Patents Examined by Igor Kershteyn
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Patent number: 11788434Abstract: Method for manufacturing a casing of an aircraft turbomachine, the casing including an annular shell extending about an axis A and made of a composite material including fibres that are woven and immersed in a resin, the annular layer including an abradable material arranged inside the shell, and covering a first inner annular surface of an intermediate section of the shell, the method including a step of gluing the layer on the first surface, during which the casing is heated and compressed by a system that is present at least partially inside the casing, wherein, prior to the heating and compression of the casing, a forming tool is mounted inside the casing and is made of two rings.Type: GrantFiled: July 10, 2020Date of Patent: October 17, 2023Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN AEROSPACE COMPOSITESInventors: Vincent Pascal Fiore, Gatien Frisoni, Foster Alexander Maxwell, Steven Meserve, Jeffrey Steven Sherman
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Patent number: 11788435Abstract: A pin member is proposed for a turbo-machine having a shroud arranged to rotate within a turbine housing. The pin member is configured to limit this rotation. It is a one-piece element comprising a cylindrical body and a limit surface for opposing motion of the shroud.Type: GrantFiled: November 11, 2020Date of Patent: October 17, 2023Assignee: CUMMINS LTD.Inventors: Simon David Moore, Karl Conlon, Matthew William Edwards
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Patent number: 11781441Abstract: An air cycle machine includes an air inlet connected to an air cycle compressor. Air downstream of the air cycle compressor is connected to be delivered across a first turbine. The air cycle compressor is driven by the first turbine through a shaft. Air downstream of the first turbine is connected to a second turbine. The second turbine is connected to deliver air downstream. The second turbine is connected with a second shaft to drive a fan rotor. The fan rotor delivers a source of air across a primary heat exchanger positioned between the inlet and the air cycle compressor. The air cycle compressor and the first turbine are formed of a metal. The second turbine and the fan rotor are formed of non-metallic materials.Type: GrantFiled: February 8, 2022Date of Patent: October 10, 2023Assignee: Hamilton Sundstrand CorporationInventors: Craig M. Beers, Donald E. Army
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Patent number: 11772135Abstract: An air nozzle includes a main body having a compressed air passageway to allow a compressed air to flow therethrough and a compensation air passageway in communication with the compressed air passageway. An external air is sucked into the compressed air passageway through the compensation air passageway and ejected together with the compressed air when the compressed air flows through the compressed air passageway.Type: GrantFiled: June 2, 2021Date of Patent: October 3, 2023Assignee: Tyco Electronics (Shanghai) Co., Ltd.Inventors: Jialin Zhang, Jinlong Li, Dan Li, Zhongxi Huang, Jiankun Zhou, Daiqiong Zhang
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Patent number: 11773820Abstract: An active folding wind turbine capable of resisting severe typhoons is provided. Each wind turbine blade includes an upper blade part and a lower blade part that are hinged to each other by a hinge device. A motor transmission system is installed in the lower blade part, is connected to the hinge device in a transmission manner, and can drive the upper blade part to rotate relative to the lower blade part through the hinge device, so that the wind turbine blade is bent. When the upper blade part rotates to an end of a travel, a blade tip of the upper blade part is propped against an upper end of the lower blade part of an adjacent wind turbine blade. A winch is built in an upper portion of the lower blade part of the wind turbine blade, and is provided with a cable.Type: GrantFiled: July 9, 2020Date of Patent: October 3, 2023Assignee: Nanjing University of Aeronautics and AstronauticsInventors: Shitang Ke, Jie Yang, Shuo Wang, Hao Wang, Hongxin Wu, Lin Du, Guangquan Han
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Patent number: 11773749Abstract: A method and system are provided for repairing a nozzle ring having a defect adjacent a transition between a ring plate and an inner skirt of the nozzle ring, comprising: forming at least one cut to detach at least one of a portion of the inner skirt, a portion of the transition, and a portion of the ring plate, thereby forming a joint surface and removing at least a portion of the defect; providing a replacement ring including replacement components for the detached at least one of a portion of the inner skirt, a portion of the transition, and a portion of the ring plate; and attaching the replacement ring to the nozzle ring at the joint surface using one of brazing or welding.Type: GrantFiled: February 15, 2022Date of Patent: October 3, 2023Assignee: CUMMINS INC.Inventors: Nikhil Doiphode, Todd M. Wieland
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Patent number: 11773748Abstract: A high temperature flange joint in a gas turbine engine includes a first flange formed on a first component abutting a second flange formed on a second component. The flange joint includes multiple adjacently spaced bolt connections. Each bolt connection includes a first spacer plate bearing against the first flange and a second spacer plate bearing against the second flange. First and second lock washers are provided that bear against the first and second spacer plates respectively. A bolt is inserted through the first and second flanges, the first and second spacer plates and the first and second lock washers. The bolt is preloaded to clamp the first flange to the second flange. Each spacer plate has a respective thickness and is sized to enhance a bearing surface in contact with the respective flange. Thereby, a bolt preload is maintained during operation of the gas turbine engine.Type: GrantFiled: June 5, 2020Date of Patent: October 3, 2023Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventors: John William Farabow, III, William J. Curtin
