Blade Making Patents (Class 29/889.7)
  • Publication number: 20150098832
    Abstract: 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: Application
    Filed: October 9, 2013
    Publication date: April 9, 2015
    Applicant: General Electric Company
    Inventors: Bradley Scott Carter, Michael Anthony Wondrasek
  • Publication number: 20150089809
    Abstract: 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: Application
    Filed: September 27, 2013
    Publication date: April 2, 2015
    Applicant: General Electric Company
    Inventors: Tao Guo, Michael Ernest Boisclair, Joseph Anthony Cotroneo, Carl Douglas Hofer, Amir Mujezinovic, Vsevolod Yuriyevich Ostrovskiy
  • Patent number: 8991021
    Abstract: 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: Grant
    Filed: June 1, 2011
    Date of Patent: March 31, 2015
    Assignee: Snecma
    Inventors: Damien Hebuterne, Janvier Lecomte
  • Publication number: 20150078913
    Abstract: 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: Application
    Filed: August 11, 2014
    Publication date: March 19, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventors: Peder Bay Enevoldsen, Stefan Oerlemans
  • Publication number: 20150075178
    Abstract: 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: Application
    Filed: September 17, 2013
    Publication date: March 19, 2015
    Inventors: Steve Halfmann, Mark C. Morris, Jason Smoke, Brandan Wakefield, Bob Mitlin
  • Patent number: 8978249
    Abstract: 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: Grant
    Filed: October 29, 2010
    Date of Patent: March 17, 2015
    Assignee: Alstom Technology Ltd.
    Inventors: Simone Hövel, Günter Ambrosy, Matthias Höbel
  • Patent number: 8956487
    Abstract: 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: Grant
    Filed: July 20, 2011
    Date of Patent: February 17, 2015
    Assignee: SNECMA
    Inventor: Francois Gallet
  • Patent number: 8955206
    Abstract: 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: Grant
    Filed: October 6, 2011
    Date of Patent: February 17, 2015
    Assignee: The Boeing Company
    Inventor: Jeffrey L. Miller
  • Publication number: 20150044048
    Abstract: 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: Application
    Filed: May 13, 2014
    Publication date: February 12, 2015
    Applicant: SAMSUNG TECHWIN CO., LTD.
    Inventor: Jong Kee AHN
  • Publication number: 20150044052
    Abstract: 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: Application
    Filed: November 14, 2013
    Publication date: February 12, 2015
    Applicant: United Technologies Corporation
    Inventors: Edwin M. Worth, Thomas G. Tillman, Frederick M. Schwarz
  • Publication number: 20150044057
    Abstract: 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: Application
    Filed: August 12, 2013
    Publication date: February 12, 2015
    Inventor: Jay G. Dinnison
  • Patent number: 8950070
    Abstract: 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: Grant
    Filed: July 9, 2012
    Date of Patent: February 10, 2015
    Assignee: Daido Steel Co., Ltd.
    Inventors: Koji Kimura, Takuma Okajima
  • Patent number: 8951008
    Abstract: 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: Grant
    Filed: June 20, 2005
    Date of Patent: February 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Christian Cornelius, Bernhard Küsters, Stephan Mais, Andreas Peters, Achim Schirrmacher, Lutz Stephan, Bernd van den Toorn
  • Patent number: 8938879
    Abstract: 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: Grant
    Filed: July 30, 2013
    Date of Patent: January 27, 2015
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Publication number: 20150023791
    Abstract: 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: Application
    Filed: March 6, 2013
    Publication date: January 22, 2015
    Inventors: Omar Sadi, Andreas Gross, Lothar Ernemann, Frieder Lörcher
  • Publication number: 20150017005
    Abstract: 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: Application
    Filed: July 2, 2014
    Publication date: January 15, 2015
    Applicant: SNECMA
    Inventors: Sylvain DOUSSEAUD, Gregory Nicolas, Gerald Gillant
  • Publication number: 20150010406
    Abstract: 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: Application
    Filed: March 9, 2014
    Publication date: January 8, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventor: Sigmund Wenningsted Torgard
  • Patent number: 8925200
    Abstract: 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: Grant
    Filed: March 27, 2008
    Date of Patent: January 6, 2015
    Assignee: United Technologies Corporation
    Inventors: Timothy P. Hasselberg, James J. Moor, David A. Gaudreau
  • Publication number: 20150003995
    Abstract: A method for making a component according to one embodiment of this disclosure includes modeling a response of the component to operating conditions. The model is then mapped to materials that would influence the response of the component to the operating conditions. A component is then fabricated using the materials such that the component includes a graded composition.
