Patents Examined by Andrew J Marien
  • Patent number: 11111001
    Abstract: The invention to which this application relates is to a propeller of the type for use in relation to water vessels and which can be moved between an in-use position in which the blades of the propeller extend outwardly to provide a propulsion force when rotated and, a storage position in which the desire is to minimize the effect of the blades as the vessel moves through the water and in which the blades are held substantially in line with the body of the propeller. The location means which allow the blades to be connected to the body are located within the body and thereby minimize the risk of corrosion and thereby increase the life of the propeller whilst also providing a secure fitment of the blades to the body and allowing ease of movement of the blades between in-use and storage positions.
    Type: Grant
    Filed: January 23, 2020
    Date of Patent: September 7, 2021
    Assignee: SUPERPROP LIMITED
    Inventor: Christopher Shaw
  • Patent number: 11073163
    Abstract: A centrifugal compressor includes impellers arranged in a plurality of stages in a direction of an axis line so that a working fluid flowing from one side inlet in the direction of the axis line is pumped outward in a radial direction, and a casing that surrounds the impellers, and that has a return channel through which the working fluid discharged from the impeller on a front stage side between the impellers adjacent to each other is guided inward in the radial direction so as to be introduced to the impeller on a rear stage side, and a plurality of return vanes disposed at an interval in a circumferential direction inside the return channel. The return vane is configured so that the thickness of a hub side in a leading edge side region is thicker than the thickness of a shroud side.
    Type: Grant
    Filed: March 27, 2018
    Date of Patent: July 27, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Ryosuke Saito
  • Patent number: 11047396
    Abstract: A bearing packing according to the invention includes a first packing having an opening portion formed therein, the opening portion allowing a rotary shaft to penetrate through the first packing, and a second packing having an opening portion formed therein, the opening portion allowing the rotary shaft to penetrate through the second packing, and configured to be brought into engagement with the first packing in a direction of the rotary shaft, and a sealed space for sealing a hydrophobic fluid in is defined around a circumference of the rotary shaft that is surrounded by the first packing and the second packing.
    Type: Grant
    Filed: June 5, 2019
    Date of Patent: June 29, 2021
    Assignee: AGATSUMA CO., LTD.
    Inventor: Shinji Todokoro
  • Patent number: 11035339
    Abstract: A method for assembling a shear web assembly of a wind turbine includes providing at least one spar cap. The method also includes forming a spar connecting member of a thermoplastic material via additive manufacturing. Further, the method includes securing the spar connecting member to the spar cap. Moreover, the method includes providing a shear web, forming a web connecting member of a thermoplastic material via additive manufacturing, and securing the web connecting member at a first end of the shear web. In addition, the method includes interconnecting the web connecting member and the spar connecting member at a joint. Thus, the method further includes heating the joint to secure the web connecting member and the spar connecting member together.
    Type: Grant
    Filed: March 26, 2018
    Date of Patent: June 15, 2021
    Assignee: General Electric Company
    Inventors: David Roberts, Nicholas K. Althoff, Michael Wenani Nielsen, James Robert Tobin
  • Patent number: 11021991
    Abstract: A measurement system for determining an angular position of a component of a gas turbine engine includes one or more proximity sensors positioned at a fixed structure of the gas turbine engine and one or more sensor targets positioned at a rotatable component of the gas turbine engine. Each sensor target of the one or more sensor targets includes a target surface having a variable distance between the target surface and the proximity sensor with rotation of the rotatable component about a component axis of rotation. A measurement of distance between the proximity sensor and the target surface as measured by the proximity sensor is indicative of an angular position of the rotatable component relative to the component axis of rotation.
    Type: Grant
    Filed: May 31, 2019
    Date of Patent: June 1, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel J. Boudreau, Eli Cole Warren, Bryan J. Hackett
  • Patent number: 11022003
    Abstract: A steam turbine exhaust chamber defining therein an exhaust passage through which steam having passed through a last-stage blade of a steam turbine is introduced to a condenser includes: a casing including an outer peripheral wall portion formed on an outer peripheral side of the exhaust passage; a bearing cone disposed on a radially inner side of the outer peripheral wall portion; and at least one bypass passage carrying a part of steam flowing through the exhaust passage from a high-pressure portion of the exhaust passage to a low-pressure portion of the exhaust passage or to the condenser, The at least one bypass passage includes a high-pressure-side opening formed in the bearing cone and a low-pressure-side opening facing steam having a lower pressure than steam facing the high-pressure-side opening.
    Type: Grant
    Filed: February 12, 2019
    Date of Patent: June 1, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Toyoharu Nishikawa, Hideaki Sugishita, Kazuyuki Matsumoto, Yoshihiro Kuwamura, Kei Nakanishi
  • Patent number: 11021232
    Abstract: An unmanned aerial vehicle includes a propulsion system including a driving device having a main body, a driving shaft rotatable relative to the main body, and a locking member disposed on the main body. The locking member includes at least one snap-fitting member. The propulsion system also includes a propeller coupled with the driving device, the propeller including a blade base and a blade mounted on the blade base. The at least one snap-fitting member is configured to snap-fit with the propeller. The propulsion system also includes an elastic abutting member sleeve coupled with the driving shaft, a first installation foolproof member disposed on the blade base, and a second installation foolproof member disposed on the locking member.