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Patent number: 11773828Abstract: Provided is a blade for a wind turbine including a trailing edge and a leading edge, a lightning protection system with at least one lightning receptor on the blade tip for receiving lightning and at least one lightning down conductor for conducting a lightning current received by the lightning receptor to the blade root, and an ice formation prevention system with a conductive layer arranged along the leading edge, and a first connection terminal on the first end and a second connection terminal on the second end for connecting the layer with a power supply unit, the first connection terminal is connected with the lightning down conductor, wherein the first connection terminal partially contacts the layer and have a rear section connected to the layer and a front section that longitudinally extends towards the blade tip.Type: GrantFiled: January 27, 2022Date of Patent: October 3, 2023Inventor: Victor March Nomen
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Patent number: 11761338Abstract: A method for producing a vibration-damping structure combination for damping vibrations for movable masses, having a first structure and a further structure, the further structure movable within a stop surface defined by a first structure surface of the first structure. The method includes a) providing the first structure, having the first structure surface and which defines a coating surface of a coating at least in some sections; b) coating the first structure surface of the first structure with the coating, the coating surface of the coating being applied such that a cavity is formed; c) filling the cavity with the filler; d) curing the filler until the further structure having a further structure surface is formed, which lies against the coating surface; and e) removing the coating, the further structure thus being movable relative to the first structure within the stop surface defined by the first structure surface.Type: GrantFiled: May 18, 2018Date of Patent: September 19, 2023Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventors: Robin Blank, Lena Farahbod-Sternahl, Christoph Kiener, Sascha Martin Kyeck, Yves Küsters, Simon Purschke, Helge Reymann
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Patent number: 11753966Abstract: A casing assembly for a gas turbine engine includes a plurality of vane casing segments. Each vane casing segment includes an arcuate member and a pair of split-line flanges. Each split-line flange includes a first axial flange end and a second axial flange end. Each split-line flange is fixedly coupled to an adjacent split-line flange of an adjacent vane casing segment. Each vane casing segment includes at least one row of stator vanes welded to the arcuate member. Each split-line flange is at least partially and circumferentially inclined relative to a rotational axis of the gas turbine engine, such that the first axial flange end is circumferentially offset from the second axial-flange end. Further, each split-line flange includes an intersecting portion, such that at least the intersecting portion of each split-line flange is circumferentially inclined relative to the rotational axis.Type: GrantFiled: February 10, 2023Date of Patent: September 12, 2023Assignee: Rolls-Royce PLCInventor: Crispin D. Bolgar
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Patent number: 11753953Abstract: An assembly for a turbomachine through which an air flow passes, includes a stator including guide vanes extending radially in relation to a longitudinal axis, at least one inter-vane platform extending between the radially outer ends of two circumferentially consecutive guide vanes, each inter-vane platform including an outer surface that faces the axis, a heat exchanger located downstream of the stator in relation to a direction of circulation of the air flow in the turbomachine during operation, this stator including a heat exchange surface extending in the extension of an inter-vane platform. At least one inter-vane platform located in the upstream extension of the heat exchange surface is provided with at least one turbulence generator on its outer surface.Type: GrantFiled: December 8, 2020Date of Patent: September 12, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Amélie Argie Antoinette Chassagne, Antoine Robert Alain Brunet, Cédric Zaccardi
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Patent number: 11753957Abstract: A method for detecting at least one roughness in a face of an abradable layer in a fan casing is provided. The method includes a step of depositing on the abradable layer a first coating and a second coating covering the first coating. The first and second coatings have respective thicknesses (N1, N2) and a physical appearance that differ from one another. Local appearance of the first coating is indicative of a need for a localized touch-up, and local disappearance of the first coating and the second coating is indicative of a need for a localized replacement of the abradable layer.Type: GrantFiled: April 10, 2020Date of Patent: September 12, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Bourolleau, Alexandre Branco, Serge Domingues, Vincent Fiore, Anwer Siraj
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Patent number: 11746663Abstract: A high-temperature component according to an embodiment is a high-temperature component which requires cooling by a cooling medium, and includes: a plurality of cooling passages through which the cooling medium is able to flow; a header portion to which downstream ends of the plurality of first cooling passages are connected; and at least one outlet passage for discharging the cooling medium flowing into the header portion to outside of the header portion. A roughness of an inner wall surface of the at least one outlet passage is not greater than a roughness of an inner wall surface of the plurality of first cooling passages in a region where a flow-passage cross-sectional area of the outlet passage is the smallest.Type: GrantFiled: February 19, 2020Date of Patent: September 5, 2023Assignee: MITSUBISHI POWER, LTD.Inventors: Shuji Tanigawa, Koichiro Iida, Ryuta Ito, Taro Tokutake, Yoshinori Wakita
