Patents Examined by Ninh H. Nguyen
  • Patent number: 10962022
    Abstract: A diaphragm 1 for a centrifugal compressor having a rear surface 2 configured to at least partly face an impeller 3, the rear surface 2 having a first portion 2a defining at least in part a diffuser 4 and a second portion 2b facing the impeller 3; the diaphragm has a duct 5 provided with an inlet 6 and an outlet 7, the outlet 7 being located on the second portion 2b of the rear surface 2, the inlet 6 being located on the rear surface 2 at a point where the static pressure is higher with respect to the static pressure at the outlet 7.
    Type: Grant
    Filed: October 18, 2017
    Date of Patent: March 30, 2021
    Assignee: NUOVO PIGNONE TECNOLOGIE—S.R.L.
    Inventor: Riccardo Brogelli
  • Patent number: 10961854
    Abstract: A component for use in a gas turbine engine includes a channel configured to port a gas from an inlet along a flow path. The component further includes a wall defining an outlet configured to receive the gas, the wall forming an angle with the flow path that is between 60 degrees and 120 degrees, the outlet having a first portion with a first diameter and a second portion with a second diameter, the first portion configured to receive the gas before the second portion, and the first diameter being greater than the second diameter.
    Type: Grant
    Filed: September 12, 2018
    Date of Patent: March 30, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Timothy J. Jennings, Mark F. Zelesky
  • Patent number: 10961829
    Abstract: An electrical submersible pump comprising a fallback bearing protection system, the system comprising: locking member; boot pivotally connected to shaft of electrical submersible pump adjacent to locking member, wherein the boot comprises a sloped outer wall capable of forming a fluid boundary thereby diverting fallback fluid away from uppermost bearing of electrical submersible pump; ridge disposed on the sloped outer wall of the boot.
    Type: Grant
    Filed: May 29, 2019
    Date of Patent: March 30, 2021
    Assignee: Halliburton Energy Services, Inc.
    Inventors: Wesley John Nowitzki, Jason Eugene Hill, Thomas Gottschalk
  • Patent number: 10961980
    Abstract: An actuator device for a wind power installation, in particular for a rotor blade of a wind power installation, and also to an associated wind power installation and a method of assembly, with an actuator component and a control component, wherein the actuator component has at least one actuator layer with a preferential direction and, substantially parallel to the actuator layer, at least one exciting layer, wherein the actuator layer comprises a photoactuator, wherein the photoactuator is designed to change a strain and/or stress of the actuator layer in the preferential direction on the basis of excitation light, wherein the exciting layer is designed to guide excitation light into the actuator layer, wherein the control component comprises a light source and a light guide, wherein the light source is arranged away from the exciting layer and is connected to the exciting layer by means of the light guide. The actuator device makes it possible to ensure greater operational reliability.
    Type: Grant
    Filed: June 19, 2017
    Date of Patent: March 30, 2021
    Assignee: Wobben Properties GmbH
    Inventor: Andree Altmikus
  • Patent number: 10954799
    Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.
    Type: Grant
    Filed: April 29, 2019
    Date of Patent: March 23, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Pitchaiah Vijay Chakka, James D. Hill, David R. Pack
  • Patent number: 10954864
    Abstract: A power transmission includes an input shaft, an output shaft, and a plurality of gear ratios selectably engagable with the input shaft and the output shaft to transfer rotational energy from the input shaft to the output shaft to drive the output shaft at a selected output shaft speed. A plurality of clutches, each clutch is located at a clutch lay shaft of a plurality of clutch lay shafts and is configured to control selective engagement of only one gear ratio of the plurality of gear ratios.
    Type: Grant
    Filed: March 25, 2019
    Date of Patent: March 23, 2021
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventors: Stephen Michael Bortoli, Aaron M. Finke, Mark J. Franklin
  • Patent number: 10954816
    Abstract: A turbocharge includes: a compressor wheel; a turbine wheel configured to rotate with the compressor wheel; a turbine housing disposed so as to cover the turbine wheel; a bearing supporting a rotational shaft of the turbine wheel rotatably; and a bearing housing accommodating the bearing. One of the turbine housing or the bearing housing includes a fin portion protruding toward the other one of the turbine housing or the bearing housing so as to extend along an axial direction of the rotational shaft, and, between the turbine housing and the bearing housing, a cavity is formed on each side of the fin portion with respect to a radial direction of the rotational shaft.
