Working Fluid Passage Or Distributing Means Associated With Runner (e.g., Casing, Etc.) Patents (Class 415/182.1)
  • Patent number: 10767553
    Abstract: A turbocharger includes a waste gate valve, a compressor, a turbine, a turbine housing which houses the turbine, a bypass channel which includes an opening cross-section, the bypass channel bypassing the turbine, a bypass channel portion formed in the turbine housing, an actuator housing which includes a separate first coolant channel having a coolant inlet port and a coolant outlet port, an electric motor arranged in the actuator housing, a transmission which includes an output shaft, the transmission being arranged in the actuator housing, and a control body coupled to the output shaft. The actuator housing is formed separately and is secured to the turbine housing. The control body controls the opening cross-section of the bypass channel.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: September 8, 2020
    Assignee: PIERBURG GMBH
    Inventors: Martin Nowak, Michael-Thomas Benra, Axel Hemsing, Andreas Koester
  • Patent number: 10767512
    Abstract: The invention relates to a particle-trapping device (2) for a turbomachine, said particles being contained in an air stream flowing inside a turbomachine, in particular the air stream flowing in the bypass region (17) of the combustion chamber (13) of said turbomachine. The device is characterized in that it comprises: —at least two particle deflectors (3, 3a, 3b, 3c), —a member (5) for collecting and storing the particles deflected by said deflector, —and means (6) for attaching said trapping device (2) to a part of the turbomachine.
    Type: Grant
    Filed: September 8, 2016
    Date of Patent: September 8, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Amaury Paillard, Stephane Pascaud
  • Patent number: 10724537
    Abstract: The present disclosure relates to a blade structure and a fan and a generator having the same. In accordance with the present disclosure, there is the effect that can ultimately enhance efficiency of the generator by forming the sweep structure or the spline structure on the blade in the inflow direction side of fluid to reduce a low-speed region around the tip of the blade.
    Type: Grant
    Filed: May 16, 2018
    Date of Patent: July 28, 2020
    Assignee: Doosan Heavy Industries & Construction Co. LTD.
    Inventors: Dai Hyun Ahn, Sung Ha Kim, Sung Hoon Ha
  • Patent number: 10711614
    Abstract: A boundary layer ingestion engine comprising a fan, the fan comprising a disc and a plurality of blades integrally formed with the disc.
    Type: Grant
    Filed: March 23, 2018
    Date of Patent: July 14, 2020
    Assignee: Rolls-Royce PLC
    Inventor: Gabriel Gonzalez-Gutierrerz
  • Patent number: 10619597
    Abstract: A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.
    Type: Grant
    Filed: February 9, 2018
    Date of Patent: April 14, 2020
    Assignee: ROHR, INC.
    Inventors: Sara Christine Crawford, Michael Aten, Anthony Lacko
  • Patent number: 10589868
    Abstract: Systems and methods are provided for an aircraft propulsor with a fan cowl with one or more tangential restraints. The tangential restraints may be configured to contact one or more tangential receiving portions of a fixed portion of the aircraft propulsor. The fan cowl may receive a load that may include a bending load. The tangential restraints may be configured to convert the bending load to membrane tension and thus decrease deflection of the fan cowl.
    Type: Grant
    Filed: September 28, 2016
    Date of Patent: March 17, 2020
    Assignee: The Boeing Company
    Inventor: Jason F. Joel
  • Patent number: 10508651
    Abstract: An automatic inflation device includes a valve body, a miniature motor and a centrifugal impeller. The valve body is provided with an air inlet and an inflation inlet, a check valve that is unidirectionally opened outwards the valve body is provided at the inflation inlet, a wind chamber and a wind guide path connected with the wind chamber are configured in the valve body, the miniature motor and the centrifugal impeller are installed in the wind chamber, the centrifugal impeller is actuated by the miniature motor, the wind chamber is communicated with the inflation inlet via the wind guide path, and the air inlet is communicated with a wind inlet of the wind chamber. The structure of the device is compact and reduced, which is applicable to directly install into inflation products. The device can inflate automatically and efficiently, and the structure is simplified and easy to actualize.
