Patents Examined by Richard Edgar
  • Patent number: 11028724
    Abstract: The present invention provides a partial admission operation turbine apparatus comprising: a rotor portion rotatably coupled to a rotary shaft of a turbine and including a plurality of rotor blades; a nozzle portion fixedly coupled to the rotary shaft in front of the rotor portion and guiding and supplying a working fluid to the rotor blades through a plurality of nozzle blades; and an inlet disk coupled to the rotary shaft in front of the nozzle portion in a plate shape and having a plurality of admission holes formed therein so as to supply the working fluid to the nozzle portion to partially admit the working fluid into the nozzle portion, wherein each of the admission holes is formed to have a different passage cross-sectional areas, so that the opening and closing of the admission holes are controlled according to operating flow rate conditions to control a partial admission ratio of the working fluid supplied to the nozzle portion.
    Type: Grant
    Filed: November 1, 2017
    Date of Patent: June 8, 2021
    Assignee: KOREA INSTITUTE OF ENERGY RESEARCH
    Inventors: Hyung Ki Shin, Jun Hyun Cho, Young Jin Baik, Gil Bong Lee, Beom Joon Lee, Chui Woo Roh, Ho Sang Ra, Jong Jae Cho
  • Patent number: 11028524
    Abstract: A positive-negative-rotation fan for a clothes dryer comprises multiple whole-size fan blades arranged on a periphery of an outer frame of the fan, and multiple half-size fan blades arranged on the periphery of the outer frame of the fan. The half-size fan blades and the whole-size fan blades have similar shapes, and the size of an edge of each half-size fan blade parallel to a radial direction of the fan is half of the size of a corresponding edge of the whole-size fan blade. The clothes dryer using the positive-negative-rotation fan can provide an even and great air volume and a great air intake pressure in a clockwise and counterclockwise alternating rotation process, and accordingly clothes are evenly dried and the drying time is short. By using a flow guide device, aggregated back-flows are not generated between the fan and an outlet of a volute.
    Type: Grant
    Filed: September 11, 2017
    Date of Patent: June 8, 2021
    Assignee: QINGDAO HAIER WASHING MACHINE CO., LTD.
    Inventors: Jindong Bing, Rongfeng Cheng, Tao Li
  • Patent number: 11022144
    Abstract: A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.
    Type: Grant
    Filed: March 22, 2019
    Date of Patent: June 1, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Matthew Andrew Hough, John S. Tu, Stephen C. Harmon, Paul F. Croteau, Russell B. Hanson, Joshua C. Rathgeb
  • Patent number: 11021973
    Abstract: A platform suitable for being interposed between two adjacent blades of a fan, and including a passage wall, a bottom wall, and axial and radial retention surfaces. The passage wall defines a fan air flow passage, the bottom wall presents a main surface for bearing against a fan disk, and the axial and radial retention surfaces are arranged at the two axial ends of the platform. The radial retention surface arranged at the upstream axial end of the platform is radially offset from the main surface of the bottom wall in the direction in which the bottom wall bears against the disk.
    Type: Grant
    Filed: March 20, 2017
    Date of Patent: June 1, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Alexandre Bernard Marie Boisson
  • Patent number: 11015527
    Abstract: Aspects of the disclosure are directed to a rotatable shaft, and a plurality of bearings coupled to the rotatable shaft, where the plurality of bearings include a first bearing, a second bearing, and a third bearing, where the first bearing defines an axial first bearing centerline, where the second bearing defines an axial second bearing centerline, where the third bearing defines an axial third bearing centerline, and where the axial second bearing centerline is radially offset from the axial first bearing centerline and the axial third bearing centerline.
    Type: Grant
    Filed: November 22, 2017
    Date of Patent: May 25, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Kevin Duffy, Ronnie K. Kovacik, Keven G. Van Duyn, Jonathan F. Zimmitti, Richard J. Rubendall, Michael M. Davis, Joseph G. Colucci, Steven M. Danley, Christopher J. Zuck, Tina Rezvani
  • Patent number: 11001389
    Abstract: A propulsion engine for an aeronautical vehicle defines a radial direction and a cooling air flowpath. The propulsion engine includes a power source; and a fan including a fan blade rotatable by the power source and extending generally along the radial direction, the fan blade defining an inlet, an outlet, and a cooling air passage extending between the inlet and the outlet and in airflow communication with the cooling air flowpath, the inlet being positioned inward from the outlet along the radial direction to provide a cooling airflow through the cooling air flowpath.
