Patents Examined by Justin D Seabe
  • Patent number: 10787913
    Abstract: An airfoil for a gas turbine engine includes axial flow and radial flow cooling circuits defined within an airfoil body. A baffle disposed in spaced relation to an inner surface of the airfoil has a plurality of impingement cooling holes configured to direct a cooling fluid at an inner surface of the airfoil body and an axial extent from the leading edge defined by an aft wall, with the axial extent being substantially constant between the inner and outer end walls and defined by a plane perpendicular to an engine axis. A first radially-extending rib is angled with respect to the baffle to define a first passage between the first rib and the baffle that tapers in cross-sectional area between the inner end wall and the outer end wall, becoming larger in cross-sectional area in a direction of cooling fluid flow through the first passage.
    Type: Grant
    Filed: November 1, 2018
    Date of Patent: September 29, 2020
    Assignee: United Technologies Corporation
    Inventors: Daniel P. Preuss, Brandon W. Spangler
  • Patent number: 10788045
    Abstract: Provided is a discharge section structure for a centrifugal compressor provided with a scroll flow passage and a discharge flow passage connected to the scroll flow passage. The discharge section structure includes a tongue section provided in a branching section between the scroll flow passage and the discharge flow passage; a first flow passage section having a center of curvature on an origin side of the scroll flow passage; and a second flow passage section communicating with the first flow passage section and having a center of curvature on an outer side of the scroll flow passage. The first flow passage section includes at least a part of the scroll flow passage, and the second flow passage section includes at least a part of the discharge flow passage. The tongue section faces the second flow passage section and is located in the middle of the second flow passage section.
    Type: Grant
    Filed: November 21, 2016
    Date of Patent: September 29, 2020
    Assignee: IHI Corporation
    Inventor: Takashi Fujiwara
  • Patent number: 10787924
    Abstract: A turbine ring assembly including both a plurality of ring sectors together forming a turbine ring and also a ring support structure including an upstream annular flange and a downstream annular flange, each ring sector having a first horizontal sealing tongue, an upstream vertical sealing tongue, and a first downstream vertical sealing tongue. Each ring sector also includes a second horizontal sealing tongue over the first horizontal sealing tongue in the radial direction of the ring. A first angled sealing element is housed both in a vertical groove present in the upstream tab and in a second horizontal groove, and a second angled sealing element is received both in a first horizontal groove and in a first vertical groove present in the downstream tab.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: September 29, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sebastien Serge Francis Congratel, Clement Jean Pierre Duffau, Matthieu Simon
  • Patent number: 10781828
    Abstract: A rotary assembly for a centrifugal pump includes a housing, an impeller, a first opening formed in one of the housing or the impeller, a first bushing disposed in the first opening, and a first shaft projection projecting axially from one of the housing or the impeller. The first bushing extends annularly around a central opening thereof and is formed from an elastomeric material. The first shaft projection is received within the central opening of the first bushing. One of the first shaft projection or the first bushing is configured to rotate relative to the other of the first shaft projection or the first bushing during operation of the centrifugal pump.
    Type: Grant
    Filed: September 12, 2018
    Date of Patent: September 22, 2020
    Assignee: HANON SYSTEMS
    Inventors: Brian Graichen, David Crowther, Jean-Claude Cadoret
  • Patent number: 10781791
    Abstract: A device for attaching to a surface of a wind turbine blade is described. The device comprises a plurality of sections to be arranged end-to-end along a portion of the blade. Each section of the device comprises: a baseplate for bonding to the surface of the blade; a first panel extending from the baseplate; first and second end walls extending respectively along transverse edges of the baseplate and the first panel; a first tab extending from the first end wall; and a second tab extending from the second end wall, the second tab being transversely offset from the first tab. The tabs are arranged such that when the sections are positioned end-to-end with a first end wall of a first section adjacent to a second end wall of a second section, the first tab of the first section overlaps the second end wall of the second section, whilst the second tab of the second section overlaps the first end wall of the first section.
    Type: Grant
    Filed: September 7, 2017
    Date of Patent: September 22, 2020
    Assignee: Vestas Wind Systems A/S
    Inventor: Thomas Potentier
  • Patent number: 10774665
    Abstract: A seal system for a gas turbine vane includes a first seal layer and an optional second seal layer. Each first seal layer includes multiple seal segments, each of which includes a first leg, a second leg, and an intermediate portion between the first leg and the second leg. Each adjacent pair of seal segments of the first seal is separated by a gap. The seal segments define a substantially complete perimeter of a seal slot in which the first seal is installed. The second seal, which is also segmented, may or may not define the substantially complete perimeter of the seal slot. If present, the second seal segments are circumferentially offset from the first seal segments to block the gaps between the first seal segments. A turbine vane including the present seal system is also disclosed.
