Patents Examined by Richard A Edgar
  • Patent number: 9890663
    Abstract: A turbine exhaust case (28) comprises a fairing (120) defining an airflow path through the turbine exhaust case, and a multi-piece frame (100) disposed through and around the fairing to support a bearing load. The multi-piece frame comprises an inner ring (104), an outer ring (102), and a plurality of strut bosses (106). The outer ring is disposed concentrically outward of the inner ring, and has open bosses (126) at strut locations. The plurality of radial struts pass through the vane fairing, are secured to the inner ring via radial fasteners (108), and are secured via non-radial fasteners (114) to the open boss.
    Type: Grant
    Filed: December 20, 2013
    Date of Patent: February 13, 2018
    Assignee: United Technologies Corporation
    Inventor: Jonathan Ariel Scott
  • Patent number: 9890700
    Abstract: Various systems and methods are described for a variable geometry turbine. In one example, a nozzle vane includes a stationary having a first cambered sliding surface and a sliding vane having a second cambered sliding surface where the second cambered sliding surface includes a flow disrupting feature in contact with the first sliding cambered surface. The sliding vane may be positioned to slide in a direction from substantially tangent along a curved path to an inner circumference of the turbine nozzle and selectively uncover the flow disrupting feature.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: February 13, 2018
    Assignee: Ford Global Technologies, LLC
    Inventors: Harold Huimin Sun, Ben Zhao, Leon Hu, Jianwen James Yi, Eric Warren Curtis, Jizhong Zhang
  • Patent number: 9885247
    Abstract: A support assembly for a gas turbine engine includes an outer support that extends about a circumferential axis and includes at least one engagement member. An inner support forms a cavity. A control ring is located within the cavity and includes at least one tab for engaging at least one engagement member on the outer support.
    Type: Grant
    Filed: May 19, 2015
    Date of Patent: February 6, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Andrew S. Miller, Peter Balawajder
  • Patent number: 9879637
    Abstract: A system and method is provided that combines fan bypass components and minimizes assembly interfaces in a turbofan engine. The system and method provide a front frame structure of reduced weight that slidably installs/removes from within the combined fan bypass components.
    Type: Grant
    Filed: December 4, 2014
    Date of Patent: January 30, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Mark Knowles, Shawn Alstad, Justin C. Mickelsen, Raymond Gage, Bill Russell Watson
  • Patent number: 9878783
    Abstract: According to one embodiment, a constant velocity (CV) joint includes a first yoke, a second yoke, and three bearings. The first yoke is configured to be rotatably coupled to an input device about a first axis and configured to receive the input device through a first opening. The second yoke is rotatably coupled to the first yoke about a second axis and rotatably coupled to an output device about a third axis. The first bearing is disposed about the first axis adjacent to the first yoke, the second bearing is disposed about the second axis adjacent to the first yoke or the second yoke, and the third bearing disposed about the third axis adjacent to the second yoke. The first and third bearings torsionally constrain movement the first yoke and the second yoke so as to achieve a substantially CV characteristic between the input device and the output device.
    Type: Grant
    Filed: April 22, 2014
    Date of Patent: January 30, 2018
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Drew Sutton, Frank B. Stamps, Christopher Foskey
  • Patent number: 9879651
    Abstract: A vane device is adapted for use in a turbine apparatus, and includes a rotary shaft and a plurality of angularly spaced-apart vane units. The rotary shaft is rotatable in a rotational direction. The vane units are connected to the rotary shaft. Each of the vane units includes a grid frame and a plurality of spaced-apart cup members. The grid frame is connected to the rotary shaft. The cup members are arranged in an array and are connected to the grid frame. Each of the cup members has an inner surface that defines a receiving space, and an outer surface that is opposite to the inner surface and that faces toward the rotational direction.
    Type: Grant
    Filed: June 30, 2015
    Date of Patent: January 30, 2018
    Inventor: Kuo-Chang Huang
  • Patent number: 9878782
    Abstract: A rotor assembly for a rotary-wing aircraft, the rotor having a central hub assembly with a flexure-type, twist-shank yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto. The arms provide for pitch changes of blades attached to the yoke through twisting of portions of the arms about a corresponding pitch axis. An inboard pitch bearing associated with each arm is attached to the hub assembly and allows for rotation of the attached blade about the pitch axis, the inboard pitch bearing also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis. An outboard pitch bearing associated with each arm is attached to the associated arm a selected distance from the inboard pitch bearing and allows for rotation of the attached blade about the pitch axis.
    Type: Grant
    Filed: February 17, 2015
    Date of Patent: January 30, 2018
    Assignee: Textron Innovations Inc.