    Type: Application
    Filed: November 14, 2012
    Publication date: January 1, 2015
    Applicant: United Technologies Corporation
    Inventor: JinQuan Xu
  • Patent number: 8918995
    Abstract: A method of repairing a damaged notch fillet radius of a turbine blade shroud includes a replacement notch fillet radius and a hardface nugget. The damaged notch fillet radius is blended out and a hardface structure positioned proximate the damaged notch fillet radius is removed. A replacement notch fillet radius is formed with weld filler and the hardface nugget is welded to at least a portion of the replacement notch fillet radius.
    Type: Grant
    Filed: March 25, 2011
    Date of Patent: December 30, 2014
    Assignee: United Technologies Corporation
    Inventor: Timothy A. Milleville
  • Patent number: 8918997
    Abstract: 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.
    Type: Grant
    Filed: October 13, 2011
    Date of Patent: December 30, 2014
    Assignee: General Electric Company
    Inventors: Steven Alan Kyriakides, Scott Gabell Riddell, Alan Majors Walker
  • Publication number: 20140373503
    Abstract: An automated technique for finishing gas turbine engine blades or vanes by generating a bespoke tooling path for each blade or vane. The bespoke tooling path is generated by scanning the aerofoil surface to generate a 3-D electronic representation of the surface. The 3-D electronic surface is then analysed to identify imperfections or defects, and then a machining path a generated through which the imperfections can be removed. The machining path is determined so as to smoothly blend the surface back to the underlying surface where the imperfections had been present. In this way, the resulting aerofoil, once machined, has optimized aerodynamic performance.
    Type: Application
    Filed: June 11, 2014
    Publication date: December 25, 2014
    Inventor: Roisin Louise HANLON
  • Publication number: 20140373355
    Abstract: 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.
    Type: Application
    Filed: August 9, 2013
    Publication date: December 25, 2014
  • Publication number: 20140369844
    Abstract: A method of machining a blade in a three-dimensional machining center, the blade including an airfoil, a platform including upstream and downstream supports formed respectively under the upstream and downstream portions thereof for supporting a sealing liner, a blade root, and a stilt interposed between the platform and the blade root, the method including the upstream and downstream supports constituting two bearing points for a six-point positioning system for positioning the blade in the three-dimensional machining center.
    Type: Application
    Filed: January 24, 2013
    Publication date: December 18, 2014
    Applicant: SNECMA
    Inventors: Michael Hansom, Huu-Thanh Tran, Christian Bariaud
  • Publication number: 20140369841
    Abstract: A blade for a water current turbine rotor, which extends along a radial direction and comprises an outer surface, an inner surface, a leading edge, and a trailing edge. The leading edge is the edge of the blade that extends along the radial direction and is disposed upstream in the direction in which the water flows along the blade, while the trailing edge is the edge of the blade opposite the leading edge and is disposed downstream in the direction of flow. At least one portion of the blade has a profile comprising a thick portion and a thin portion, the cross section being perpendicular to the radial direction. The thick portion and the thin portion each have a maximum thickness along a direction perpendicular to the outer surface, the maximum thickness of the thick portion being at least four times greater than the maximum thickness of the thin portion.
