Patents Examined by Michael L Sehn
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Patent number: 12227885Abstract: A fibrous preform for forming the fibrous reinforcement of a composite material part, the fibrous preform being made as a single piece and obtained by three-dimensional weaving, the preform including first and second skins and a longitudinal stiffening portion connecting the first to the second skin, the longitudinal stiffening portion forming a stiffening element of the part in the longitudinal direction. The preform has an intermediate portion extending in the longitudinal direction between two end portions. The longitudinal stiffening portion includes, in the intermediate portion, longitudinal non-woven threads or strands held together by first transverse threads or strands coming from the first skin and second transverse threads or strands coming from the second skin. In the end portions, the longitudinal threads or strands of the longitudinal stiffening portion are woven with the transverse threads or strands.Type: GrantFiled: January 19, 2021Date of Patent: February 18, 2025Assignee: SAFRANInventors: Bruno Jacques Gérard Dambrine, Yann Didier Simon Marchal, Dominique Marie Christian Coupe, Marc-Antoine Colot
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Patent number: 12215715Abstract: A balancing system includes a rotor hub having a center axis and a balancing ring surrounding the rotor hub. The balancing ring includes a plurality of ring teeth. A pinion gear includes a plurality of gear teeth in meshing engagement with the plurality of ring teeth, wherein the pinion gear is selectively rotated to adjust a position of the balancing ring relative to the rotor hub.Type: GrantFiled: August 3, 2023Date of Patent: February 4, 2025Assignee: RTX CORPORATIONInventor: Enzo DiBenedetto
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Patent number: 12215603Abstract: An airfoil includes a CMC airfoil wall that defines a platform, a root that extends radially from the platform, and an airfoil section that extends radially from the platform opposite the root. The CMC airfoil wall includes a wishbone-shaped fiber layup structure. The wishbone-shaped fiber layup structure includes first and second arms that merge into a single leg. The first and second arms are comprised of a network of fiber tows, and the single leg includes fiber tows from each of the first and second arms that are interwoven in the single leg. The single leg forms a portion of the root, and the first and second arms extend in opposite directions from the single leg and form a portion of the platform.Type: GrantFiled: June 23, 2023Date of Patent: February 4, 2025Assignee: RTX CORPORATIONInventors: Marcus DeReimer, Michael G. McCaffrey
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Patent number: 12209569Abstract: A segmented wind turbine rotor blade includes sleeve-shaped pressure pieces arranged between rotor blade segments, each of which is mounted on a connecting bolt. Each pressure piece includes one or more cylindrical sections and a tool engaging section for an assembly tool). Each pressure piece is connected to a corresponding connecting bolt in a form fit manner, so that a screwing force can be applied to the corresponding connecting bolt via the assembly tool via the pressure piece. A diameter of the cylindrical section(s) is less than a diameter of the tool engaging section. Each two adjacent pressure pieces are arranged rotated by 180° relative to one another.Type: GrantFiled: November 3, 2021Date of Patent: January 28, 2025Assignee: Nordex Energy SE & Co. KGInventors: Gerald Festner, Torsten Wackrow
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Patent number: 12209503Abstract: A turbine ring assembly having ring segments made of ceramic matrix composite material and each having first and second attachment tabs and a cavity for the circulation of air flow, a metal support having a first bracket and a second bracket bearing axially upstream against the second tab, a first metal flange arranged upstream of the first bracket and having an inner periphery bearing axially downstream against the first tab and an outer periphery fastened to the first bracket, and air passage orifices formed in the inner periphery of the first flange and/or in the second bracket, the orifices configured to ensure that the air flow passes from the cavity to the outside of the assembly.Type: GrantFiled: March 25, 2022Date of Patent: January 28, 2025Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Jarrossay, Aurélien Gaillard, Pascal Cédric Tabarin, Arthur Paul Gabriel Nimhauser, Clément Emile André Cazin
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Patent number: 12203391Abstract: A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.Type: GrantFiled: May 8, 2023Date of Patent: January 21, 2025Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Barry Barnett
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Patent number: 12203484Abstract: The invention relates to a fan blade (3) of a turbomachine (15) comprising a structure (4) made of composite material having, within the root (5) and/or the stilt (6) of the blade, a first layer (11) comprising the lower face (16) and having a first thickness (E1) of between 10% and 25% of the total thickness (E), a second layer (12) comprising the suction face (17) and having a second thickness (E2) of between 10% and 25% of the total thickness (E), and a central layer (13) extending between the first layer (11) and the second layer (12), the shortening of the warp strands (9) in the first and second layers (11, 12) being greater than the shortening of the warp strands (9) in the central layer (13).Type: GrantFiled: May 25, 2022Date of Patent: January 21, 2025Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Pascal Jean-Charles Gondre, Nicolas Paul Tableau, Julien Paul Schneider-Die-Gross