    Type: Grant
    Filed: March 17, 2017
    Date of Patent: December 17, 2019
    Assignee: Guangdong Travelmall Health Technology Co., Ltd.
    Inventor: Zhiming Liu
  • Patent number: 10502134
    Abstract: The invention relates to an aircraft turbofan type engine (1) comprising an air intake duct (2) having an inner face provided with an acoustic attenuation shroud (11) located upstream from a fan (3) of this engine (1). This acoustic attenuation shroud (11) comprises a regular alternation of first portions and second portions with different first and second thicknesses along the radial direction, the number of alternations being greater than twice the number of passing azimuth acoustic vibration modes occurring in the engine (1) without the acoustic attenuation shroud (11) operating under conditions corresponding to a landing phase and a take-off phase.
    Type: Grant
    Filed: November 23, 2015
    Date of Patent: December 10, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Laurent Louis Robert Baudoin, Georges Jean Xavier Riou
  • Patent number: 10473113
    Abstract: A centrifugal blower includes a rotation shaft, an impeller, a casing. The impeller includes a plurality of blades and a side panel. The casing accommodates the impeller and includes an air intake portion positioned adjacent to the side panel. The air intake portion includes a downstream end portion and an inner wall surface. The side panel includes an upstream end portion and an inner panel surface that is an inner surface of the side panel. The downstream end portion and the upstream end portion face each other across a space in an angular range. A difference between a smallest inner radius of the inner wall surface of the air intake portion and a smallest inner radius of the inner panel surface is smaller than or equal to a thickness of the side panel in the angular range.
    Type: Grant
    Filed: December 7, 2016
    Date of Patent: November 12, 2019
    Assignee: DENSO CORPORATION
    Inventors: Hiroyuki Usami, Masaharu Sakai, Sho Kosaka, Yohei Kamiya
  • Patent number: 10436068
    Abstract: A gas turbine engine includes a compressor section, combustion section, and turbine section. The turbine section includes a turbine component stage, the turbine component stage including a plurality of turbine components together including a flowpath surface along a circumferential direction of the gas turbine engine. The flowpath surface defines in part a core air flowpath of the gas turbine engine and further defines a contour along the circumferential direction. The contour repeats less frequently than once per turbine component to accommodate a hot gas streak through the turbine section.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: October 8, 2019
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Patent number: 10400785
    Abstract: A propeller formed along the lines of a vortex, i.e. a Fibonacci spiral projected onto a surface formed by a square hyperbola. Fluid flows evenly along the length of the propeller with less turbulence allowing it to operate at a higher pitch without stalling and resulting in reduced power requirements for a given flow rate. The underlying geometric shape of a vortex is an equiangular logarithmic spiral also known as golden spiral or Fibonacci spiral as is often found in natural objects ranging from sea shells to spiral galaxies. When viewed three dimensionally, the fluid flow in a vortex can be drawn as a projection of a golden spiral onto a surface of revolution of a square hyperbola where the vertex is equal to one and the focus is equal to the square root of 2.
    Type: Grant
    Filed: April 7, 2015
    Date of Patent: September 3, 2019
    Assignees: Cleanfuture Energy Co Ltd., Uli Kruger
    Inventors: Uli Kruger, Sutepong Pochana
  • Patent number: 10392938
    Abstract: A pre-sintered preform (114) and a repair process (100) utilizing the pre-sintered preform (114) are disclosed, each of which result in a brazement (116) comprising a replacement protective coating (118) deposited on a component surface (110). The protective coating (118) exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component (102).
    Type: Grant
    Filed: August 9, 2018
    Date of Patent: August 27, 2019
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Somesh J. Ghunakikar, James A. Yarbrough, Mark A. Garcia
  • Patent number: 10377475
    Abstract: A nozzle for use with a rotor blade for a reaction drive type helicopter includes a first wall, a second wall opposing the first wall, and sidewalls extending between the first wall and the second wall enclosing a cavity having an upstream end and a downstream end. The nozzle includes an inlet section for receiving a gasflow at the upstream end. The distance between the first wall and the second wall reduces to a throat downstream of the inlet section. An expansion section extending from the throat, downstream thereof.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: August 13, 2019
    Assignee: RJ HELICOPTER CORP.