    Type: Application
    Filed: January 24, 2013
    Publication date: December 18, 2014
    Applicant: GE Energy Power Conversion Technology Ltd.
    Inventors: Hugo Duchene, Philippe Cagnin, Antoine Girard-Pecarrere
  • Publication number: 20140363303
    Abstract: A hybrid turbine blade having a box beam assembly structure and method of designing such a hybrid turbine blade are disclosed. The box beam assembly provides the primary structure for supporting loads on the blade, and comprises oppositely positioned spar caps joined by oppositely positioned shear webs. For a portion of the blade, the box beam assembly further comprises a root buildup. In one embodiment, the shear webs comprise foam core sandwiched between two biaxial fiber-reinforced plastic laminates (FRP), the spar caps comprise uniaxial FRP laminates, and the root buildup comprises triaxial FRP laminates. The blades are designed using a novel inside-out method, wherein the box beam is first designed to support expected loads, and an aerodynamic surface is then designed to be supported by the box beam. The blade may be constructed in segments that are joined with connectors that engage the box beam structure.
    Type: Application
    Filed: June 4, 2014
    Publication date: December 11, 2014
    Applicant: The Regents of the University of California
    Inventors: Perry M. Roth-Johnson, Richard E. Wirz
  • Publication number: 20140356148
    Abstract: Provided is a radial vane with which manufacturing is possible with superior economy, without incurring a cut loss associated with vane separation in a weld part of a thread bundle With a longitudinal intermediate part of a contiguous bundle of threads being a fold-over part, both end parts of the fold-over part of the thread bundle are opened into radial shapes and superpositioned, leaving a space in the center part of the fold-over part, a ring-shaped fold-over part (12) is formed within the circumference of the space in the center part thereof. The outer part of the ring-shaped fold-over part (12) is welded in a ring shape, forming a ring-shaped core part (13). A through hole (11) is formed in the inner side of the fold-over part (12), and radial vane parts (14) are formed in which a plurality of thread materials (21) extend outward from the core part (13) toward the outer circumference side from all regions of the circumference direction.
    Type: Application
    Filed: January 25, 2013
    Publication date: December 4, 2014
    Inventors: Izumi Higuchi, Yasushi Ueba, Hideaki Nishimura, Masaki Higuchi
  • Publication number: 20140356168
    Abstract: In one aspect, a flexible fan blade for use in a centrifugal fan impeller having at least one of a rear plate and a front plate with an air inlet is provided. The flexible fan blade comprises a fixed central portion fixedly coupled to at least one of the front plate and the rear plate of the centrifugal fan impeller. The flexible fan blade also includes a trailing edge extending from the fixed central portion and being moveable between a first position and a second position. The trailing edge is fabricated from a compliant material. Furthermore, the trailing edge is flexible in relation to the fixed central portion between a first position and a second position. The flexible fan blade also includes a leading edge extending from the fixed central portion in opposed relation to the trailing edge.
    Type: Application
    Filed: March 15, 2013
    Publication date: December 4, 2014
    Applicant: Regal Beloit America, Inc.
    Inventor: Regal Beloit America, Inc.
  • Publication number: 20140352148
    Abstract: 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.
    Type: Application
    Filed: May 16, 2014
    Publication date: December 4, 2014
    Applicant: RTI International Metals, Inc.
    Inventor: Sesh Tamirisakandala
  • Publication number: 20140356176
    Abstract: A rotor blade assembly for a wind turbine having a rigid root insert is disclosed. The rotor blade assembly includes a blade root section having an end face with a substantially annular cross-section defined by an outer sidewall surface and an inner sidewall surface. The end face is configured to attach the rotor blade assembly to a hub. The rotor blade assembly includes a radial bore hole provided a predetermined span-wise distance from the end face and extending between the sidewall surfaces and a longitudinal bore hole provided between the sidewall surfaces and extending from the end face to the radial bore hole. The rigid root insert is disposed within the longitudinal bore hole and extends from the end face to the radial bore hole. As such, the rigid root insert is configured to increase the stiffness of the blade root section when the rotor blade assembly is attached to the hub with bolts that extend into and through the radial bore hole and the longitudinal bore hole.