    Type: Grant
    Filed: February 28, 2019
    Date of Patent: June 1, 2021
    Assignee: SZ DJI TECHNOLOGY CO., LTD.
    Inventors: Tao Deng, Ruochen Tang, Yueyao Tu
  • Patent number: 11008879
    Abstract: A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
    Type: Grant
    Filed: January 18, 2019
    Date of Patent: May 18, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: William S. Pratt, Matthew E. Bintz, Steven D. Roberts, Adam Hart
  • Patent number: 10975706
    Abstract: A stator vane may comprise an airfoil extending between a first platform and a second platform, the airfoil including a core extending relatively orthogonal to the first platform and the second platform, at least one of the first platform or second platform comprising a frustic load transmission feature, wherein the frustic load transmission feature comprises at least a first angular surface disposed proximate a platform edge, wherein the first angular surface is defined by a non-orthogonal angle ? with respect to an outer platform surface.
    Type: Grant
    Filed: January 17, 2019
    Date of Patent: April 13, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Bryan H. Farrar, Andrew J. Lazur, Howard J. Liles, Bryan P. Dube
  • Patent number: 10962021
    Abstract: A centrifugal impeller is disclosed having a non-axisymmetric flowpath surface. The centrifugal compressor may comprise a hub and a plurality of circumferentially spaced vanes. The hub has a flowpath surface and an axis of rotation. The plurality of circumferentially spaced vanes extend from the flowpath surface, with each of the vanes having a pressure-side fillet and a suction-side fillet extending from a leading edge to a trailing edge of the vane. The pressure-side fillet and suction-side fillet intersect the flowpath surface at a runout. The runout of the pressure-side fillet of a first vane is asymmetric to the runout of the suction-side fillet of the first vane.
    Type: Grant
    Filed: August 17, 2018
    Date of Patent: March 30, 2021
    Assignee: Rolls-Royce Corporation
    Inventor: Steven Mazur
  • Patent number: 10954916
    Abstract: The invention relates to a wind turbine blade having integrated thermoplastic anchoring sites for attachment of surface mounted devices, a method for producing such blade and a wind turbine equipped with such blade.
    Type: Grant
    Filed: July 17, 2015
    Date of Patent: March 23, 2021
    Assignee: LM WP PATENT HOLDING A/S
    Inventor: Michael Drachmann Haag
  • Patent number: 10941780
    Abstract: A slurry seal assembly for use about a rotatable shaft between a process side and an atmosphere side is presented. The slurry seal assembly includes a sleeve, a rotatable seal ring, a stationary seal ring, a floating bushing seal assembly, and a plurality of slots. The sleeve is disposed about and rotatable with the shaft. The rotatable seal ring contacts and is rotatable with the sleeve. The stationary seal ring is arranged to form a sealing interface with the rotatable seal ring. The floating bushing seal assembly is disposed about the sleeve so that an inner annular surface along the floating bushing seal assembly is separated from an outer annular surface along the sleeve by a gap. The slots are disposed along the sleeve within the process side adjacent to the floating bushing seal assembly. The slurry seal assembly is applicable to devices whereby a fluid is movable between an inlet and an outlet.
    Type: Grant
    Filed: May 4, 2020
    Date of Patent: March 9, 2021
    Assignee: Stein Seal Company
    Inventor: Thurai Manik Vasagar
  • Fan
    Patent number: 10935034
    Abstract: A fan is disclosed. The fan includes a base mountable to a ceiling; a base motor contained in the base; a multi-section shaft operably connected to the base motor and moveable between a collapsed position and an extended position; and a fan assembly connected to the multi-section shaft and including a fan motor and at least one fan blade operably connected to the fan motor, wherein in response to a signal, the base motor raises or lowers the fan assembly by moving the multi-section shaft between the collapsed position and the extended position.
    Type: Grant
    Filed: January 2, 2019
    Date of Patent: March 2, 2021
    Assignee: PHANSEE COMPANY, LLC
    Inventors: Philip Emanuel Noble, Christopher Patrick Noble
  • Patent number: 10927708
    Abstract: A hybrid propulsion system and methods for cooling the same are provided. The system may comprise a gas turbine and a secondary engine. The gas turbine engine may have a core passage and an engine compartment. The secondary engine may be a supersonic and/or hypersonic engine. The system may comprise a thermal barrier, an inlet and an exhaust. The thermal barrier may longitudinally envelope the gas turbine engine. The thermal barrier may comprise an inner envelope, an outer envelope, an upstream opening, and a downstream opening. The inlet may be in fluid communication with the ambient environment and the gas turbine engine via the upstream opening. The exhaust may be in fluid communication with the ambient environment and the gas turbine engine via the downstream opening. The engine compartment may be located between a boundary of the core passage and the inner envelope.
