Patents Examined by Ninh H. Nguyen
  • Patent number: 11401943
    Abstract: An impeller includes a hub, a plurality of blades coupled with the hub, and a plurality of ribs connected to the plurality of blades. Each of the plurality of ribs has a connecting end coupled with the hub. Each of the plurality of blades intersects with at least one of the plurality of ribs.
    Type: Grant
    Filed: June 22, 2020
    Date of Patent: August 2, 2022
    Assignee: SUNON ELECTRONICS (KUNSHAN) CO., LTD.
    Inventors: Alex Horng, Chi-Min Wang
  • Patent number: 11401944
    Abstract: The impeller includes a disc having a main surface extending outward in a radial direction toward one side in an axial direction, a plurality of blades defining a flow path extending to an outlet on one side from an inlet on the other side in the axial direction, and a cover disposed to cover the plurality of blades. At least one of an inlet side region and an outlet side region which are a connection portion between the blade and the main surface and a connection portion between the blade and the cover has a small fillet portion curved in an arc shape and having a small radius of curvature. An intermediate region formed between the inlet side region and the outlet side region has a large fillet portion having a large radius of curvature.
    Type: Grant
    Filed: March 2, 2021
    Date of Patent: August 2, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Shuichi Yamashita, Miku Kuroda, Hiroaki Oka
  • Patent number: 11396885
    Abstract: A screw system including a plurality of segmented blades. Each blade segment of the plurality of blade segments including a mounting portion and a vane portion. The mounting portion, having a helical length, for removably attaching the blade segment. The vane portion extending from the mounting portion along the helical length thereof. The vane portion having a front surface that is not parallel to a back surface from the mounting portion to a tip of the blade segment, along the helical length.
    Type: Grant
    Filed: November 25, 2020
    Date of Patent: July 26, 2022
    Assignee: Percheron Power, LLC
    Inventors: Jerry L. Straalsund, Sharon D. Atkin, Nicholas Z. Hertelendy
  • Patent number: 11396817
    Abstract: A gas turbine blade having a casted metal airfoil, the airfoil has a main wall defining at least one interior cavity, having a first side wall and a second side wall, which are coupled to each other at a leading edge and a trailing edge, extending in a radial direction from a blade root to a blade tip and defining a radial span from 0% at the blade root to 100% at the blade tip. The main airfoil has a radial span dependent chord length defined by a straight line connecting the leading edge and the trailing edge as well as a radial span dependent solidity ratio of metal area to total cross-sectional area. Solidity ratios in a machined zone of the airfoil from 80% to 85% of span are below 35%, in particular all solidity ratios in the zone.
    Type: Grant
    Filed: January 8, 2019
    Date of Patent: July 26, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Daniel M. Eshak, Susanne Kamenzky, Andrew Lohaus, Daniel Vöhringer, Samuel R. Miller, Jr.
  • Patent number: 11391179
    Abstract: The gas turbine engine can have a structure for holding bearings within a casing, with a shaft being rotatably mounted to the casing via the bearings and via the structure, the structure having a first wall segment and a base structure receiving the bearings, the first wall segment having a proximal end structurally joined to the base structure, the first wall segment extending away from the base structure, and having a portion extending at least partially axially and thereby being radially flexible relative to the second wall segment, the structure providing both structural resistance and radial stretchability.
    Type: Grant
    Filed: February 12, 2019
    Date of Patent: July 19, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Remy Synnott, François Doyon
  • Patent number: 11391162
    Abstract: A spar for a vane arc segment of a gas turbine engine includes an elongated spar leg that has a spar wall that circumscribes a core passage. There is a plenum passage embedded in the spar wall between inner and outer portions of the spar wall. The inner portion of the spar wall is fully solid such that the plenum passage is fluidly isolated from the core passage. The outer portion of the spar wall has a plurality of cooling through-holes for emitting cooling air from the plenum passage.
    Type: Grant
    Filed: December 15, 2020
    Date of Patent: July 19, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jon E. Sobanski, Howard J. Liles
  • Patent number: 11391178
    Abstract: A cooling fluid distribution element intended to be fixed to a support structure for supplying cooling fluid to a wall to be cooled, typically a turbine ring sector, facing it, the distribution element including a body defining a cooling fluid distribution internal volume and a multi-perforated plate which delimits this internal volume and includes a plurality of outlet through-perforations which put the internal volume into communication with the turbine ring sector, the distribution element further including an inlet orifice opening into the cooling fluid distribution internal volume, which internal volume includes directional fins for directing this cooling fluid from this inlet orifice to the outlet through-perforations.