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Patent number: 12195406Abstract: A part includes a substrate made of ceramic matrix composite material, the substrate being coated with a multilayer stack including at least, and in this order, starting from the substrate a tie layer including silicon; an insulation layer including a rare earth disilicate or silica; a barrier layer including a rare earth disilicate; the part further including at least one thermocouple inserted between the insulation layer and the barrier layer.Type: GrantFiled: December 13, 2022Date of Patent: January 14, 2025Assignees: SAFRAN CERAMICS, SAFRANInventors: Eric Conete, Lisa Pin, Ioannis Stasinopoulos
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Patent number: 12196089Abstract: A monitoring device for a rotary machine is a monitoring device for monitoring a clearance of a rotary machine including a casing for housing a rotating part and a stationary part, including: at least one position sensor disposed outside the casing and configured to detect a relative position of the casing to the rotating part in a radial direction; and an estimation unit configured to obtain an estimated value of an internal clearance between the rotating part and the stationary part in the casing, based on a measured value detected by the at least one position sensor.Type: GrantFiled: November 8, 2021Date of Patent: January 14, 2025Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Makoto Kondo, Takehiko Yamaguchi, Katsuhisa Hamada, Takashi Nakano
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Patent number: 12196110Abstract: The invention relates to a blisk segment for a gas turbine, comprising at least one first blade having an airfoil, a leading edge, a trailing edge, a blade root, a suction side and a pressure side, a pedestal, and a first fillet having a device for influencing crack growth. The robustness of the gas turbine is improved in accordance with the invention in that, at the leading edge of the first blade, at least on the first fillet, a first surface structure is arranged and interacts with the crack-influencing device for influencing crack growth and for flow influencing.Type: GrantFiled: February 28, 2023Date of Patent: January 14, 2025Assignee: MTU Aero Engines AGInventors: Benjamin Hanschke, Alexander Halcoussis, Amadeusz Rekosiewicz, Moritz Thon, Benjamin Linke
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Patent number: 12180848Abstract: A centrifugal compressor includes: a housing including an intake flow path; a compressor impeller arranged in the intake flow path and including a plurality of blades; an accommodation chamber formed upstream of the blades in a flow of intake air in the housing; a movable member arranged in the accommodation chamber and movable to a protruding position where the movable member protrudes into the intake flow path and to a retracted position where the movable member is retracted from the intake flow path; a plurality of slits formed closer to the blades with respect to the accommodation chamber in the housing and connected to the intake flow path; a plurality of compartment walls circumferentially separating the plurality of slits; and an outer circumferential wall connecting radially outer ends of the plurality of compartment walls.Type: GrantFiled: November 6, 2023Date of Patent: December 31, 2024Assignee: IHI CorporationInventors: Atsushi Yonemura, Ryota Sakisaka, Yoichi Sato, Taiki Kanzawa
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Patent number: 12180856Abstract: An aerodynamic arm for an aircraft turbine engine casing includes a tubular outer shell having a generally elongate shape extending substantially along an axis. The shell has axial ends configured to be connected to a turbine engine casing. An electrically conductive core extends inside the shell and has ends configured to electrically connect to the ends of the shell. An insulating material occupies a space between the core and the shell.Type: GrantFiled: January 7, 2020Date of Patent: December 31, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventor: Marc Missout
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Patent number: 12163445Abstract: A composite airfoil assembly for a turbine engine including an airfoil extending in a radial direction between a root and a tip to define a span length. The airfoil including a composite core and a set of skins overlying the composite core. The set of skins include an outer skin defining at least a portion of an exterior surface of the airfoil. A dovetail extends radially below the root, the dovetail including the composite core and the set of skins, the dovetail further including a fan skin overlying the outer skin proximate the root.Type: GrantFiled: June 29, 2023Date of Patent: December 10, 2024Assignee: General Electric CompanyInventor: Elzbieta Kryj-Kos
