper portion of the mold.Type: ApplicationFiled: May 13, 2014Publication date: February 12, 2015Applicant: SAMSUNG TECHWIN CO., LTD.Inventor: Jong Kee AHN
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Publication number: 20150044052Abstract: A fan blade comprises a main body having an airfoil extending between a leading edge and a trailing edge. The fan blade has at least one of a channel closed by a cover, and an end cap covering at least one of the leading and trailing edges. At least one of a cover and an end cap has a pair of opposed ends. A step is defined extending from at least one of a suction wall and a pressure wall of the airfoil, to an outer surface of the one of a cover and an end cap at one of the opposed ends, and the step being less than or equal to about 0.010 inch (0.0254 centimeter) in dimension.Type: ApplicationFiled: November 14, 2013Publication date: February 12, 2015Applicant: United Technologies CorporationInventors: Edwin M. Worth, Thomas G. Tillman, Frederick M. Schwarz
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Publication number: 20150044057Abstract: An impeller blade formed of a central base portion having a center axis. At least a pair of impeller blades is extended outwardly from the central base portion, with each impeller blade further including an extension. A leading edge is formed on each of the impeller blades, with each leading edge being defined by an outer periphery of the central base portion, and each leading edge having at least a portion that forms a continuous curve with a radius decreasing outwardly toward a radial tip of the corresponding impeller blade, wherein the continuous decreasing radius curve of each leading edge is formed by a portion of an ellipse centered on the center axis, a short axis of the ellipse being equal to a long axis thereof divided by approximately three and one-half. Each blade extension is projected from the corresponding impeller blade opposite of the leading edge.Type: ApplicationFiled: August 12, 2013Publication date: February 12, 2015Inventor: Jay G. Dinnison
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Patent number: 8951008Abstract: The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.Type: GrantFiled: June 20, 2005Date of Patent: February 10, 2015Assignee: Siemens AktiengesellschaftInventors: Christian Cornelius, Bernhard Küsters, Stephan Mais, Andreas Peters, Achim Schirrmacher, Lutz Stephan, Bernd van den Toorn
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Patent number: 8950070Abstract: 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.Type: GrantFiled: July 9, 2012Date of Patent: February 10, 2015Assignee: Daido Steel Co., Ltd.Inventors: Koji Kimura, Takuma Okajima
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Patent number: 8938879Abstract: A method of manufacturing a component is provided. The method includes forming one or more grooves in an outer surface of a substrate. Each groove extends at least partially along the surface of the substrate and has a base, a top and at least one discharge point. The method further includes forming a run-out region adjacent to the discharge point for each groove and disposing a coating over at least a portion of the surface of the substrate. The groove(s) and the coating define one or more channels for cooling the component. Components with cooling channels are also provided.Type: GrantFiled: July 30, 2013Date of Patent: January 27, 2015Assignee: General Electric CompanyInventor: Ronald Scott Bunker
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Publication number: 20150023791Abstract: The axial fan has a motor (1), on the rotor side of which an impeller is fixed, wherein fan blades (24) with a front and a rear edge (26, 27) project from the hub of said impeller. The motor (1) is fixed to a housing (3) by means of a suspension (2). The suspension has a bracing part (4 to 8) made of a flat material, said bracing part connecting the motor (1) to the housing (3) and being arranged in an approximately vertical manner in the flow direction of the air. The aim of the invention is to design the axial fan such that the axial fan has a high overall efficiency and only a low flow resistance. This is achieved in that the bracing part (4 to 8) is provided with at least one recess (7) over a part of the length of the bracing part. The flow resistance due to the bracing part is minimized by means of the recess. The recess reduces the weight of the axial fan.Type: ApplicationFiled: March 6, 2013Publication date: January 22, 2015Inventors: Omar Sadi, Andreas Gross, Lothar Ernemann, Frieder Lörcher
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Publication number: 20150017005Abstract: The invention relates to an insert for a turbine engine test vane including the insert and a vane body. The insert includes at least two external surfaces. The insert is configured to fit into the vane body, such that the external surfaces are vane aerodynamic surfaces each forming part of a vane aerodynamic profile.Type: ApplicationFiled: July 2, 2014Publication date: January 15, 2015Applicant: SNECMAInventors: Sylvain DOUSSEAUD, Gregory Nicolas, Gerald Gillant
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Publication number: 20150010406Abstract: A rotor blade with a supporting structure, wherein the rotor blade has a rotor blade base section and a rotor blade tip section, is provided. The supporting structure includes a first supporting segment for supporting the rotor blade base section and at least a second supporting segment for supporting the rotor blade tip section. Furthermore, the supporting structure includes the first supporting segment and the second supporting segment along the rotor blade longitudinal direction. The first supporting segment is joined to the second supporting segment in a supporting structure transition section, wherein the supporting structure transition section is located in between the rotor blade base section and the rotor blade tip section. Finally, the first supporting segment and/or the second supporting segment include a fibre material. A method for manufacturing the rotor blade is also provided.Type: ApplicationFiled: March 9, 2014Publication date: January 8, 2015Applicant: Siemens AktiengesellschaftInventor: Sigmund Wenningsted Torgard
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Patent number: 8925200Abstract: An example method of repairing an airfoil includes the steps of securing additional material to a worn airfoil and limiting movement of the additional material with a guide. The method alters some of the additional material to form a desired airfoil contour. Another example method of forming a portion of an airfoil includes the steps of securing additional material to an airfoil, limiting movement of the additional material with a guide, and altering some of the additional material to form a desired airfoil contour.Type: GrantFiled: March 27, 2008Date of Patent: January 6, 2015Assignee: United Technologies CorporationInventors: Timothy P. Hasselberg, James J. Moor, David A. Gaudreau