Patents Examined by Eldon Brockman
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Patent number: 9488192Abstract: An assembling and disassembling device for a compressor has a substantially cylindrical bundle that is received insertably and removably on an inner circumferential surface of a substantially tubular compressor casing that is mounted horizontally and further includes: a plate-like member that is provided on an axial end portion of the bundle at an opposite side of an insertion direction so as to protrude outward in a radial direction of the bundle and a threaded-rod member that inserts and removes the bundle connected to the plate-like member into and from the compressor casing by being screwed into a threaded hole provided in the plate-like member and being rotated.Type: GrantFiled: July 25, 2011Date of Patent: November 8, 2016Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATIONInventors: Mitsuhiko Ota, Hideki Yamada
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Patent number: 9481449Abstract: A blade, configured to be mounted on a hub of a turbomachine propeller so that an empty space is defined between a base of the blade and a face of the hub facing the base. The blade includes a retractable blanking mechanism configured to reversibly occupy at least one of following two positions: a deployed position in which the retractable blanking mechanism at least partially closes off the empty space; and an extreme retracted position in which the retractable mechanism is kept out of the empty space.Type: GrantFiled: June 19, 2012Date of Patent: November 1, 2016Assignee: SNECMAInventor: Sebastien Pascal
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Patent number: 9476427Abstract: A counter-rotating wet gas compressor for deployment and operation on the sea floor is described. The compressor has alternating rows of impellers, with each successive row of impellers being mounted a central hub or to an outer sleeve. According to some embodiments, no static diffusers are positioned between the alternating counter-rotating rows of impellers such that the design is structurally robust, compact and capable of compressing fluids that contain significant portions of liquid phase.Type: GrantFiled: November 28, 2012Date of Patent: October 25, 2016Assignee: FRAMO ENGINEERING ASInventors: Bernt Helge Torkildsen, Per Gunnar Vikre, Hans Frederik Kjellnes
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Patent number: 9476308Abstract: A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions. The first trip strips are arranged at a first spacing from one another. The second trip strips are arranged at a second spacing from one another. A turbulence promoter is arranged in the bend and at a third spacing from the first trip strips that is different than the first spacing. The turbulence promoter is arranged at a fourth spacing from the second trip strips that is different than the second spacing.Type: GrantFiled: December 27, 2012Date of Patent: October 25, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Travis Goeller, Erik R. Granstrand, Irwin D. Singer, Dominic J. Mongillo, Jr., Edward F. Pietraszkiewicz
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Patent number: 9476305Abstract: An integral turbine includes a forward hub section and an aft hub section. The forward hub section and the aft hub section are metallurgically coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split turbine. The turbine further includes an airfoil blade ring metallurgically coupled to a radial outer surface of the coupled forward and aft hub sections and an impingement cavity formed within an interior portion of the coupled forward and aft hub sections. The impingement cavity includes an interior surface that is positioned proximate to the radial outer surface of the coupled forward and aft hub sections. Further, an impingement cooling air flow impinges against the interior surface of the impingement cavity to provide convective and conductive cooling to the radial outer surface of the coupled forward and aft hub sections.Type: GrantFiled: May 13, 2013Date of Patent: October 25, 2016Assignee: HONEYWELL INTERNATIONAL INC.Inventors: David K. Jan, Amandine Miner
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Patent number: 9469399Abstract: The invention relates to a separable blade attachment (1) for a bearingless main rotor of a helicopter with an airfoil blade (2), a flexbeam (3) and a control cuff (4) enclosing at least a predominant portion of said flexbeam (3). A separable junction arrangement between said flexbeam head (13), said control cuff (4, 22) and said root end of said airfoil blade (2) is mechanical with removable fasteners. A stiffened link (17) is provided between respective trailing edges (9) of the control cuff (4) and said airfoil blade (2).Type: GrantFiled: October 15, 2013Date of Patent: October 18, 2016Assignee: Airbus Helicopters Deutschland GmbHInventors: Gerald Kuntze-Fechner, Markus Bauer
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Patent number: 9470243Abstract: A guide vane attachment structure including a first fitting portion formed in a vane joint surface of a guide vane, a support member whose constituent material is a metal is integrally connected to a fan frame, and a second fitting portion to be fitted to the first fitting portion formed in a support joint surface of the support member.Type: GrantFiled: March 8, 2012Date of Patent: October 18, 2016Assignee: IHI CorporationInventors: Tadahiro Ishigure, Yukihiro Kondo, Takaomi Inada