    Type: Grant
    Filed: July 31, 2018
    Date of Patent: September 15, 2020
    Assignee: General Electric Company
    Inventors: John Ellington Greene, Neelesh Nandkumar Sarawate
  • Patent number: 10738638
    Abstract: The present disclosure is directed to a rotor blade and method for forming the rotor blade. The rotor blade includes a platform having a bottom side radially spaced from a top side and a leading edge portion axially spaced from a trailing edge portion. An airfoil extends radially outwardly from the top side of the platform and a shank extends radially inwardly from the bottom side of the platform. The shank includes a lip that extends axially outwardly from a forward wall of the shank. The lip defines a radially inward surface and a radially outward surface and a plurality of slots. Swirler vane inserts are disposed within respective slots of the plurality of slots. Each swirler vane insert extends radially inwardly from the inward surface of the lip and axially outwardly from the forward wall of the shank.
    Type: Grant
    Filed: September 7, 2016
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Soumyik Bhaumik
  • Patent number: 10738738
    Abstract: A nacelle for an aircraft propulsion system includes a core cowl portion, a bifurcation portion and an extension portion. The core cowl portion extends about a centerline to the bifurcation portion. The bifurcation portion is connected to and extends radially between the core cowl portion and the extension portion. The extension portion projects out from the bifurcation portion and circumferentially extends over the core cowl portion. The extension portion includes an acoustic panel and a structural reinforcement. The acoustic panel includes a cellular core between a perforated face skin and a back skin, wherein the face skin is radially inboard of the back skin. The structural reinforcement is bonded to the back skin and structurally reinforces the acoustic panel.
    Type: Grant
    Filed: June 17, 2016
    Date of Patent: August 11, 2020
    Assignee: Rohr, Inc.
    Inventors: Jinqiu Lu, Christian Soria
  • Patent number: 10737774
    Abstract: Various embodiments of an unmanned aerial vehicle are disclosed. In some embodiments, the UAV includes a motor assembly rotatable about a rotation axis and a propeller hub assembly removably engageable with the motor assembly. The propeller hub assembly includes a retainer configured and dimensioned for engagement with the motor assembly such that rotation of the motor assembly causes corresponding rotation of the propeller hub assembly. The retainer includes a pair of deflectable arms resiliently repositionable between a first position and a second position, for engagement and disengagement with the motor assembly, respectively. The arms are movable inwardly towards the rotation axis from the first position to the second position upon application of an external force and movable outwardly away from the rotation axis from the second position to the first position upon removal of the external force.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: August 11, 2020
    Assignee: GoPro, Inc.
    Inventors: Ryan Michael Goldstein, David Milton
  • Patent number: 10738639
    Abstract: Aspects of the disclosure are directed to a seal comprising: a first fitting configured to couple to a first disk, and a curvic joint including curvic teeth, where a first distance between the first fitting and the curvic teeth is equal to or greater than a first thickness of the first disk. In some embodiments, an engine comprises: a compressor disk, a turbine disk, and a seal including: a first fitting configured to couple to the turbine disk, a second fitting configured to couple to the compressor disk, and a curvic joint including curvic teeth, where a first axial distance between the first fitting and the curvic teeth is greater than or equal to a first radial thickness of the turbine disk.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Steven D. Porter, Thomas A. Mariano
  • Patent number: 10738618
    Abstract: A ventilation flow path, a cooling air flow path, a mixing space, and a mixed air flow path are formed in a gas turbine rotor. The ventilation flow path guides compressed air farther on an axially upstream side than an air discharge port of a compressor to an interior of a compressor rotor as compressor extracted air. The cooling air flow path guides cooling air to a part farther on an axially downstream side than the air discharge port. The compressor extracted air and the cooling air are mixed in the mixing space. The mixed air flow path guides mixed air containing the compressor extracted air and the cooling air into a turbine rotor.
    Type: Grant
    Filed: October 21, 2016
    Date of Patent: August 11, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Shinya Hashimoto, Keita Takamura
  • Patent number: 10731510
    Abstract: A gas turbine engine includes a static structure which includes a first fluid passage and a rotatable shaft. A bearing assembly supports the rotatable shaft relative to the static structure. The bearing assembly includes an outer race with a damper passage that extends between the static structure and the outer race. A second fluid passage extends from the damper passage to a seal.
    Type: Grant
    Filed: May 8, 2015
    Date of Patent: August 4, 2020
    Assignee: RAYTHON TECHNOLOGIES GROUP
    Inventor: Paul R. Hanrahan
  • Patent number: 10731491
    Abstract: Bolt holes 16 are formed in a joint part 14 of a turbine housing 12, with flanged bolts 40 screwed in the bolt holes 16. A flange part 32 of a bearing housing 30 is sandwiched between bearing surfaces 44a of the flanged bolts 40 and an inner end face 14b of the joint part 14. A sealing ring 48 is interposed in an annular space s. Before the flanged bolts 40 are fastened, there is formed a height difference G equivalent to a compression allowance h for the sealing ring 48, between an outer end face 60a of the joint part 14 and a bolt receiving surface 32a of the flange part 32. The flanged bolts 40 are screwed into the bolt holes 16 until the bearing surfaces 44a make tight contact with the outer end face 60a so as to resiliently deform the sealing ring 48.