    Type: Grant
    Filed: October 16, 2018
    Date of Patent: July 19, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Pierre Jean-Baptiste Metge, Sébastien Serge Francis Congratel, Lucien Henri Jacques Quennehen
  • Patent number: 11391160
    Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.
    Type: Grant
    Filed: June 4, 2019
    Date of Patent: July 19, 2022
    Assignee: Raytheon Technologies Inc.
    Inventors: Troy Shannon Prince, Matthew E. Bintz, Charles P. Gendrich
  • Patent number: 11384647
    Abstract: A composite blade formed by laying up composite layers containing reinforcing fiber and resin, the composite blade comprising: a blade root mounted in a blade groove; an airfoil extending from the blade root to a front end side; and a metal patch mounted between the blade groove and the blade root, and bonded to the blade root.
    Type: Grant
    Filed: February 14, 2020
    Date of Patent: July 12, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Ryoji Okabe, Masami Kamiya, Kentaro Shindo
  • Patent number: 11378093
    Abstract: A rotor for a compressor includes a hub and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip. Each of the airfoils is coupled to the hub at the root and is spaced apart from adjacent ones of the airfoils over the span by a throat dimension. The throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the airfoils. The throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value that is less than 70% of the maximum value.
    Type: Grant
    Filed: October 1, 2020
    Date of Patent: July 5, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: David Richard Hanson, John A. Gunaraj, Jeffrey Hayes, Nick Nolcheff, John Repp
  • Patent number: 11378095
    Abstract: A centrifugal compressor includes an impeller, a compressor inlet pipe for guiding air to the impeller, a scroll passage disposed on an outer peripheral side of the impeller, and a bypass passage connecting the compressor inlet pipe and the scroll passage and bypassing the impeller. In a cross-section perpendicular to an axis of the compressor inlet pipe, when A1 is a connection portion on a downstream side in a rotational direction of the impeller of connection portions between an inner wall surface of the compressor inlet pipe and an inner wall surface of the bypass passage, C is a virtual circle constituting the inner wall surface of the compressor inlet pipe, and L1 is a tangent line of the virtual circle C at the connection portion A1, the inner wall surface of the bypass passage is formed from the connection portion A1 along the tangent line L1.
    Type: Grant
    Filed: July 13, 2018
    Date of Patent: July 5, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Yoshihiro Hayashi, Yutaka Fujita, Kenichiro Iwakiri
  • Patent number: 11371524
    Abstract: A windmill, including a first end plate, a second end plate, and a plurality of primary blades disposed between the first end plate and the second end plate. The first end plate includes a central part provided with a base connected to a motor shaft. The second end plate includes a central part provided with an air inlet; the space between every two adjacent blades forms an air channel. The plurality of primary blades each includes an outmost end with respect to the central part of the first end plate, and the outmost end extends out of an outer edge of the second end plate. The connection line of every two adjacent outmost ends of the plurality of primary blades forms a circle, and the diameter D1 of the circle is larger than the diameter D2 of the second end plate.
    Type: Grant
    Filed: June 16, 2020
    Date of Patent: June 28, 2022
    Assignee: ZHONGSHAN BROAD-OCEAN MOTOR CO., LTD.
    Inventors: Yanhu Lin, Miao Zhang, Wei Lei
  • Patent number: 11371526
    Abstract: A compressor for a heating, ventilating, air conditioning, and refrigeration (HVAC&R) unit includes an impeller, a shaft configured to rotate the impeller, and a fastener. The impeller includes an opening and does not include keys, splines, pins, or any combination thereof. The fastener is coupled to an end of the shaft and extends through the opening of the impeller, and the fastener is configured to stretch in an axial direction relative to the shaft via a tensioner during assembly of the compressor.
    Type: Grant
    Filed: September 25, 2018
    Date of Patent: June 28, 2022
    Assignee: Johnson Controls Tyco IP Holdings LLP
    Inventor: Paul William Snell
  • Patent number: 11371525
    Abstract: The present disclosure provides a centrifugal fan blade, an air treatment device and a fan; the centrifugal fan blade includes a hub and a plurality of fan blades; the plurality of fan blades are distributed around the periphery of the hub; each fan blade includes a first blade and a second blade; moreover, the first blade is in a backward blade form; and the second blade is in a forward blade form. The centrifugal fan blade can improve the flowing of the airflow and improve the air output efficiency.
