Patents Examined by Behnoush Haghighian
  • Patent number: 11408435
    Abstract: A rotor includes: a hub; and a plurality of blades disposed on the hub. Each of the plurality of blades has a suction surface, a pressure surface, a leading edge, a trailing edge, a tip-side edge, and a hub-side edge. The suction surface has a first curved surface portion curved convexly toward the trailing edge such that the trailing edge is inclined to a pressure surface side in a first region which is a partial region, in a blade height direction of the blade, of a region connected to the trailing edge.
    Type: Grant
    Filed: June 22, 2018
    Date of Patent: August 9, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Kenichiro Iwakiri, Nobuhito Oka, Hironori Honda
  • Patent number: 11408437
    Abstract: A vacuum pump includes a rotor that has a rotor central portion and a plurality of stages of rotor blade portions extending from the rotor central portion and having a predetermined elevation angle, and a casing that houses the rotor therein. The rotor further includes a rotor fin. The rotor fin includes a fin shaft portion connected to an end of the rotor central portion, and a transfer blade that extends from the fin shaft portion and causes particles to bounce back in a direction toward an outer periphery of the rotor, the particles falling onto the abovementioned end through an inlet port. The height of the transfer blade and the number of transfer blades are set based on the fall velocity of the particles and the rotation speed of the rotor, such that the particles are prevented from falling onto the abovementioned end without colliding with the transfer blade.
    Type: Grant
    Filed: October 12, 2018
    Date of Patent: August 9, 2022
    Assignee: Edwards Japan Limited
    Inventors: Manabu Nonaka, Toshiki Yamaguchi
  • Patent number: 11371369
    Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.
    Type: Grant
    Filed: May 15, 2019
    Date of Patent: June 28, 2022
    Assignee: CUMMINS LTD.
    Inventors: Matthew William Edwards, Karl Conlon, Simon David Moore, Christopher Parry, Andrew Sullivan, Paul Ghosh, Mark R. Holden, George E. Sandford, Nandakishore Arcot Madhusudan, Stephen David Hughes, Christopher J. Shaw
  • Patent number: 11365631
    Abstract: A turbine rotor blade according to at least one embodiment to be connected to a rotational shaft so as to be rotatable around an axis includes a hub having a hub surface inclined with respect to the axis in a cross-section along the axis; and a plurality of rotor blades disposed on the hub surface. In a throat portion where a blade-to-blade distance between two adjacent rotor blades is smallest, a value (Lt/r) obtained by dividing the blade-to-blade Lt at a given radial position by a distance r from the axis to the radial position is maximum at a position where a dimensionless span length is in a range of 0.2 to 0.65, assuming that the dimensionless span length is 0 at a position of a root end portion on a hub side and is 1 at a position of a tip end portion opposite to the hub side.
    Type: Grant
    Filed: November 29, 2018
    Date of Patent: June 21, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Takeru Chiba, Toru Hoshi
  • Patent number: 11359600
    Abstract: Provided is an aerodynamic structure for mounting to a surface of a wind turbine rotor blade, which aerodynamic structure includes a plurality of rectangular comb elements and/or a plurality of angular comb elements, wherein a comb element includes comb teeth arranged in a comb plane that subtends an angle to the surface of the rotor blade. The embodiments further describe a wind turbine rotor blade including such an aerodynamic structure.
    Type: Grant
    Filed: June 19, 2019
    Date of Patent: June 14, 2022
    Assignee: SIEMENS GAMESA RENEWABLE ENERGY A/S
    Inventor: Stefan Oerlemans
  • Patent number: 11346246
    Abstract: A cooled turbine component in a turbine engine is provided. The cooled turbine component includes a brazed in heat transfer feature, the brazed in heat transfer feature including a thin film including a heat transfer feature incorporated into a surface of the film. The thin film is capable of conforming to a surface of the cooled turbine component and is attached to the surface of the cooled turbine component via a braze material. A method for cooling a turbine component in a turbine engine is also provided.
    Type: Grant
    Filed: December 1, 2017
    Date of Patent: May 31, 2022
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Stephen Erick Holland, Veronica Arocho Pettit, Matthew H. Lang, Andrew Medla
  • Patent number: 11346248
    Abstract: A nozzle segment for a gas turbine engine comprises an outer band having a cooling air inlet, an inner band having a first cooling air outlet, and a nozzle airfoil comprising a cooling flow passage arranged to receive the cooling air as a cooling air stream. A first channel and a second channel are arranged within the cooling flow passage. A deflector is arranged to divide the cooling air stream into a first cooling air stream in the first channel and a second cooling air stream in the second channel, respectively. The deflector deflects the first cooling air stream obliquely to a suction sidewall in the first channel, wherein the first channel is configured to transport the first cooling air stream along the first channel in a swirly flow.
    Type: Grant
    Filed: February 3, 2021
    Date of Patent: May 31, 2022
    Assignee: General Electric Company Polska Sp. Z o.o.
    Inventors: Tomasz Bulsiewics, Leszek Marek Rzeszutek, Maciej Michal Stańczyk, Dariusz Olczak, Jaroslaw Stec
  • Patent number: 11346226
    Abstract: A turbine wheel (100) for a turbocharger includes a hub (110) and blades (120). The hub includes a primary outer surface (116), a back wall surface (115), a peripheral edge (119) extending between the primary outer surface and the back wall surface, and a central axis (111). The hub has a back wall thickness measured parallel to the central axis from the primary outer surface to the back wall surface. The blades (120) extend from the primary outer surface of the hub and are integrally formed with the hub by casting. Each blade has a blade thickness measured tangential to the central axis between opposed surfaces of the blade. A maximum diameter of the peripheral edge is 60 mm or more. Over a majority of a radially outer region (117), a thickness ratio of the blade thickness to the back wall thickness varies by 25% or less. The radially outer region extends from the peripheral edge to a 25% meridional.
    Type: Grant
    Filed: December 22, 2017
    Date of Patent: May 31, 2022
    Assignee: BorgWarner Inc.
    Inventor: Lakshmi Srikar Yellapragada
  • Patent number: 11339662
    Abstract: A rotor of a gas turbine, having two adjacent rotor disks having a plurality of blade-holding grooves for receiving rotor blades, distributed around the periphery thereof, and having an axially extending peripheral ring projection radially beneath the blade-holding grooves. A peripheral rotor component is fixed to the ring projections, between the rotor disks. In order to protect the periphery, the rotor disk or the rotor component includes at least two recesses arranged on the periphery in a distributed manner, in each of which engaging shoulders of the rotor component or the rotor disk engage.
    Type: Grant
    Filed: July 24, 2019
    Date of Patent: May 24, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Peter Kury, Harald Hoell, Karsten Kolk, Vyacheslav Veitsman, Yulia Bagaeva, Christopher W Ross, Peter Schröder, Andrew Waddell
  • Patent number: 11333171
    Abstract: High performance wedge diffusers utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the wedge diffuser includes a diffuser flowbody and tapered diffuser vanes, which are contained in the diffuser flowbody and which partition or separate diffuser flow passages or channels extending through the flowbody. The diffuser flow channels include, in turn, flow channel inlets formed in an inner peripheral portion of the diffuser flowbody, flow channel outlets formed in an outer peripheral portion of the diffuser flowbody, and flow channel throats fluidly coupled between the flow channel inlets and the flow channel outlets. The diffuser vanes include a first plurality of vane sidewalls, which transition from linear sidewall geometries to non-linear sidewall geometries at locations between the flow channel inlets and the flow channel outlets.
    Type: Grant
    Filed: November 18, 2020
    Date of Patent: May 17, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Shakeel Nasir, Nick Nolcheff, Cristopher Frost
  • Patent number: 11326476
    Abstract: A system for coupling a shroud to a case associated with a gas turbine engine and a gas turbine engine including such a system includes the case defining a bore and the shroud retained within the case. The shroud defines a pocket. The system includes a pin received through the bore and at least partially positioned within the pocket. The pin has a perimeter. The system includes a load spreader including a first side and a second side opposite the first side. The first side is interconnected to the second side by a flexible portion. The first side, the second side and the flexible portion are received about a portion of the perimeter of the pin, and the load spreader is configured to transmit at least one of an axial point load and a circumferential point load from the pin over a surface of the shroud.
    Type: Grant
    Filed: October 22, 2020
    Date of Patent: May 10, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Donald Tillman, Ryon James Stanley, Courtney Murphy
  • Patent number: 11326454
    Abstract: A rotor has a rotor body having: a flange with a circumferential array of discontiguous apertures; and a surface spaced apart from the flange. One or more rotor balance weight assemblies each have a weight and a fastener. The weight has: a passageway having a first end and a second end; an internal thread along the passageway; and a boss at the first end of the passageway. The boss is in a respective one of the apertures. The fastener has: a shank having a first end and a second end and an external thread engaged to the passageway internal thread; an engagement feature at the shank first end for engagement by a tool to turn the fastener; and a head at the second end contacts the surface.
    Type: Grant
    Filed: March 20, 2020
    Date of Patent: May 10, 2022
    Assignee: Raytheon Technologies Corporation
    Inventor: Richard W. Rosborough
  • Patent number: 11319824
    Abstract: A rotor for a gas turbine having a rotor disk on which there are a plurality of rotor components distributed around the circumference. The rotor disk has a circumferential securing shoulder with a contact face. Retaining faces come to bear against the contact face, each of the retaining faces have a retaining shoulder of the respective rotor component and are designed with a form that complements the contact face. In order to optimize the bearing stresses between the retaining shoulder and the securing shoulder, the retaining face has a smaller radius than the contact face, namely the retaining radius is at least 0.99 times and at most 0.995 times the contact radius. Also provided is an axially extending aperture in the rotor component, the width of which in the circumferential direction is 25% to 75% of the rotor component width in the circumferential direction.
    Type: Grant
    Filed: April 16, 2019
    Date of Patent: May 3, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Harald Hoell, Kevin Kampka, Peter Schröder
  • Patent number: 11306704
    Abstract: A powertrain for a wind turbine (100) comprises at least a first powertrain component (21, 22, 23, 26) and a second powertrain component (21, 22, 23, 26). A rotating output of the first powertrain component (21, 22, 23, 26) is coupled to a rotating input of the second powertrain component (21, 22, 23, 26) and a powertrain housing enclosing the powertrain components (21, 22, 23, 26), the powertrain housing comprising at least a first powertrain housing section (211, 221, 231, 261) enclosing at least part of the first powertrain component (21, 22, 23, 26) and a second powertrain housing section (211, 221, 231, 261) enclosing at least part of the second powertrain component (21, 22, 23, 26).
    Type: Grant
    Filed: December 11, 2018
    Date of Patent: April 19, 2022
    Assignee: Vestas Wind Systems A/S
    Inventor: Lars Skifter
  • Patent number: 11286783
    Abstract: An airfoil includes an airfoil section that has an airfoil wall that surrounds a cavity. The airfoil wall includes an exterior monolithic ceramic shell and an interior CMC liner that has CMC plies. An outermost ply of the CMC plies forms tabs that are raised from an underlying ply so as to define a slot. The exterior monolithic ceramic shell includes an underlapping shell piece and an overlapping shell piece. The underlapping shell piece has a portion disposed in the slot and bonded with the tabs. The overlapping shell piece extends over the tabs and is bonded to the tabs. There are channels bounded by adjacent ones of the tabs, the underlapping shell piece, and the overlapping shell piece. Channel orifices through the CMC liner connect the cavity and the channels.
    Type: Grant
    Filed: April 27, 2020
    Date of Patent: March 29, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Thomas J. Martin, John E. Holowczak, Matthew B. Kennedy, Paul F. Croteau, Paul Attridge
  • Patent number: 11286944
    Abstract: An oil passage of a centrifugal compressor includes a first oil passage that communicates with an oil pan and a speed increaser chamber to supply oil to a speed increaser and the seal. A second oil passage communicates with the speed increaser chamber. A third oil passage extends upward in a gravitational direction from an end of the second oil passage. A fourth oil passage extends in a horizontal direction and causes the oil pan and an end of the third oil passage to communicate with each other. A pressure relief passage that communicates with an outside is arranged in at least one of a portion of the fourth oil passage through which a gas layer passes and a portion of the oil pan in which the gas layer is stored.
    Type: Grant
    Filed: February 27, 2019
    Date of Patent: March 29, 2022
    Assignee: KABUSHIKI KAISHA TOYOTA JIDOSHOKKI
    Inventors: Ryosuke Fukuyama, Takahito Kunieda, Satoru Mitsuda, Masahiro Suzuki, Ryo Umeyama, Yoshiyuki Nakane
  • Patent number: 11261736
    Abstract: A vane for a gas turbine engine includes an airfoil section that has an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side that bound an internal cavity. The airfoil section has associated characteristics including a center of pressure and an aerodynamic load vector through the center of pressure. The airfoil wall has a single rib connecting the pressure side and the suction side. The single rib is aligned with the aerodynamic load vector.
    Type: Grant
    Filed: September 28, 2020
    Date of Patent: March 1, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jon E. Sobanski, Rutva A. Patel, Robert White, III
  • Patent number: 11255308
    Abstract: The present invention relates to a wind tower (10) for delivering wind flow to a turbine. The wind tower (10) including includes a support structure (12) mounted to a support surface (14) and a wind intake section 16 rotatably mounted to the support structure (12) and elevated with respect to the support surface (14). The intake section (16) includes a plurality of internal passageways (32) extending between a plurality of wind-facing inlets (22) and a plurality of outlets (34). The plurality of inlets (22) are orientated for concurrently receiving an oncoming wind-flow W. Each of the inlets (22) are in fluid communication with one of the outlets 34 via one of the passageways (32). The wind tower (10) further includes an output passageway (42) for collecting wind flow W from the plurality of outlets (34).
    Type: Grant
    Filed: March 8, 2017
    Date of Patent: February 22, 2022
    Inventor: Vaclav Puta
  • Patent number: 11255210
    Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment that is supported by the carrier relative to a high temperature zone. The blade track segment provides a heat shield for use in high temperature applications protecting the carrier and other components.
    Type: Grant
    Filed: October 28, 2020
    Date of Patent: February 22, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.
    Inventors: Ted J. Freeman, Jeremy Roehm
  • Patent number: 11248492
    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotatable shaft defining a longitudinal axis, and a bearing housing extending along the longitudinal axis to define a bearing compartment. The bearing housing has a first seal land defined along an inner diameter of the bearing housing, a seal carrier fixedly attached to an outer periphery of the shaft, and a seal member extending outwardly from the seal carrier. The seal member defines a plurality of helical grooves facing radially outward to establish a first sealing relationship with the first seal land, and each one of the helical grooves has a major component extending in an axial direction relative to the longitudinal axis. A method of sealing for a gas turbine engine is also disclosed.
    Type: Grant
    Filed: March 18, 2019
    Date of Patent: February 15, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Joseph H. Polly, Sean P. McGee