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Patent number: 9458723Abstract: A power turbine includes a first stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: February 28, 2014Date of Patent: October 4, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Daniel J Lecuyer, Niloofar Moradi
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Patent number: 9447792Abstract: A centrifugal blower provided with a spiral shaped scroll chamber where a bottom part of the scroll chamber gradually expands downward in the axial direction of the fan well along with expansion of the spiral and where a flow area gradually expands toward an air outlet from a spiral start part of the casing, the centrifugal blower having an initial slant angle ?0 at the spiral start part of the bottom part of the scroll chamber of a range of angle of 5.2° to 27.5° or setting a backflow prevention rib at the fan outlet.Type: GrantFiled: December 2, 2015Date of Patent: September 20, 2016Assignees: DENSO CORPORATION, NIPPON SOKEN, INC.Inventors: Yasushi Mitsuishi, Masaharu Sakai, Masanori Yasuda, Shouichi Imahigashi, Syunsuke Ishiguro
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Patent number: 9447696Abstract: A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75-175% of the second coefficient of thermal expansion.Type: GrantFiled: December 27, 2012Date of Patent: September 20, 2016Assignee: United Technologies CorporationInventors: Michael G. McCaffrey, Brandon T. Rouse, Thomas Almy, Igor S. Garcia, John R. Farris, Mark Borja
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Patent number: 9447776Abstract: A turning device to rotate the rotatable part of a wind turbine that comprises a stationary part and a rotatable part is described. The rotatable part is rotatable with respect to the stationary part of the wind turbine, and the stationary part is located within a nacelle, wherein the nacelle is at least partially enclosed by a housing. The turning device comprises a first lever and a second lever that is detachably attached to the rotatable part of the wind turbine. The first lever and the second lever reach from inside the housing of the nacelle through an opening to the outside of the nacelle, so that the drive is located outside of the housing of the nacelle, when the turning device is attached to the wind turbine.Type: GrantFiled: November 20, 2013Date of Patent: September 20, 2016Assignee: SIEMENS AKTIENGESELLSCHAFTInventor: Thorkil Munk-Hansen
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Patent number: 9441639Abstract: A heat shield for a rotor in a turbine engine is provided. The heat shield includes a main body having a first pair of recesses. The first pair of recesses is adapted to fit around a portion of one or more rotor blades or between two axially adjacent rotor wheels. The first pair of recesses limits axial and radial movement of the heat shield by interaction with the rotor blades or by interaction with the two axially adjacent rotor wheels. The first pair of recesses engage axially adjacent rotor blades or the axially adjacent rotor wheels. The heat shield protects the rotor from hot gas.Type: GrantFiled: May 13, 2013Date of Patent: September 13, 2016Assignee: General Electric CompanyInventor: Matthew Troy Hafner
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Patent number: 9441492Abstract: An aircraft rotor blade having a root portion having a through seat and designed for connection to the rotor; and a main portion extending from the root portion. The blade is produced by polymerizing an assembly having a main structure of composite material, and a composite material covering defining the outer surface of the blade. At the root portion, the main structure has a contoured block; and a lamina member extending about at least part of the block, and having a first part adhering to a first peripheral portion of the block, and a second part spaced apart from and facing a second peripheral portion of the block to form the seat; the lamina member having a pre-preg of continuous unidirectional fibers.Type: GrantFiled: February 7, 2013Date of Patent: September 13, 2016Assignee: AGUSTAWESTLAND S.P.A.Inventors: Fabio Nannoni, Francesco Scapinello, Giuseppe Manenti
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Patent number: 9441609Abstract: In a torque limiter, wedge-shaped spaces are formed between inner and outer rings so as to be arranged in the circumferential direction. In each wedge-shaped space, there are arranged a first roller and a second roller that transmit torque between the inner and outer rings by being brought into wedge-engagement when the inner and outer rings rotate relative to each other in one direction and in the other direction, respectively. Between the first and second rollers, there is arranged an urging device that urges the first and second rollers in such directions that the first and second rollers are brought into wedge-engagement. Each wedge-shaped space is formed such that when the torque becomes equal to or higher than a predetermined value, a first wedge angle of the first roller or a second wedge angle of the second roller becomes such an angle that wedge-engagement of the roller is cancelled.Type: GrantFiled: September 17, 2013Date of Patent: September 13, 2016Assignee: JTEKT CORPORATIONInventor: Hideki Fujiwara