    Type: Grant
    Filed: May 17, 2019
    Date of Patent: June 28, 2022
    Assignee: Gree Electric Appliances, Inc. of Zhuhai
    Inventors: Xixi Kuang, Cheng Zeng, Zhongmei Wei, Weixue Lin, Ge Yu
  • Patent number: 11371534
    Abstract: Provided is a compressor including: a compressor body that has a motor and compresses air; an aftercooler for cooling the compressed air supplied from the compressor body; a dryer for dehumidifying the compressed air flowing out from the aftercooler; a drain discharge valve for discharging a drain from the dryer; a first pressure sensor for measuring air pressure downstream of the aftercooler; and a control device having a rotation-speed adjusting unit that drives the motor at second acceleration smaller than first acceleration, the first acceleration being rated acceleration of the motor, when a pressure value measured by the first pressure sensor is less than a first threshold value predetermined at startup of the motor.
    Type: Grant
    Filed: July 3, 2019
    Date of Patent: June 28, 2022
    Assignee: KOBELCO COMPRESSORS CORPORATION
    Inventors: Katsunori Hamada, Shuto Yakubo, Akira Hoshikawa
  • Patent number: 11371515
    Abstract: In accordance with one aspect the present invention may comprise a regenerative blower comprising: a housing, a first port and second port in the housing, an airflow channel extending between the first and second ports for airflow between the ports, an impeller rotatable in an impeller channel to promote airflow in the airflow channel from the first port to the second port, a motor to drive the impeller, and an interrupter between the first and second ports to limit airflow from the second port to the first port.
    Type: Grant
    Filed: February 11, 2018
    Date of Patent: June 28, 2022
    Assignee: Fisher & Paykel Healthcare Limited
    Inventors: Donald Roy Kuriger, Johannes Nicolaas Bothma
  • Patent number: 11371532
    Abstract: An inlet collector for a centrifugal fan and a centrifugal fan are provided. By arranging a tragus-shaped section in a guiding section, reverse flow caused by intersection of inlet leakage flow at a volute tongue side and inlet airflow is blocked by the tragus-shaped structure in movement process, and the leakage flow no longer collide with the inlet airflow. An inner curved surface of the tragus-shaped section controls backflow to change smoothly along an inner wall surface of the tragus-shaped section and re-enter a volute for circulation. A tragus profile is adopted to guide the airflow to change more smoothly in the velocity direction near the wall of the guiding section, so as to effectively reduce the impact of the inlet airflow on the guiding section. By using the inlet collector, energy loss of airflow is reduced, vortex formation is suppressed, and aerodynamic performance and fan noise are improved.
    Type: Grant
    Filed: January 18, 2022
    Date of Patent: June 28, 2022
    Assignee: XI'AN JIAOTONG UNIVERSITY
    Inventors: Xiaomin Liu, Chenye Tian, Jiahao Wang, Guang Xi
  • Patent number: 11371383
    Abstract: A system and a method for inspecting components of a turbojet engine using RFID tags and an associated interrogator device. The inspection system includes at least one RFID tag associated with a component of the turbojet engine and an interrogator device arranged so as to be able to communicate with the RFID tag, the interrogator device being equipped with an RFID antenna arranged so as to be able to be inserted into a nacelle compartment of the turbojet engine through an inspection opening intended for the passage of an endoscope probe.
    Type: Grant
    Filed: July 24, 2019
    Date of Patent: June 28, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Tony Alain Roger Joël Lhommeau, Guillaume Philippe Camille Bastard, Hervé Jean Albert Mouton, Philippe Roger Jacques Canteau
  • Patent number: 11365647
    Abstract: A gas turbine engine de-icing system includes a heat exchanger. A coolant loop is in fluid communication with the heat exchanger and is configured to circulate a heat transfer fluid. An engine oil loop is in fluid communication with the heat exchanger and is configured to transfer heat to the heat transfer fluid. A gas turbine engine inlet structure has at least one fan inlet guide vane. A spray bar is disposed at least partially in at least one fan inlet guide vane. The spray bar is in fluid communication with the coolant loop. The spray bar is configured to spray the heat transfer fluid onto an inner surface of the at least one fan inlet guide vane to de-ice the fan inlet guide vane.
    Type: Grant
    Filed: February 28, 2020
    Date of Patent: June 21, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Ian T. Marchaj
  • Patent number: 11365688
    Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.
    Type: Grant
    Filed: June 10, 2021
    Date of Patent: June 21, 2022
    Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis