Patents Examined by Brian O Peters
  • Vacuum pump
    Patent number: 11125245
    Abstract: A vacuum pump housing a rotor, comprises: a first case including a first flange; and a second case including a second flange, connected to the first case through the first flange and the second flange, and arranged on an exhaust port side with respect to the first case. The first flange and the second flange are fastened to each other with a bolt, and the first flange includes a first recessed portion formed corresponding to an attachment position of the bolt at a surface, and the second flange includes a second recessed portion formed corresponding to the attachment position of the bolt at a surface.
    Type: Grant
    Filed: October 26, 2019
    Date of Patent: September 21, 2021
    Assignee: Shimadzu Corporation
    Inventor: Kota Watanabe
  • Reciprocal motion wind energy harvesting device
    Patent number: 11125208
    Abstract: A reciprocal motion wind energy harvesting device has a first lever arm assembly and a second lever arm assembly, which are supported by and rotate about a central shaft. The lever arm assemblies have pluralities of vanes along their length to receive wind force. The vanes are configured to be rotatable in order to produce opposing and reciprocating motion of the lever arm assemblies. The lever arm assemblies are operatively connected to a generator in order to convert the wind force received by the vanes into energy.
    Type: Grant
    Filed: July 3, 2019
    Date of Patent: September 21, 2021
    Inventor: Johnnie Ace Williams
  • Axial flow wind wheel and air conditioner
    Patent number: 11125238
    Abstract: The present disclosure provides an axial flow wind wheel and an air conditioner, the axial flow wind wheel includes a wheel hub and a plurality of blades, the blades are arranged on the wheel hub at intervals, the blade includes a front blade edge and a rear blade edge arranged from front to back, and a top blade edge connecting to outer ends of the front blade edge and the rear blade edge, the top blade edge defines a cut surface inclining from a pressure surface to a suction surface of the blade, and the cut surface extends from the front blade edge to the rear blade edge, the cut surface includes an outer cut edge defined at the top blade edge, and an inner cut edge defined at the pressure surface, and the inner cut edge is defined to concave inwards and protrude outwards, forming a concave-convex shape.
    Type: Grant
    Filed: June 17, 2019
    Date of Patent: September 21, 2021
    Assignees: GD MIDEA AIR-CONDITIONING EQUIPMENT CO., LTD., MIDEA GROUP CO., LTD.
    Inventors: Bo Wang, Xujie Cai, Hejie Zhou
  • Centrifugal impeller for gas turbine engine
    Patent number: 11125154
    Abstract: The centrifugal impeller can have a hub and a plurality of blades, each of the blades having a span extending from the hub to a tip edge, camber lines extending from an inlet edge to an outlet edge between two opposite faces, including a tip camber line extending along the tip edge and a 50% span camber line extending at 50% of the span, a thickness extending between opposite faces of each blade, the tip edge having, at a location corresponding to 5% of the tip camber line, less than 15% of the maximum thickness, each of the blades having, along the 50% span camber line, a thickness reaching at least 58% of the maximum thickness and then reducing by at least 5% of the maximum thickness within 10% of the length of the 50% span camber line.
    Type: Grant
    Filed: November 5, 2019
    Date of Patent: September 21, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jason Nichols, Ignatius Theratil, Mohammadreza Amiralaei
  • Ceiling fan
    Patent number: 11125241
    Abstract: A ceiling fan includes a support unit, a stator, a rotor and a lamp. The support unit includes an axle and a magnetic disc fit around the axle. The stator is fit around the axle. The rotor has a plurality of blades rotatably mounted to the axle. The lamp includes a housing and a light emitting portion below a magnetic top face of the housing. The magnetic top face of the housing is attracted to the magnetic disc.
    Type: Grant
    Filed: August 22, 2019
    Date of Patent: September 21, 2021
    Assignee: Sunonwealth Electric Machine Industry Co., Ltd.
    Inventors: Alex Horng, Tso-Kuo Yin, Chung-Hao Tsai
  • Turbofan arrangement with blade channel variations
    Patent number: 11118459
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a fan including a rotor hub rotatable about an engine longitudinal axis and an array of fan blades, a geared architecture, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine. The low pressure turbine drives the fan through the geared architecture. Each fan blade of the array of fan blades includes pressure and suction sides and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, and facing pressure and suction sides of adjacent fan blades define a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent fan blades.
    Type: Grant
    Filed: July 23, 2019
    Date of Patent: September 14, 2021
    Assignee: AYTHEON TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Sue-Li Chuang
  • Wind turbine generator system, wind turbine blade, and reinforcing method for wind turbine blade
    Patent number: 11118563
    Abstract: A wind turbine blade is reinforced while suppressing possible stress concentration resulting from a load imposed on a blade root portion of the wind turbine blade in a flap direction. The wind turbine blade includes a blade main body extending from the blade root portion toward a blade tip portion and an FRP reinforcing layer formed so as to cover at least a part of the outer surface of the blade root portion of the blade main body. The FRP reinforcing layer includes a plurality of laminated fiber layers and a resin with which the plurality of fiber layers is impregnated. The FRP reinforcing layer is formed such that, in a cross section along a longitudinal direction of the blade main body, both ends of the plurality of laminated fiber layers in the longitudinal direction are tapered.
    Type: Grant
    Filed: June 26, 2018
    Date of Patent: September 14, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Yasutaka Kimura, Takao Kuroiwa, Keisuke Ota
  • Coanda effect bearing cooler
    Patent number: 11111961
    Abstract: A compact, energy efficient air cooling system for a rotating shaft bearing module includes a Coanda surface having a periphery that smoothly curves from a radial center to axial alignment with a side of the module. A fan blade mounted on the shaft directs an airflow radially parallel and adjacent to the Coanda surface, causing the airflow to be bent by the Coanda effect from radial to axial, and to be directed along the side of the housing. Embodiments that can be applied to existing housings include a Coanda panel adjacent to the housing end face. A double suction fan blade can draw both external air and air from between the panel and the housing. In other embodiments the housing end face itself is a Coanda surface. A fan cover can have an inwardly curved periphery that forms a reduced gap or nozzle with the Coanda surface.
    Type: Grant
    Filed: January 10, 2018
    Date of Patent: September 7, 2021
    Assignee: Flowserve Management Company
    Inventors: Scott C. Judge, Andrew Todd Koehler, Stephen R. Schappert
  • Counter rotating power turbine with reduction gearbox
    Patent number: 11105200
    Abstract: The present disclosure is directed to a turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction. The turbine engine includes a power turbine including a first turbine rotor assembly interdigitated with a second turbine rotor assembly along the longitudinal direction; a gear assembly coupled to the first turbine rotor assembly and the second turbine rotor assembly, wherein the gear assembly includes a first input interface coupled to the first turbine rotor assembly, a second input interface coupled to the second turbine rotor assembly, and one or more third gears coupled to the first input interface and the second input interface therebetween; and a first output shaft and a second output shaft, wherein each of the first output shaft and the second output shaft are configured to couple to an electrical load device.
    Type: Grant
    Filed: July 13, 2017
    Date of Patent: August 31, 2021
    Assignee: General Electric Company
    Inventors: Jeffrey Donald Clements, Darek Tomasz Zatorski, Brandon Wayne Miller, Joseph Robert Dickman
  • Steam turbine
    Patent number: 11105201
    Abstract: A steam turbine includes: a rotor; a casing; a thrust bearing; a steam inlet; a first pipe; a first regulation valve; a second pipe; a second regulation valve; and a control device. The control device estimates an exhaust flow rate of the steam turbine based on an operating point map which derives the exhaust flow rate of the steam turbine from an operating point of the steam turbine and estimates the thrust force applied to the thrust bearing based on the exhaust flow rate.
    Type: Grant
    Filed: March 16, 2017
    Date of Patent: August 31, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventor: Takuro Koda
  • Compressor and method for determining blade deformation and gas turbine including the compressor
    Patent number: 11092073
    Abstract: A compressor for a gas turbine having means for determining whether a blade of the compressor has been deformed includes a rotor having an outer circumference on which a blade is formed; a monitoring part for monitoring a driving state of the blade in order to acquire monitoring information on the driving state of the blade; and a control part for determining whether the blade has been deformed based on the monitoring information. The monitoring part detects time points at which the trailing edge and the leading edge of the blade pass and acquire the detection time information of the detected time point. The control part receives the detection times of the trailing edge and the leading edge from the monitoring part and determines whether the blade has been deformed based on the detection time of the trailing edge and the detection time of the leading edge.
    Type: Grant
    Filed: March 7, 2019
    Date of Patent: August 17, 2021
    Inventor: Sang Jo Kim
  • Systems and methods for redirection of airflow in an information handling system after an air mover fault
    Patent number: 11089713
    Abstract: A vane assembly may be configured to mechanically couple to a first air mover and a second air mover, and the vane assembly may include a first set of one or more vanes configured to be proximate to the first air mover when the vane assembly is mechanically coupled to the first air mover and the second air mover and a second set of one or more vanes configured to be proximate to the second air mover when the vane assembly is mechanically coupled to the first air mover and the second air mover.
    Type: Grant
    Filed: November 11, 2019
    Date of Patent: August 10, 2021
    Assignee: Dell Products L.P.
    Inventors: Eduardo Escamilla, Corey D. Hartman, Zhen Huang
  • Return stage of a multi-staged compressor or expander with twisted guide vanes
    Patent number: 11073162
    Abstract: A return stage through which a process fluid is designed to flow along a throughflow direction of a radial turbomachine, wherein the return stage extends in annular fashion about an axis and is defined radially inwardly by an inner delimiting contour and radially outwardly by an outer delimiting contour. At least one guide vane stage including guide vanes extends at least along a part of the third section and segments the return stage in the circumferential direction into flow channels, wherein in each case a profile midline of a profile cross section defines an inner track on the side of the inner delimiting contour and an outer track on the side of the outer delimiting contour. A radial turbomachine includes at least one such return stage.
    Type: Grant
    Filed: January 9, 2018
    Date of Patent: July 27, 2021
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventor: Viktor Hermes
  • Mistuned airfoil assemblies
    Patent number: 11073021
    Abstract: A mistuned airfoil assembly for a gas turbine engine is disclosed. The mistuned airfoil assembly may comprise a hub and airfoils extending radially from the hub. The airfoils may consist of first airfoils and at least one second airfoil. The first airfoils may be formed from a first titanium alloy and the at least one second airfoil may be formed from a second titanium alloy. The first titanium alloy and the second titanium alloy may have different natural frequencies.
    Type: Grant
    Filed: August 15, 2019
    Date of Patent: July 27, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Charles H. Roche
  • Gas turbine engine variable pitch fan blade
    Patent number: 11073087
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section. The fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed and a fixed area fan nozzle in communication with the fan section.
    Type: Grant
    Filed: February 24, 2014
    Date of Patent: July 27, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • Constant-velocity joint link with reduced axial stiffness
    Patent number: 11066157
    Abstract: The present application provides a drive link for a constant-velocity joint of an aircraft rotor, the link connecting a drive hub attached to a driveshaft to a rotor yoke. The link comprises a leading bearing connected to the drive hub, a trailing bearing connected to the yoke, a central portion between the bearings, and a tension loop connecting the bearings. The tension loop is formed from a composite material and is formed as a continuous band. The tension loop transfers drive forces from the leading bearing to the trailing bearing for driving the yoke in rotation with the driveshaft.
    Type: Grant
    Filed: June 12, 2018
    Date of Patent: July 20, 2021
    Assignee: Bell Textron Inc.
    Inventors: Richard E. Rauber, Frank B. Stamps
  • Planetary gear drive and aircraft gas turbine with a planetary gear drive
    Patent number: 11060419
    Abstract: The invention relates to a planetary gearbox having a ring gear support, in particular in a geared fan engine, characterized by a bolt connection for connecting the ring gear support to a static component, wherein the bolt connections are arranged on the circumference of the ring gear support in the axial direction of the planetary gearbox, and the bolt connections are designed and arranged in such a way that there is a frictional joint with a defined frictional force between the ring gear support and the static component and that a material separation, in particular a gap, is arranged between the ring gear support and the static component.
    Type: Grant
    Filed: May 29, 2019
    Date of Patent: July 13, 2021
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Hannes Wuestenberg
  • Turbine engine
    Patent number: 11053947
    Abstract: A gas turbine engine for an aircraft includes an engine core including a turbine, compressor, and core shaft connecting turbine to compressor; a fan located upstream of the engine core and including a plurality of fan blades each having a leading and trailing edge. The turbine includes a lowest pressure turbine stage having a row of rotor blades, each rotor blades extending radially and having a leading and trailing edge. The engine has a fan tip axis that joins a radially outer tip of the leading edge of a fan blade and the radially outer tip of the trailing edge of a rotor blade of the lowest pressure stage. The fan tip axis lies in a longitudinal plane which contains a centreline of engine. A fan axis angle is defined as the angle between fan tip axis and centreline, and is in a range between 10 and 20 degrees.
    Type: Grant
    Filed: March 20, 2020
    Date of Patent: July 6, 2021
    Assignee: ROLLS-ROYCE plc
    Inventors: Richard G Stretton, Michael C Willmot
  • Centrifugal rotary machine
    Patent number: 11041497
    Abstract: A centrifugal rotary machine includes: an impeller which includes a disk, blades, and a cover; and a sealing device which seals the gap, in which the casing includes an end wall surface which defines a radial flow path between the end wall surface and a cover end surface, an inlet-side inner peripheral surface which is connected to a radially inner side of the end wall surface and extends to the one side in the axial direction so as to define an introduction flow path of a fluid to the impeller, and a circulation flow path which is formed in the casing and is open to an end portion on a radially outer side of the end wall surface and the inlet-side inner peripheral surface to cause the radial flow path and the introduction flow path to communicate with each other.
    Type: Grant
    Filed: February 8, 2017
    Date of Patent: June 22, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Akihiro Nakaniwa, Shinichiro Tokuyama
  • Turbomachine blade with optimised cooling
    Patent number: 11035235
    Abstract: A turbine blade of a turbine engine such as a turbojet engine, comprising: a root supporting a blade and extending in a wingspan direction, ending in a vertex, the blade comprising a leading edge and a trailing edge, with a pressure side wall and a suction side wall separated from one another and connecting the leading edge (17) to the trailing edge, the blade also comprising: cooling ducts in which air collected at the blade root circulates; first and second inner side recesses running along the pressure side wall in order to form a heat shield spaced apart from one another along the pressure side wall; and at least one duct extending from the pressure side wall to the suction side wall between the first and second side recesses.
    Type: Grant
    Filed: October 18, 2017
    Date of Patent: June 15, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Charlotte Marie Dujol, Sébastien Serge Francis Congratel, Patrice Eneau, Léandre Ostino, Michel Slusarz