    Type: Grant
    Filed: November 29, 2018
    Date of Patent: May 11, 2021
    Assignee: General Electric Company
    Inventor: Kevin Edward Hinderliter
  • Patent number: 10989226
    Abstract: A fan optimizing acoustic characteristics includes a yoke adapted to secure the fan to a building member and a central support structure extending from the yoke. The central support structure is an elongated member having a first end and a second end, the first end being selectively secured to the yoke and the second end extending downwardly therefrom. A fan assembly is secured to the second end of the central support structure. The fan also includes a plurality of sound absorbing elements.
    Type: Grant
    Filed: April 29, 2019
    Date of Patent: April 27, 2021
    Inventor: Dennis A Tracy
  • Patent number: 10989207
    Abstract: This new ceiling fan is designed to improve functionality of the airflow and to decrease the obtrusive appearance of the traditional axial ceiling fan by incorporating the lower profile airflow technology of a centrifugal fan. The main advantages are that it is much smaller with a lower profile that is mounted flat against the ceiling and can have more focused directional airflow thus enabling a user to feel more air circulation in the specific area of the room. The fan can also be set to oscillate around the room for more diffuse air circulation. Low profile lighting kits can be designed into the lower cover. This new design should be easily mountable on existing ceiling fan electrical boxes. Ideally it could be controlled with the same remote control technology available today for floor standing oscillating fans.
    Type: Grant
    Filed: May 18, 2018
    Date of Patent: April 27, 2021
    Inventor: Joseph Kraft
  • Patent number: 10989222
    Abstract: One exemplary embodiment of this disclosure relates to a refrigerant compressor. The compressor includes an axial section having a plurality of blades and vanes and a centrifugal section having an impeller. The centrifugal section is arranged downstream of the axial section.
    Type: Grant
    Filed: July 14, 2017
    Date of Patent: April 27, 2021
    Inventor: Justin Jongsik Oh
  • Patent number: 10982676
    Abstract: A coolant pump includes a conveying channel, a drive shaft, a coolant pump impeller arranged on the drive shaft, a control slide which controls a flow cross-section of an annular gap between an exit of the coolant pump impeller and the conveying channel, a side channel pump which includes a side channel pump impeller arranged on the drive shaft and a side channel having an inlet and an outlet where a pressure can be generated by the side channel pump impeller rotating, a pressure channel having a flow cross section which fluidically connects the outlet to a first pressure chamber of the control slide, a valve which closes the flow cross-section, a second pressure chamber arranged on a side of the control slide facing the coolant pump impeller, and a connection channel arranged from the side channel into the second pressure chamber between the inlet and the outlet.
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: April 20, 2021
    Assignee: PIERBURG GMBH
    Inventors: Stephan Zielberg, Michael-Thomas Benra, Stefan Rothgang, Andreas Burger, Helmut Prinz
  • Patent number: 10982561
    Abstract: An example integrated support and sensor includes a longitudinal member to support an inner duct relative to an outer duct, and a sensor received within a bore of the longitudinal member and configured to collect a measurement from a flow path bounded by the inner duct.
    Type: Grant
    Filed: October 13, 2014
    Date of Patent: April 20, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tuan David Vo, George E. Allen
  • Patent number: 10969015
    Abstract: An apparatus comprising a housing, seal, and energy storing device. The housing is coupled to a structure in an exhaust system of an aircraft. The structure is positioned relative to a surface within the exhaust system such that a gap is present between the surface and structure. The seal has an end positioned in contact with the surface to reduce a flow of exhaust through the gap and is coupled to the housing such that the seal extends within the housing. The energy storing device is coupled to the housing and engaged with the seal to allow the seal to translate in a first direction relative to the housing when the gap increases and in a second direction opposite the first direction relative to the housing when the gap decreases such that the seal continues to reduce the flow of exhaust through the gap as the gap changes in size.
    Type: Grant
    Filed: October 19, 2017
    Date of Patent: April 6, 2021
    Assignee: The Boeing Company
    Inventor: Nevin M. George
  • Patent number: 10961857
    Abstract: A turbine section for use in gas turbine engine includes a turbine case, a plurality of gas path components, a vane mount unit, and an inner vane static seal assembly. The turbine vane comprising ceramic matrix composite materials to insulate the metallic materials of the vane mount unit.
    Type: Grant
    Filed: December 21, 2018
    Date of Patent: March 30, 2021
    Inventors: Michael J. Whittle, Daniel K. Vetters
  • Patent number: 10961869
    Abstract: A gas turbine engine component includes a first flange with a plurality of first jack screw holes and a second flange attached to the first flange. The second flange includes a plurality of second jack screw holes that are concentric with the plurality of first jack screw holes.