    Type: Application
    Filed: May 31, 2013
    Publication date: December 4, 2014
    Applicant: General Electric Company
    Inventor: Christopher Daniel Caruso
  • Publication number: 20140348657
    Abstract: A blade (1) for a turbomachine, including an impact chamber (2), a single impulse body (3) being situated in the impact chamber, a clearance (S1+S2) between the impulse body and the impact chamber being at least 10 ?m and/or at most 1.5 mm in at least one direction.
    Type: Application
    Filed: May 21, 2014
    Publication date: November 27, 2014
    Inventors: Frank Stiehler, Andreas Hartung
  • Publication number: 20140341738
    Abstract: A wind turbine blade comprising a lightning protection system is provided. The lightning protection system comprises a lightning conductor located along a longitudinal portion of the wind turbine blade and is coupled to an electrical ground. A lightning receptor module is arranged on an external surface of the wind turbine blade and electrically coupled to the lightning conductor. An elongate receptor band is installed on the external surface of the wind turbine blade, over the lightning receptor module, and the receptor band is arranged to receive a stroke of lightning and transfer electrical current from the lightning stroke to the lightning conductor through the lightning receptor module. Further, the elongate receptor band comprises a crease in a longitudinal cross-sectional profile of the elongate receptor band. A method of installing a lightning protection system on a wind turbine blade is further provided.
    Type: Application
    Filed: December 14, 2012
    Publication date: November 20, 2014
    Inventors: Anton Bech, Henrik Aarup, Michael Heuer, Sonke Harders
  • Publication number: 20140341743
    Abstract: Methods for modifying a turbine buckets include removing at least an original outer edge for an entire length of the slash face of the turbine bucket and adding a new material to the slash face to build a new outer edge, wherein the new outer edge extends the entire length of the slash face.
    Type: Application
    Filed: May 15, 2013
    Publication date: November 20, 2014
    Applicant: General Electric Company
    Inventors: James Ryan Connor, John David Ward, JR., Mark Lawrence Hunt, Robert Trent Hullender
  • Patent number: 8884182
    Abstract: A method of modifying an end wall contour is provided. The method includes creating a weld pool using a laser, adding a metal or a ceramic powder or a wire filler to the melt pool and modifying the part of the turbine in a manner that results in a change of about 0.005 to about 50 volume percent in the part of the turbine. The weld pool is created on a turbine component and contains molten metal or ceramic derived as a result of a heat interaction between the laser and the turbine component.
    Type: Grant
    Filed: December 11, 2006
    Date of Patent: November 11, 2014
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Hsin-Pang Wang, Ronald Scott Bunker, Sudhir Kumar Tewari, Magdi Naim Azer
  • Patent number: 8881397
    Abstract: A method for designing an air cooled turbine airfoil includes selecting a number of different internal cooling air circuits, forming a ceramic core for each of the different cooling air circuits, forming a metal airfoil over each of the ceramic cores, leaching away the ceramic cores, mounting the airfoils in a stage of a turbine, passing a hot gas stream through the turbine, passing cooling air through each of the airfoils, and measuring a pressure and temperature differential across each of the airfoils to determine which cooling air circuit has the best performance.
    Type: Grant
    Filed: October 16, 2012
    Date of Patent: November 11, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Adam R Dowd
  • Publication number: 20140325841
    Abstract: 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.
    Type: Application
    Filed: December 5, 2012
    Publication date: November 6, 2014
    Applicant: SNECMA
    Inventor: Gerard Derrien
  • Patent number: 8875393
    Abstract: A method for forming at least one cooling channel in a wall which is cooled by cool air flowing in the channel is provided. The channel includes a hole and a diffusion portion, the hole opening out at one end into the inside surface of the wall, and at its other end into the diffusion portion where it forms an orifice. The diffusion portion flares around the orifice and opens out into the outside surface of the wall. The diffusion portion has a bottom whose front end is substantially plane, sloping, and extending in front of the orifice, and also has a margin extending behind, round the sides, and in front of the orifice, the margin joining the sides of the front end.