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Patent number: 9434467Abstract: This invention relates to a blade assembly comprising: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device which comprises an annular catcher having a restriction through which the root portion cannot radially pass, the restriction being located radially outwardly and radially spaced from the root part during use.Type: GrantFiled: June 11, 2013Date of Patent: September 6, 2016Assignee: ROLLS-ROYCE plcInventors: Kenneth John Mackie, Kenneth Franklin Udall
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Patent number: 9429028Abstract: A pinned root fixing arrangement of axial flow steam turbine rotor discs made of a low alloy that is less susceptible to stress corrosion cracking (SCC). Such an arrangement has a first ratio, which is defined as ratio of the axial breadth of the disc fingers and the sum of the axial breath and the axial breadth G of the gap between adjacent disc fingers, in the range of about 0.4 to about 0.6 and further has a second ratio, which is defined as the ratio of the length of the disc fingers and the blade fingers to the diameter, between 4 and 6.Type: GrantFiled: July 25, 2013Date of Patent: August 30, 2016Assignee: ALSTOM Technology LtdInventors: Arnaud Buguin, Michel Floch, Julien Lemaire
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Patent number: 9404367Abstract: A method for balancing a compressor rotor assembly including a forward weldment (211) and an aft weldment (212) includes pre-balancing the aft weldment (212) of the compressor rotor assembly (210) with compressor disks (220) prior to populating the compressor disks (220) with circumferentially installed compressor rotor blades (230). Pre-balancing the aft weldment (212) includes measuring a rotational balance of the aft weldment (212). Pre-balancing the aft weldment (212) also includes determining a number of underplatform weights (260) needed and a location for each underplatform weight (260) within a circumferential slot (236) of one the compressor disks (220). Pre-balancing the aft weldment (212) further includes mounting each underplatform weight (260) in the determined location.Type: GrantFiled: November 21, 2012Date of Patent: August 2, 2016Assignee: Solar Turbines IncorporatedInventors: Cory Patrick Muscat, Laura Elizabeth McDonald, James Eric Miller, Gary Paul Vavrek
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Patent number: 9394915Abstract: A seal land for a gas turbine engine can include a seal body that can extend between a leading edge portion, a trailing edge portion, a radially outer surface and a radially inner surface. A notch can extend at least partially through the seal body between the radially outer surface and the radially inner surface.Type: GrantFiled: June 4, 2012Date of Patent: July 19, 2016Assignee: United Technologies CorporationInventors: Amy M. Gordon, Jonathan J. Jakiel, Jonathan P. Burt, Steven D. Porter
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Patent number: 9377029Abstract: A blade of a turbomachine or a flying machine includes a blade airfoil extending in a radial direction from a blade root to a blade tip. The blade airfoil has an inflow-side leading edge, an outflow-side trailing edge, a pressure side and a suction side. A surface of each of the pressure side and the suction side extends between the inflow-side leading edge and the outflow-side trailing edge. The blade tip has an end face with a camber line that extends from the inflow-side leading edge to the outflow-side trailing edge. At least one tip-side recess forms a depression from the end face into the blade airfoil, the depression extending continuously from the pressure side to the suction side and having a partial length of the camber line.Type: GrantFiled: June 22, 2012Date of Patent: June 28, 2016Assignee: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Willy Heinz Hofmann, Josef Ballmann
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Patent number: 9366147Abstract: A device controlling shifting of a propeller turbine engine into reverse mode, by acting on a shaft for controlling pitch of propellers. The device includes: at least one centrifugal weight arranged to drive the propellers into a flag position thereof under action of the centrifugal force; and an actuator that can rotate the control shaft to shift the pitch of the propellers from a traction mode to a reverse mode, passing through a zero pitch position. The centrifugal weight is in an unstable equilibrium position in relation to action of the centrifugal force when the control shaft shifts the pitch of the propellers through the zero pitch position. Further, an actuation mechanism exerts a torque on the control shaft when the centrifugal weight is in the unstable equilibrium position, to prevent it from staying in this position.Type: GrantFiled: November 16, 2011Date of Patent: June 14, 2016Assignee: SNECMAInventor: Francois Gallet