    Inventors: Frank B. Stamps, Patrick R. Tisdale, Tom Donovan, Richard E. Rauber
  • Patent number: 9874102
    Abstract: A cooling system (10) positioned within a turbine airfoil (12) and having film cooling channels (16) positioned within inner and outer endwalls (18, 20) of the turbine airfoil (12), with cooling fluids supplied to the cooling channels (16) other than from an aft cooling chamber (22) to prevent blockages from developing within the film cooling channels (16) from debris that typically collects with the aft cooling chamber (22) during steady state operation of the turbine engine is disclosed. The cooling system (10) may include one or more midchord cooling channels (24) extending from a midchord cooling chamber (26) and including an outlet (28) positioned closer to a downstream edge (30) of the inner endwall (18) than an upstream wall (32) forming the aft cooling chamber (22).
    Type: Grant
    Filed: September 8, 2014
    Date of Patent: January 23, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Gm Salam Azad, Ching-Pang Lee, Alan A. Thrift, Daniel Joo, Johan K. Westin, Caleb Myers
  • Patent number: 9874104
    Abstract: A shroud and hanger assembly for a gas turbine engine and a method of transferring load from a ceramic matrix composite (CMC) shroud to a CMC shroud hanger assembly are provided. The shroud and hanger assembly includes a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, the shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion and a shroud formed of a second material having a second coefficient of thermal expansion, the forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of the shroud.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: January 23, 2018
    Assignee: General Electric Company
    Inventor: Jason David Shapiro
  • Patent number: 9861853
    Abstract: A turbine damping device is mounted on a fitness device, and has a housing assembly, a turbine assembly, and a regulating unit. The turbine assembly is mounted inside the housing assembly and has a turbo casing, a turbo wheel, and an adjusting plate. The turbo casing has an exhaling hole. The adjusting plate is controlled by the regulating unit and mounted movably in the exhaling hole. The turbo wheel is mounted rotatably inside the turbo casing. The turbo casing and the turbo wheel generate an airflow resistance that is an exercising load for users using the fitness device. The adjusting plate regulates an opening size of the exhaling hole to adjust the airflow resistance. The turbine damping device has a simple structure and maintenance thereof is easy. A user adjusts the exercising load easily by controlling the adjusting plate. The fitness device with airflow resistance is helpful to environmental protections.
    Type: Grant
    Filed: September 13, 2015
    Date of Patent: January 9, 2018
    Assignee: ZHONGSHAN SHENGDONGLI CO., LTD.
    Inventor: Yongjun Chen
  • Patent number: 9863436
    Abstract: A pump housing has a spiral housing and includes a suction channel (14) which runs out in a space (15). The space (15) is for arranging an impeller (6), rotatable about a rotation axis (5), and includes a spirally peripheral channel (16) open to the space (15) and running out into a pressure channel. A receiver (20) for a differential pressure sensor is provided within the pump housing. A first sensor channel (22) is provided, which connects the receiver (20) to a pressure-side interior of the pump housing. A second sensor channel (23) connects the receiver (20) to the pressure-side interior of the pump housing. The receiver (20) for the differential pressure sensor is arranged between the spirally peripheral channel (16) and the suction channel (14), so that the channels can be formed by way of simple bores.
    Type: Grant
    Filed: January 17, 2013
    Date of Patent: January 9, 2018
    Assignee: GRUNDFOS HOLDING A/S
    Inventors: Casper Pedersen, Nicholas Pedersen
  • Patent number: 9856888
    Abstract: A system and method are disclosed to attach a blade section (2) of a fan blade (1), in particular of a smoke extractor fan, to a fan hub, as well as a fan blade (1), which provides a high tensile strength even at high temperatures. The attaching part and fan blades (1) are to be produced so as to save as much weight as possible. The attaching part has a connecting section (5) embodied to produce a high-tensile connection to a blade section (2) of a fan blade (1). The connecting section can be arranged essentially in the interior of the blade section (2).
    Type: Grant
    Filed: September 9, 2014
    Date of Patent: January 2, 2018
    Assignee: W & S Management GmbH & Co. KG
    Inventor: Henrik Witt
  • Patent number: 9845787
    Abstract: Wind turbine systems and methods are disclosed herein. A representative system includes a wind turbine blade having an inner region that has an internal load-bearing truss structure, and an outer region that has an internal, non-truss, load-bearing structure. In particular embodiments, the truss structure can include a triangular arrangement of spars, and/or can include truss attachment members that connect components of the truss without the use of holes in the spars. Spars can be produced from a plurality of pultruded composite members laminated together in longitudinally extending portions. The longitudinally extending portions can be connected at joints that interleave projections and recesses of each of the spar portions. The blades can include fan-shaped transitions at a hub attachment portion, formed by laminated layers and/or a combination of laminated layers and transition plates.