    Type: Grant
    Filed: October 29, 2018
    Date of Patent: February 23, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Nicholas Dwain Metzger
  • Patent number: 10927698
    Abstract: A turbocharger includes a variable-nozzle cartridge having a nozzle ring that supports an array of variable vanes in the turbine nozzle. A heat shroud and spring assembly is disposed in a space bounded between the turbine wheel, the nozzle ring, and the center bearing housing of the turbocharger. The heat shroud and spring assembly includes discretely formed heat shroud and spring components configured as annular non-planar disk-shaped parts. The heat shroud and spring are in contact with each other at their radially inner and radially outer peripheral regions, but are spaced apart between those peripheral regions, thereby creating a sealed-off dead space between them. The dead space can significantly reduce the maximum temperature of the spring, relative to arrangements having a single shroud or having dual shrouds with no dead space between them.
    Type: Grant
    Filed: January 10, 2019
    Date of Patent: February 23, 2021
    Assignee: Garrett Transportation I Inc.
    Inventors: Vit Micanek, Miroslav Protiva, Lucie Kovarova
  • Patent number: 10907492
    Abstract: A gas turbine engine includes a turbine blade rotating about an axis of rotation defining an axial direction. A blade outer air seal is positioned radially outward of a radially outer tip of the turbine blade. The blade outer air seal has a forward support and an aft support. The forward support is supported on a forward hook from a blade outer air seal support. The aft support is supported on an aft hook from the blade outer air seal support. The blade outer air seal has a central web extending between the forward support and the aft support and radially outwardly of the turbine blade radially outer tip. A radially outer chamber is defined radially outwardly of the central web, and axially intermediate the forward support and the aft support. The radially outer chamber is divided into at least two separate subchambers maintained at two different pressures. A forward subchamber is at a higher pressure than an aft subchamber. A seal separator separates the forward and aft subchambers.
    Type: Grant
    Filed: September 7, 2018
    Date of Patent: February 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Thomas E. Clark, William M. Barker
  • Patent number: 10895164
    Abstract: A method for reducing the leakage of an organic working fluid operating within a turbine (10) of an Organic Rankine Cycle system, the method comprising the injection of a fluid flow rate (Q) into a volume (I) at a static pressure lower than the total pressure (P1) upstream of the turbine and located near of at least one labyrinth seal (L1, L11) of at least one stage of the turbine (10), said fluid flow rate (Q) having an initial exergetic content lower than the initial exergetic content of the organic working fluid located inside the turbine and flowing through said labyrinth seal (L1, L11).
    Type: Grant
    Filed: January 18, 2017
    Date of Patent: January 19, 2021
    Assignee: TURBODEN S.P.A.
    Inventors: Mario Gaia, Roberto Bini
  • Patent number: 10895162
    Abstract: The invention relates to a guide vane segment for an aircraft engine, having at least one guide vane element, having at least one flange formed in a radial extension direction (R) of the guide vane element and at least one positioning member projecting from the flange in the radial extension direction (R), and at least one seal carrier, which is arranged at the flange and is aligned relative to the guide vane element by way of the positioning member, wherein the flange has a supporting surface on which the seal carrier is supported, wherein a partial surface of the positioning member is adjacent to the flange at a transition from the flange to the positioning member, and respective surface normal lines of the supporting surface and of the partial surface enclose between them an angle (?) that is different from a zero angle.
    Type: Grant
    Filed: February 9, 2017
    Date of Patent: January 19, 2021
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Manfred Feldmann, Rudolf Stanka, Oliver Thiele
  • Patent number: 10876535
    Abstract: A compressor includes a thrust force adjusting part which is configured to adjusts a thrust force between a back surface of a disc part in an impeller and a casing. The thrust force adjusting part includes an outer sealing part which seals a gap between the back surface and the casing, an inner sealing part which seals the gap at a position away inward in a radial direction, and a throttle formation part which has a throttle part in which the gap in an axial direction is formed to be narrowed inward in the radial direction. An outer space sandwiched by the outer sealing part and the inner sealing part and an inner space sandwiched by the inner sealing part and the throttle part are formed the gap. The width of the throttle part is narrower than the width of the inner space.
    Type: Grant
    Filed: September 5, 2018
    Date of Patent: December 29, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventor: Hideki Nagao
  • Patent number: 10858950
    Abstract: An example high-performance system includes an example high-performance component including a substrate and a multilayer abradable track adjacent to the substrate. The abradable track includes a plurality of alternating layers along a thickness of the abradable track. The plurality of alternating layers includes at least one relatively porous abradable layer and at least one relatively dense layer. A porosity of the relatively dense layer is lower than that of the at least one relatively porous abradable layer. The example high-performance system may include a rotating component configured to contact and abrade the multilayer abradable track. An example technique for forming the multilayer abradable track includes thermal spraying a first precursor composition toward the substrate to form a relatively porous abradable layer of a layer pair of a plurality of layer pairs of the multilayer abradable track, and a second precursor composition to form a relatively dense layer of the pair.
    Type: Grant
    Filed: July 24, 2018
    Date of Patent: December 8, 2020
    Assignees: Rolls-Royce North America Technologies, Inc., Rolls-Royce Corporation
    Inventors: Jun Shi, Li Li, Ted J. Freeman