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Patent number: 12157555Abstract: Embodiments provide a propeller ground stop mechanism configured to keep an unpowered propeller of an aircraft (e.g. when the aircraft is on the ground and not operating) static. The propeller is prevented from rotating due to external forces (e.g. an air flow caused by wind, manual rotation of the propeller). When the propeller is powered, and the propeller is providing thrust, the propeller ground stop mechanism automatically disengages and does not provide any drag. Among various benefits, the propeller ground stop mechanism provides added safety to the ground support personnel.Type: GrantFiled: November 8, 2023Date of Patent: December 3, 2024Assignee: Wisk Aero LLCInventors: Geoffrey Alan Long, Pieter DePape
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Patent number: 12158082Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.Type: GrantFiled: February 20, 2023Date of Patent: December 3, 2024Assignee: General Electric CompanyInventors: Nicholas Joseph Kray, Arthur William Sibbach
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Patent number: 12146414Abstract: A vane assembly includes vanes, an actuator assembly, and a controller. The vanes are configured to rotate about their pitch axes. The actuator assembly includes an annular ring arranged radially outward of the vanes and coupled to the vanes, a magnet arranged on the annular ring, and a stator arranged adjacent the magnet. The ring is configured to rotate the vanes about the pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and annular ring about the central axis. The controller controls movement of the ring via the stator and magnets in response to at least one of (i) at least one operating condition of the gas turbine engine, or (ii) at least one operating parameter of the at least one first vane.Type: GrantFiled: October 21, 2022Date of Patent: November 19, 2024Assignee: Rolls-Royce North American Technologies Inc.Inventors: Timothy Unton, Andrew Eifert, Michael Moser
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Patent number: 12149152Abstract: The present invention discloses an axial flux magnet motor stator assembly, an assembling method, and a ceiling fan, wherein a coil winding assembly can be prefabricated, then assembled on a stator winding column without the need to reserve a large avoidance space between two adjacent stator winding columns, accordingly the gap between them can be minimized, for which each of them can have a maximum number of turns of the coil winding assembly to enhance the magnetic flux, further improve the output power and torque, provide an assembly efficiency and reduce the manufacturing cost. The terminals of each coil winding assembly are located in the bottom cover filling slot and fixed by an adhesive to ensure that the electrical connection is reliable and stable. Thus, a ceiling fan of the present invention using the above assembly has the characteristics of large output power and torque under the same size.Type: GrantFiled: April 7, 2023Date of Patent: November 19, 2024Assignee: ZK Optoelectronics Technology (Zhongshan) Co., Ltd.Inventor: Wei dian Lu
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Patent number: 12140045Abstract: A method for manufacturing a blade of a fan for an aircraft turbomachine extending around a longitudinal axis, the blade including an aerofoil made of a composite material having a leading edge and a trailing edge connected by a pressure side and a suction side, the aerofoil extending between a base and a free end, the method including each of the following steps: —pairing and bonding a metal shield to the leading edge, —obtaining a first measurement of a radial moment weight of the blade before or after the metal shield has been bonded to the leading edge and determining a machining kerf, —machining the free end and/or the trailing edge along the machining kerf so as to adjust the mass and radial moment weight of the blade, —obtaining a second measurement of the radial moment weight of the blade.Type: GrantFiled: June 16, 2022Date of Patent: November 12, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pierre-Alexis Poulet, Richard Mounien, Lucas Antoine Christophe Lauwick
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Patent number: 12140151Abstract: A turbo fan, formed by ultrasonic welding, a first component including: a flat portion; and plate-shaped blade portions standing from the flat portion, and a second component having recessed groove portions in each of which an end portion of the respective blade portion fits. The groove portions have a groove width greater than a thickness of the end portions of the blade portions. The turbo fan includes a group of positioning ribs partially burying two clearances created on two sides of the end portion in a thickness direction thereof, respectively, in a pre-welding state. The group of positioning ribs protrude in the thickness direction from the end portion of at least one of the blade portions, or from side surfaces of at least one of the groove portions, and are in contact with side surfaces of the groove portion, or in contact with the end portion of the blade portion.Type: GrantFiled: July 14, 2023Date of Patent: November 12, 2024Assignee: MABUCHI MOTOR CO., LTD.Inventors: Kenji Shiraki, Hideki Yoshiura, Tetsushi Yoshikawa, Sakie Kawakami
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Patent number: 12140042Abstract: An optimized blade with an anchor element to be used in a streaming engine and method of manufacturing such blade. The blade contains a lower part, an upper part and an anchor element, wherein the anchor element is located inside of the blade, and wherein the anchor element connects the lower part and the upper part.Type: GrantFiled: June 10, 2020Date of Patent: November 12, 2024Assignee: Siemens Energy Global GmbH & Co. KGInventor: Andreas Graichen