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Patent number: 11739662Abstract: A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (?r) along the radial direction, a total volume (V), and a normalized radius (r?). The normalized radius (r?) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation: 0 . 1 ? ( r ? ) - 1 < ? ? r r < K ? ( r ? ) - 4 / 3 , wherein the normalized radius (r?) is between 1.25 and 8 and K is equal to 40%, or the normalized radius (r?) is between 2.75 and 4.5 and K is equal to 65%.Type: GrantFiled: March 23, 2022Date of Patent: August 29, 2023Assignee: General Electric CompanyInventors: Harry Kirk Mathews, Jr., William Morton, Constantinos Minas
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Patent number: 11732599Abstract: Methods and apparatus for real-time clearance assessment using a pressure measurement are disclosed. An example method includes determining a first and a second static pressure measurement at a first measurement location and a second measurement location, respectively, relative to the blade tip clearance, determining a normalized pressure measurement using the first and second static pressure measurements, generating a conversion curve to correlate the normalized pressure measurement with a clearance measurement, wherein the conversion curve is developed for the turbine engine during testing at a plurality of operating conditions, and adjusting active clearance control of the blade tip clearance based on the conversion curve.Type: GrantFiled: September 26, 2022Date of Patent: August 22, 2023Assignee: General Electric CompanyInventors: Taehong Kim, Aaron J. Sentis
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Patent number: 11732606Abstract: A cooling structure includes: a housing including an inner cylindrical portion through which a shaft is inserted; a coolant flow path formed in the housing and opened on one side of the housing in a rotational axis direction, the coolant flow path being located radially outside the inner cylindrical portion; a lid member disposed in an opening of the coolant flow path, the lid member located radially outside the inner cylindrical portion and adjacent to the coolant flow path; a first end portion on the lid member, the first end portion contacting, in the radial direction, an inner circumferential surface of the coolant flow path on one side in the radial direction; and a second end portion on the lid member, the second end portion contacting, in the rotational axis direction, an abutment surface on the housing on the other side in the radial direction.Type: GrantFiled: March 29, 2022Date of Patent: August 22, 2023Assignee: IHI CorporationInventor: Kenichi Segawa
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Patent number: 11732605Abstract: For a rotary electric machine housing, a cooling jacket and compressed air flow passages are formed on an outer circumferential side of the cooling jacket. On an outer side wall of the rotary electric machine housing, a terminal casing is formed and electric terminal portions are accommodated in the terminal casing. Air bleed ports are formed in a shroud case of a gas turbine engine. Compressed air that is compressed by a compressor wheel flows into the air bleed ports. The compressed air that has passed through the air bleed ports flows through air bleed passages formed in an engine housing and the compressed air flow passages. Then, the compressed air reaches the terminal casing.Type: GrantFiled: March 30, 2022Date of Patent: August 22, 2023Assignee: HONDA MOTOR CO., LTD.Inventors: Manabu Yazaki, Tatsuya Choji, Naoki Ito
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Patent number: 11725537Abstract: An air-jet cooling device for a casing of a turbomachine, in particular a turbine casing, including a cooling air housing having a wall, and a tube having a first end mounted on the wall of the housing so as to put the tube into fluid communication with the housing, orifices being formed in a wall of the tube in order to eject the cooling air coming from the housing on the casing. The tube has a section at the first end with a gradual variation that defines a boss. The boss has a curved surface to be immersed in the cooling air so as to avoid a detachment of a boundary layer of the cooling air at an interface between the first end of the tube and the housing.Type: GrantFiled: September 23, 2020Date of Patent: August 15, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Contini, Laurent Claude Descamps, Rémy Miled Michel Haynau, Maria Goossens, Benoit Guillaume Silet
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Patent number: 11725591Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; a gearbox that can receive an input from the core shaft, and can output drive to a fan shaft via an output of the gearbox so as to drive the fan at a lower rotational speed than the core shaft; and a fan shaft mounting structure arranged to mount the fan shaft within the engine, the fan shaft mounting structure including at least two supporting bearings connected to the fan shaft. A fan-gearbox axial distance is defined as the axial distance between the output of the gearbox and the fan axial centreline, the fan-gearbox axial distance being greater than or equal to 0.35 m.Type: GrantFiled: January 14, 2022Date of Patent: August 15, 2023Assignee: ROLLS-ROYCE plcInventor: Mark Spruce
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Patent number: 11725531Abstract: Rotor systems including an engine shaft, a forward hub, a rear hub, a rotor disk arranged between the forward hub and the rear hub, and a seal tube configured to define a forward hub compartment and a rear hub compartment. The forward hub compartment is defined forward of the rotor disk and the rear hub compartment is defined aft of the rotor disk. The seal tube is connected at a forward end to at least one of the rotor disk and the engine shaft and at a rear end to at least one of the rear hub and the engine shaft and the seal tube includes at least one axial compliance element configured to enable axial extension and compression of the seal tube in an axial direction along the engine shaft.Type: GrantFiled: November 22, 2021Date of Patent: August 15, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Nicholas J. Lawliss, Paul Boules