    Type: Grant
    Filed: May 26, 2010
    Date of Patent: November 4, 2014
    Assignee: SNECMA
    Inventors: Emmanuel Pierre Camhi, Laurent Crouilbois, Jean Pierre Mareix, Didier Pasquiet
  • Patent number: 8869378
    Abstract: A manufacturing process of a monobloc vaned disc including a cutout by abrasive water jet, including: a continuous cutout, with an ejection head of a tool opposite a first face of the block, of a piece passing through the thickness of the block, the continuous cutout revealing a junction line between a second face of the block opposite the first, and the surface of the block cut out by the abrasive water jet; followed by at least one enhancement cutout, with the ejection head opposite the second face of the block, of a piece extending only over part of the thickness of the block, and integrating at least part of the junction line.
    Type: Grant
    Filed: August 5, 2010
    Date of Patent: October 28, 2014
    Assignee: SNECMA
    Inventors: Perrine de la Rupelle, Serge Berlanger, Mitch Miller, William Pearson, Mark Stromberg
  • Patent number: 8869397
    Abstract: A method reinforcing an axisymmetric annular metal part by including a winding of composite material. A metal blank for the part is prepared, a cavity is formed therein that opens out into a coaxial inside face thereof, and that presents a right cross-section of axial extent that decreases from the inside towards the outside, a reinforcing yarn is wound in the cavity, the cavity is closed, the assembly is subjected to a hot isostatic compression process, and the blank is machined to obtain a final part.
    Type: Grant
    Filed: June 14, 2010
    Date of Patent: October 28, 2014
    Assignee: Messier-Bugatti-Dowty
    Inventors: Patrick Dunleavy, Jean-Michel Patrick Maurice Franchet, Gilles Charles Casimir Klein, Richard Masson
  • Publication number: 20140314576
    Abstract: A wind turbine blade holding arrangement is described comprising a root frame for securing to a root portion of a blade; an airfoil clamp for arranging about an airfoil portion of the blade; and an airfoil frame for supporting the airfoil clamp wherein the root frame and tip clamp are realized for use in a first blade orientation in a first storage and transport stage of the blade and also for use in a second blade orientation in a second storage and transport stage of the blade, wherein the first and second blade orientations are essentially at right angles to each other. A method of handling a number of wind turbine blades is also described.
    Type: Application
    Filed: February 4, 2014
    Publication date: October 23, 2014
  • Patent number: 8863382
    Abstract: A wind turbine rotor blade and a wind turbine incorporating the rotor blade include a first and second composite skin. A first and a second spar pultrusion having a base and a plurality of integral ribs generally normal to base are attached to the inside surface of the first and second composite skins and extend the span of the rotor blade. At least one shear web connects a rib of the first spar pultrusion to a corresponding rib of the second spar pultrusion. The width of the spar pultrusions decreases in a step-wise fashion along the span of the rotor blade from the root to the tip. The leading or trailing edge of the rotor blade may be selectably opened for inspection and repair.
    Type: Grant
    Filed: January 24, 2012
    Date of Patent: October 21, 2014
    Assignee: Piasecki Aircraft Corp.
    Inventor: Frederick W Piasecki
  • Publication number: 20140308132
    Abstract: Disclosed are a shroud impeller of a centrifugal compressor and a method of manufacturing the same where the shroud impeller includes a rotary hub connected to a driving shaft, a plurality of blades radially provided about a rotational axis of the rotary hub, and an integral shroud bonded onto top ends of the blades.