    Type: Grant
    Filed: July 27, 2016
    Date of Patent: August 4, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Shingo Shudo, Daigo Watanabe, Takumi Tokiyoshi, Motoki Ebisu
  • Patent number: 10724498
    Abstract: A vane device includes a rotary shaft and a plurality of vane units angularly spaced apart from each other relative to the rotary shaft. Each of the vane units includes a grid frame that has grid spaces, and a plurality of vanes respectively disposed adjacent to the grid spaces. Each vane is swingable between a cover position and an open position. The size of the vanes decreases along a radial direction from a vicinity of the rotary shaft to a distance away from the rotary shaft.
    Type: Grant
    Filed: October 27, 2017
    Date of Patent: July 28, 2020
    Inventor: Kuo-Chang Huang
  • Patent number: 10724393
    Abstract: A seal assembly, comprising a first segment, a second segment, and a seal incorporated between the first segment and the second segment, the seal comprising a mesh. The first segment may comprise a blade outer air seal and the second segment may comprise a vane. In various embodiments, the first segment and the second segment may define a gap, and the seal may seal the gap. The seal may have a first member and a second member that enmeshes the first member. The seal may comprise a member that enmeshes a non-metallic member. The seal may comprise a ceramic fiber enmeshed by a member. The seal may comprise a non-metallic member enmeshed by a metallic member. The seal may comprise a plurality of annular connecting members, each annular connecting member extending about the seal. The seal may comprise a single annular member.
    Type: Grant
    Filed: January 15, 2015
    Date of Patent: July 28, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Timothy Davis
  • Patent number: 10724397
    Abstract: A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.
    Type: Grant
    Filed: December 8, 2017
    Date of Patent: July 28, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Darin S. Lussier, Sreenivasa R. Voleti, Thomas J. Robertson, Jr., Christopher M. Quinn
  • Patent number: 10724540
    Abstract: A turbofan engine is disclosed having a bypass duct with an asymmetry in aerodynamic profile caused by a local obstruction in the bypass duct. The engine comprises stator vanes circumferentially spaced-apart around a circumference of the bypass duct. A first group of adjacent stator vanes includes a majority of the plurality of stator vanes and are arranged in a first circumferential sector of the bypass duct and have equal stagger angles. A second group of adjacent stator vanes includes a minority of the plurality of stator vanes and are arranged in a second circumferential sector circumferentially positioned relative to the local obstruction. The stator vanes of the second group have stagger angles different from the stagger angles of the stator vanes of the first group.
    Type: Grant
    Filed: December 6, 2016
    Date of Patent: July 28, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Yau-Wai Li, Peter Townsend, Ronald Dutton, Bernadette Mason
  • Patent number: 10724544
    Abstract: A centrifugal compressor is provided. The centrifugal compressor includes a housing and a rotatable assembly mounted for rotation about an axis within the housing. The rotatable assembly includes an impeller forming part of a compressor stage. A first air intake is located at a first end of the apparatus, the first air intake providing an air source for the compressor stage and a second air intake is located at a second end of the apparatus. A thrust plate is attached to the rotatable assembly, the thrust plate including at least one interior channel so that air entering the second air inlet passes through the at least one interior channel.
    Type: Grant
    Filed: June 16, 2016
    Date of Patent: July 28, 2020
    Assignee: Vortech Engineering, Inc.
    Inventors: Gregory Graham, Robert Anderson, James Middlebrook
  • Patent number: 10717543
    Abstract: Apparatus and methods for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft are disclosed. The apparatus includes a rotor shaft coupled the bladed rotor of the aircraft and driven by a turbine shaft of the engine via a speed-reducing gear train. A speed-augmenting power transfer device has an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device. An electric generator disposed in a hub of the bladed rotor is coupled to the output of the speed-augmenting power transfer device and configured to generate electrical power for the device associated with the bladed rotor.
    Type: Grant
    Filed: October 30, 2017
    Date of Patent: July 21, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lazar Mitrovic, Richard Ullyott
  • Patent number: 10718219
    Abstract: A turbine blade having a base and an airfoil, the base including cooling air inlets and an internal cooling air passageway, and the airfoil including an internal multi-bend heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, and a tip flag cooling system.
    Type: Grant
    Filed: September 7, 2018
    Date of Patent: July 21, 2020
    Assignee: Solar Turbines Incorporated
    Inventors: Andrew T. Meier, Nnawuihe Okpara, Stephen Edward Pointon, Kevin Hirako