    Type: Grant
    Filed: March 23, 2015
    Date of Patent: December 19, 2017
    Assignee: Vestas Wind Systems A/S
    Inventors: Myles L. Baker, Cory P. Arendt, Bernard G. Madrid, Sheldon Vilhauer
  • Patent number: 9828879
    Abstract: A shroud retention system may include a shroud hanger having an outer hanger wall that defines a clip groove including a narrow groove portion and an enlarged groove portion, with the enlarged groove portion defining a radial height that is greater than a radial height of the narrow groove portion. The system may also include a shroud segment having a shroud wall and a retention clip configured to couple the shroud segment to the shroud hanger. The retention clip may include an inner rail, an outer rail and a clip wall extending radially between the inner and outer rails. The inner rail may be configured to extend along an inner surface of the shroud wall. The outer rail may include a narrow rail portion configured to be received within the narrow groove portion and an enlarged rail portion configured to be received within the enlarged groove portion.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: November 28, 2017
    Assignee: General Electric Company
    Inventors: Gregory Kent Sluyter, Alexander Martin Sener, Aaron Michael Dziech
  • Patent number: 9822768
    Abstract: The invention relates to a wind turbine comprising a rotor hub (7) rotating about a rotor axis (8), rotor blades (9, 10, 11) extending radially with respect to the rotor axis (8) at the same angular spacing relative to one another, and a remote wind gauge (19) that is fastened externally on the surface of the hub (7) in a mounting (20) and oriented such that wind characteristics at a distance in front of the hub (7) can be ascertained or measured, wherein the remote wind gauge (19) is arranged between two neighbouring rotor blades (9, 10) and in the radial direction of the rotor axis (8) and the mounting (20) is fastened to a respective blade bearing flange (21, 22) in the region of the connection of the rotor hub (7) to the rotor blades (9, 10), such that the remote wind gauge (19) can be retrofitted to the wind turbine (1).
    Type: Grant
    Filed: December 12, 2012
    Date of Patent: November 21, 2017
    Assignee: SSB Wind Systems GmbH & Co. KG
    Inventor: Norbert K├Âtting
  • Patent number: 9822706
    Abstract: The present invention relates to a subassembly for a gas turbine, in particular a gas turbine aircraft engine, having a turbine casing (11); a midframe (14), which is adjacent downstream to the turbine casing and has a number of support ribs (15) spaced apart in the peripheral direction. The turbine casing and the midframe define a flow duct (33) for a working gas exiting a combustion chamber of the gas turbine, and a cavity, in particular a cooling air duct (19), with an opening on the flow duct side is formed between the turbine casing and the midframe. An edge contour (40) of the opening on the turbine casing side varies along the periphery radially and/or axially.
    Type: Grant
    Filed: August 18, 2015
    Date of Patent: November 21, 2017
    Assignee: MTU AERO ENGINES AG
    Inventor: Martin Hoeger
  • Patent number: 9822663
    Abstract: The present invention relates to a fire resistant fan casing for a gas turbine engine. The casing has a projection such as a reinforcing rib or a mounting pad. The projection comprises at least one shell portion formed of a fiber/plastic composite material encasing a core of fire resistant material such as a metallic material or a ceramic matrix composite material.
    Type: Grant
    Filed: January 14, 2015
    Date of Patent: November 21, 2017
    Assignee: ROLLS-ROYCE plc
    Inventor: Dale Edward Evans
  • Patent number: 9816396
    Abstract: A system and method is provided for an integrated aircraft turbofan engine outer flowpath ducting and front frame that minimizes assembly interfaces and reduces overall aircraft engine weight. The system and method provide an integrated turbofan engine outer flowpath ducting and front frame system that decouples the fairing/aerodynamic duties from the struts/weight bearing duties thereby enabling efficient distribution of mechanical load.
    Type: Grant
    Filed: October 16, 2014
    Date of Patent: November 14, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Justin C. Mickelsen, Laurence David Noble Liston, Mark Knowles, Shawn Alstad
  • Patent number: 9810073
    Abstract: A turbine blade includes a cooling channel through which cooling air is passed, and a swirl portion provided at an entrance of the cooling channel so as to form a swirl flow in the cooling air. The turbine blade may increase cooling performance of a root unit, improve the stiffness of the root unit, and increase the internal heat transfer efficiency of a blade unit.
    Type: Grant
    Filed: December 15, 2014
    Date of Patent: November 7, 2017
    Assignee: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION Co., LTD
    Inventor: Sung Chul Jung
  • Patent number: 9810231
    Abstract: A turbocharger assembly can include a housing with a through bore and an axial face disposed in the through bore; a locating plate with a keyed opening attached to the housing; and a journal bearing disposed in the through bore where the journal bearing includes a keyed compressor end and an enlarged outer portion defined between two axial faces by an outer diameter and an axial length where the axial face disposed in the through bore of the housing, the locating plate, and the two axial faces of the journal bearing axially locate the journal bearing in the through bore and where the keyed opening of the locating plate and the keyed compressor end of the journal bearing azimuthally locate the journal bearing in the through bore. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.
    Type: Grant
    Filed: May 13, 2013
    Date of Patent: November 7, 2017
    Assignee: Honeywell International Inc.
    Inventors: Frederic Daguin, Joel Castan, Nicolas Vazeille, Dominique Armand, Steven Liu, Yong Jun Chen, Shinichi Adachi