    Type: Application
    Filed: June 24, 2013
    Publication date: October 16, 2014
    Inventors: Kyung Kook KIM, Sang Eon LEE
  • Patent number: 8858183
    Abstract: A rotor blade for a rotary-wing aircraft includes a core member having a first end that extends to a second end, and a spar member positioned about the core member. The spar member includes a first end section that extends to a second end section. A tip core assembly is mounted at the second end section of the spar member. The tip core assembly is formed from a honeycombed material. The rotor blade also includes a rotor blade skin mounted about the spar member and the tip core assembly.
    Type: Grant
    Filed: December 3, 2010
    Date of Patent: October 14, 2014
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Richard Joseph Simkulak, Kevin P. Leahy, Frank Caputo, Daniel Ciesielski
  • Patent number: 8857054
    Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels.
    Type: Grant
    Filed: July 7, 2008
    Date of Patent: October 14, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Keith C. Goldfinch, Oliver M. Strother, Julian MacKechnie-Jarvis
  • Patent number: 8857055
    Abstract: A process is provided for forming shaped air holes, such as for use in turbine blades. Aspects of the disclosure relate to forming shaped portions of air holes using a short pulse laser, forming a metered hole corresponding to each shaped portion, and separately finishing the shaped portion using a short-pulse laser. In other embodiments, the order of these operations may be varied, such as to form the shaped portions and to finish the shaped portions using the short-pulse laser prior to forming the corresponding metered holes.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: October 14, 2014
    Assignee: General Electric Company
    Inventors: Bin Wei, Jon Conrad Schaeffer, Ronald Scott Bunker, Wenwu Zhang, Kathleen Blanche Morey, Jane Marie Lipkin, Benjamin Paul Lacy, Wilbur Douglas Scheidt
  • Publication number: 20140298651
    Abstract: 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.
    Type: Application
    Filed: November 2, 2012
    Publication date: October 9, 2014
    Applicant: GE AVIO S.r.L.
    Inventor: Francesco Bertini
  • Patent number: 8850703
    Abstract: With a method for finish-machining the blade tips of rotor wheels made in BLISK design, the rotor wheel or multi-stage compressor rotor (1), is machined—blade by blade and stage by stage—at the blade tips (2) by a conical cutter (5) whose cutting edge (6) is oriented tangentially to the outside surface of the rotor wheel/compressor rotor and routed on the blade tip essentially along the centerline thereof, with the cutting force being introduced perpendicular to the tool axis and in the stiffest direction of the blade (3), i.e. the centerline (11) of the blade cross-section and the perpendicular axis extending from the centerline. The cutting action and the force introduction of the conical cutter at the blade tip allow production of blade tips with a geometrically precisely defined edge without setting the respective blades into vibration.
    Type: Grant
    Filed: January 12, 2010
    Date of Patent: October 7, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Leping Zhu, Gregor Riedel
  • Publication number: 20140294567
    Abstract: A guide vane for a turbomachine axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine; and a trailing edge gap being formed between an upper trailing edge of the guide vane and the flow-limiting wall and/or between a lower trailing edge of the guide vane and the inner ring; the upper trailing edge and/or the lower trailing edge of the guide vane having at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge and/or the lower trailing edge in the area of the lower trailing edge. Also, a guide vane cascade, as well as a method for manufacturing a guide vane or a guide vane cascade.
    Type: Application
    Filed: April 1, 2014
    Publication date: October 2, 2014
    Inventor: Georg ZOTZ
  • Patent number: 8844132
    Abstract: 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.
    Type: Grant
    Filed: July 22, 2011
    Date of Patent: September 30, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Mario Blais, Michel Bellerose
  • Publication number: 20140286785
    Abstract: A method of producing an airfoil is provided. The method includes forming a steel airfoil preform with a pocket on at least one of the pressure and suction surfaces, forming a cover plate for the pocket and welding the cover plate over the pocket.
    Type: Application
    Filed: March 8, 2013
    Publication date: September 25, 2014
    Inventor: General Electric Company