    Type: Grant
    Filed: March 19, 2019
    Date of Patent: March 30, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Kaleb Von Berg
  • Patent number: 10954964
    Abstract: A gas turbine engine for an aircraft includes: a flow path boundary, which delimits the flow path through the engine radially on the outside, and a lining, which lines the flow path boundary on the inside, at least along an axial section. Here, the lining includes a plurality of panels, which, in the circumferential direction of the flow path boundary, adjoin each other and which together line a circumferential area of 360°, wherein each panel has two end faces, which each adjoin an end face of an adjacent panel. The panels are of beveled design at their end faces, such that two mutually adjoining panels form a V-shaped gap between them, the minimum clearance of which is realized at the inside of the panels. The panels can be sound-absorbing panels. Also disclosed is a panel for a gas turbine engine.
    Type: Grant
    Filed: January 23, 2019
    Date of Patent: March 23, 2021
    Assignees: Rolls-Royce Deutschland Ltd & Co KG, Rolls-Royce plc
    Inventors: Christoph Richter, Tom Hilton
  • Patent number: 10935042
    Abstract: A ceiling fan blade mounting structure includes a blade holding base and a fastening assembly. The blade holding base includes a plurality of connection members spaced apart from each other. The fastening assembly includes a wedging member, a rotating block, and a fastening member. The wedging member is fastened with one of the plurality of connection members. A first end of the rotating block is rotatably connected to the wedging member. A first end of the fastening member is rotatably connected to a second end of the rotating block. The fastening member is configured to rotate about the rotating block to cause a second end of the fastening member to be fastened with another one of the plurality of connection members.
    Type: Grant
    Filed: March 24, 2017
    Date of Patent: March 2, 2021
    Assignees: GD MIDEA ENVIRONMENT APPLIANCES MFG CO., LTD., MIDEA GROUP CO., LTD.
    Inventors: Yuqiang Guo, Xinmin Tang, Ying Tong
  • Patent number: 10933992
    Abstract: A rotor system of a tail-sitter aerial vehicle configured to rotate about an axis of rotation is provided including a rotor hub which rotates about the axis of rotation and at least one rotor blade operably coupled to the rotor hub. The at least one rotor blade is configured to rotate about a folding axis between an extended position where the at least one rotor blade is substantially within a plane perpendicular to the axis of rotation and a stowed position where the rotor blade is arranged out of the plane of at an angle less than ninety degrees to the axis of rotation.
    Type: Grant
    Filed: October 27, 2016
    Date of Patent: March 2, 2021
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Bryan Kenneth Baskin, Frank P. D'Anna, Mark R. Alber
  • Patent number: 10934884
    Abstract: An assembly (50) for a turbine engine includes an annular row of stator blades with a longitudinal axis (B) having variable pitch blades each comprising a radial vane (6), at least one of its ends of which is connected to a radially extending pivot (14) and being engaged in rotation around its axis (A) in a ring (16), characterised in that a tubular component (26) is mounted coaxially around the pivot (14), wherein said tubular component (26) comprises a first annular zone (26a) mounted tightly on the pivot (14) and a second annular zone (26b) comprising an annular bulge (28) extending substantially radially outwards in relation to the axis (A) of the pivot (14), wherein the annular bulge (28) and the pivot (14) define an annular space (30).
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: March 2, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Rémi Philippe Guy Onfray, Benoit André Pierre Frossard, Clément Miraton
  • Patent number: 10934844
    Abstract: A gas turbine engine comprises an engine core, a tie bolt, and a fail-safe system. The engine core includes a compressor, a turbine, and a shaft that couples the compressor with the turbine for rotation with the turbine about an axis. The tie bolt locates axially the compressor relative to the turbine. The fail-safe system is configured to transmit torque from the turbine to the compressor through the tie bolt in response to a shaft disconnect event.
    Type: Grant
    Filed: May 31, 2018
    Date of Patent: March 2, 2021
    Assignee: Rolls-Royce Corporation
    Inventors: Chadd D. Engel, Bradford J. Riehle
  • Patent number: 10934871
    Abstract: A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track. The ceramic-matrix composite blade track includes a plurality of track segments located circumferentially adjacent to one another to form a track ring. Features of the track segments provide tortuous paths for gasses trying to pass through the ceramic-matrix composite blade track that may reduce leakage through the blade track.
    Type: Grant
    Filed: February 22, 2016
    Date of Patent: March 2, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Peter Broadhead, Aaron D. Sippel, David J. Thomas, Joseph P. Lamusga