    Type: Grant
    Filed: September 28, 2017
    Date of Patent: March 23, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Tsuyoshi Kitamura, Seiichi Ibaraki, Toyotaka Yoshida, Hiroshi Suzuki, Motoki Ebisu
  • Patent number: 10954955
    Abstract: A centrifugal fan assembly comprises a blade assembly integrally formed. The blade assembly comprises a plurality of blades integrally formed, wherein each blade of the plurality of blades has a twisted shape with a first portion of a hub end of the each blade facing a first adjacent blade, and a second portion of a outer end of the each blade diagonal to the first portion of the hub end facing a second adjacent blade, a fixing portion integrally connected to the blades. The centrifugal fan assembly comprises at least one opening formed in the fixing portion and a hub plate comprising a recessed portion and a convex portion enabled to couple to the blade assembly. The concave portion is provided to correspond to a shape of the fixing portion and the convex portion is provided to correspond to a shape of the at least one opening.
    Type: Grant
    Filed: November 26, 2018
    Date of Patent: March 23, 2021
    Assignee: SAMSUNG ELECTRONICS CO., LTD.
    Inventors: Hooi Joong Kim, Ho Choi
  • Patent number: 10947959
    Abstract: A method of performing maintenance on a wind turbine component (18, 22, 24) of a wind turbine (10) having an integrated lifting apparatus (40). The method includes lifting a first temporary support (104) using the integrated lifting apparatus (40), coupling the first temporary support (104) to the nacelle (12) or the hub (16) and the integrated lifting apparatus (40), removing the wind turbine component (18, 22, 24) using the integrated lifting apparatus (40) and the first temporary support (104) in combination. The method may further include installing a replacement wind turbine component (18, 22, 24) using at least a part of the integrated lifting apparatus (40) and the first temporary support (104) in combination, decoupling the first temporary support (104) from the nacelle (12) or the hub (16) and the integrated lifting apparatus (40), and removing the first temporary support (104) from the wind turbine (10) using the integrated lifting apparatus (40).
    Type: Grant
    Filed: August 11, 2017
    Date of Patent: March 16, 2021
    Assignee: MHI Vestas Offshore Wind A/S
    Inventor: Tomohiro Numajiri
  • Patent number: 10947901
    Abstract: Gas turbine engine (GTE) compressor sections and compressor intake ducts are provided having Soft Foreign Object debris (SFOD) endwall treatments, which reduce peak damage to GTE components in the event of SFOD ingestion. In embodiments, the GTE compressor section includes a compressor rotor and a compressor intake duct. The compressor intake duct includes an intake flow passage, which extends through compressor intake duct to the compressor rotor. A first duct endwall extends around a centerline of the flow passage to bound a peripheral portion of the intake flow passage. An SFOD endwall treatment includes topological features formed in or otherwise provided on the first duct endwall. The topological features of the SFOD endwall treatment are configured such that SFOD impacting the topological features is directed in a radially inward direction toward the flow passage centerline prior discharge of the SFOD from the intake flow passage and into the compressor rotor.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: March 16, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Timothy Darling, Costantinos Vogiatzis
  • Patent number: 10947864
    Abstract: A gas turbine having a turbine casing, an outer and inner casing part between which a hot gas flows. An annular duct is formed between the outer casing part and the turbine casing to accommodate a cooling fluid. An exhaust gas casing is positioned downstream in the flow direction of the hot gas. A bearing system for a rotor has bearing struts arranged around the circumference which extend from a shaft bearing to an outer casing and, in the hot gas path of an exhaust gas diffuser arranged in the exhaust gas casing are shielded by another strut set which surrounds the bearing struts and is hollow to support the diffuser, wherein, to center the turbine and the exhaust gas casing, these are connected to one another via a fit wherein the turbine and the exhaust gas casing can be supplied with cooling air independently of one another.
    Type: Grant
    Filed: July 28, 2017
    Date of Patent: March 16, 2021
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventors: Dirk Allebrod, Stephan Sonnen
  • Patent number: 10941664
    Abstract: A component for a turbine engine includes a body having a wall separating a combustion air flow path from a cooling air flow path. The component can include an isolation chamber formed in the cooling air flow path. The component can also include at least one cyclone separator having a cooling air inlet fluidly coupled to the cooling air flow path.
    Type: Grant
    Filed: March 18, 2019
    Date of Patent: March 9, 2021
    Assignee: General Electric Company
    Inventors: Daniel Endecott Osgood, Jonathan Russell Ratzlaff, Kirk D. Gallier
  • Patent number: 10941674
    Abstract: An assembly for a gas turbine engine includes a first casing, a second casing, and struts extending from the first casing to support the second casing. The assembly further includes a fairing and a multi-piece heat shield assembly. The fairing is disposed between the first casing and the second casing and around each of the struts. The multi-piece heat shield assembly includes a first shield extending between the first casing and the fairing, and a second shield extending between the fairing and the first casing. The multi-piece heat shield assembly further includes a third shield extending between the fairing and the second casing, and fourth and fifth heat shields extending from the third heat shield between the fairing and each of the struts.
    Type: Grant
    Filed: April 19, 2019
    Date of Patent: March 9, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Matthew Budnick, Conway Chuong, Jonathan Ariel Scott, Darrell Weidner, Chris Bates
  • Patent number: 10941666
    Abstract: A multi-stage axial turbine (typically between 4 and 10 stages) designed to operate more efficiently with partial admission of low temperature steam in each stage except the last one or two stages. Each stage of the subject turbine operates efficiently with smaller pressure drops thereby maintaining much smaller reductions in fluid density per stage. Each stage has blisks built as a single piece and the steam passages built into the periphery of the blisks. Each subsequent stage then only requires a small increase in flow area that can be achieved by using only a small increase in admission and blade height.
    Type: Grant
    Filed: October 24, 2017
    Date of Patent: March 9, 2021
    Assignee: Intex Holdings Pty Ltd
    Inventor: Roger Davies
  • Patent number: 10934842
    Abstract: Provided is a turbocharger, including: a compressor impeller (impeller) having a through hole; a shaft inserted through the through hole; and a fastening member caulked to a distal end portion of the shaft projecting from the through hole.
    Type: Grant
    Filed: January 23, 2019
    Date of Patent: March 2, 2021
    Assignee: IHI Corporation
    Inventor: Yoshimitsu Matsuyama
  • Patent number: 10934848
    Abstract: In a fan blade of a turbofan engine and a method for determining a shape of the fan blade, a shape from a blade root of the fan blade up to a predetermined position in a span direction of the fan blade is same as a shape from a blade root of an original fan blade up to a predetermined position in a span direction of the original fan blade, and a shape from the predetermined position in the span direction of the fan blade up to a blade tip thereof is a shape formed by rotating, only by a predetermined angle in a direction opposite to a direction of rotation of the fan blade with a rotating shaft as a center, each of blade elements present from the predetermined position in the span direction of the original fan blade up to a blade tip thereof.
    Type: Grant
    Filed: January 30, 2019
    Date of Patent: March 2, 2021
    Assignee: HONDA MOTOR CO., LTD.
    Inventor: Yu Narita
  • Patent number: 10934892
    Abstract: An axial flow turbine comprising a casing, a rotor having an axial rotational axis and rotatably mounted into the casing, at least one set of a plurality of moving blades supported by the rotor; and at least one diaphragm having an outer ring, an inner ring, concentric to the outer ring, and a plurality of static blades mounted therebetween, at least the outer ring being split in an upper half and a lower half along a vertical joint plane. The turbine diaphragm comprises an assembly system for assembling the upper half to the lower half while allowing the upper half and the lower half to move axially relative to each other.
    Type: Grant
    Filed: August 3, 2017
    Date of Patent: March 2, 2021
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Julien Lemaire, Eric Ollivau, Dominique Travers
  • Patent number: 10927685
    Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 1750 degree Fahrenheit, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.
    Type: Grant
    Filed: July 19, 2018
    Date of Patent: February 23, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Kevin Seymour, Christopher W. Strock, Thomas D. Kasprow
  • Patent number: 10927757
    Abstract: A method of reducing rotor bow in a high pressure rotor of a gas turbine engine that has in axial flow a low pressure rotor and a high pressure rotor. The method involves storing bleed air from the gas turbine engine when the engine is running to provide stored pneumatic energy; and using that stored pneumatic energy after the engine has been shut-down to rotate the high pressure rotor at a speed and for a duration that reduces rotor bow. A gas turbine engine wherein rotor bow in the high pressure rotor after engine shut-down has been reduced by carrying out the aforesaid method is also disclosed.
    Type: Grant
    Filed: November 29, 2018
    Date of Patent: February 23, 2021
    Assignee: ROLLS-ROYCE PLC
    Inventor: Andrew Stevenson
  • Patent number: 10927681
    Abstract: Disclosed herein is a gas turbine blade. The gas turbine blade includes a turbine blade (33) provided in a turbine, and film cooling elements (100), each including a cooling channel (110) for cooling of the turbine blade (33), an outlet (120) through which cooling air is discharged, and a plurality of ribs (130), wherein the outlet (120) extends from a longitudinally extended end of the cooling channel (110) to an outer surface of the turbine blade (33) and has a width increased from one end of the cooling channel (110) to the outer surface of the turbine blade (33), and the ribs (130) face each other on inner walls of the outlet (120).
    Type: Grant
    Filed: August 22, 2017
    Date of Patent: February 23, 2021
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Ki Don Lee