    Inventor: David J. White
  • Patent number: 10301941
    Abstract: A turbine engine rotor blade including an airfoil defined by plane airfoil sections stacked in a radial direction, each airfoil section being positioned radially at a height H, where height H is expressed as a percentage of the total height of the airfoil, and being identified by its sweep angle ? and its dihedral angle ?, wherein the sweep angle ? varies as a function of height H in such a manner that the sweep angle ? reaches a maximum at a height H?M, the value H?M lying in the range 5% to 40%, and the sweep angle ? increases from 0% to H?M, and wherein the dihedral angle ? varies as a function of H, the dihedral angle ? being a decreasing function of height H for heights H lying in the range 0% to H?1, H?1 lying in the range 10% to 40%.
    Type: Grant
    Filed: August 4, 2014
    Date of Patent: May 28, 2019
    Assignee: SAFRAN AIRCARFT ENGINES
    Inventors: Damien Joseph Cellier, Alicia Lise Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Vincent Paul Gabriel Perrot, Laurent Christophe Francis Villaines
  • Patent number: 10288076
    Abstract: A cooling system that includes two or more fans that each have a chassis. The chassis includes a first face, a second face, and a sidewall. The fans then can be attached to each other by attaching a sidewall of a first fan chassis to a sidewall of a second fan chassis. An adjustable vane is attached perpendicularly and approximately equidistant between the fans, with an angular control element that is attached to the first fan chassis. The vane can be oriented such that the vane divides the airflow distributed to the fans. The vane then can be adjusted radially by the angular control element, which is attached to the fan chassis. If an impeller of a fan chassis fails the vane can be adjusted radially using an angular control element to distribute more airflow to the failed fan superimposing the non-failed fan chassis.
    Type: Grant
    Filed: November 17, 2017
    Date of Patent: May 14, 2019
    Assignee: International Business Machines Corporation
    Inventors: William J. Anderl, Karl Stathakis
  • Patent number: 10247043
    Abstract: A ducted cowl support includes an annular structure configured to be mounted to an annular turbine engine frame and including one or more bypass ducts integrally formed therein.
    Type: Grant
    Filed: December 11, 2015
    Date of Patent: April 2, 2019
    Assignee: General Electric Company
    Inventors: William Howard Hasting, David Edward Dale, Jared Matthew Wolfe
  • Patent number: 10202866
    Abstract: The present disclosure relates generally to a system for handling a gas turbine engine fan case. The system includes a composite fan containment case including a case outer surface, a case inner surface, and at least one main case aperture extending from the case outer surface through the case inner surface, and at least one shear puck, the at least one shear puck including a shear puck protrusion; wherein the shear puck protrusion of each of the at least one shear pucks is disposed within a respective one of each of the at least one main case apertures.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: February 12, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Darin S. Lussier
  • Patent number: 10174623
    Abstract: The present invention provides a method of designing a manufacturing geometry for a tip portion of a rotary blade for a gas turbine engine. The method comprises first devising a theoretical hot running geometry of the tip portion at a specified design condition. Next, the theoretical operational forces acting on the theoretical hot running geometry at the specified design condition are calculated e.g. using CFD software. Then, the manufacturing geometry is determined (e.g. using FEA analysis) using the calculated theoretical operational forces.
    Type: Grant
    Filed: April 26, 2016
    Date of Patent: January 8, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: John M Scott
  • Patent number: 10145385
    Abstract: A liquid pump has a pump housing defining a pump chamber. A motor is accommodated within the pump housing and separated from the pump chamber by an end cap. An impeller disposed within the pump chamber is driven by the motor. The pump chamber has an inlet and one or more outlets. The outlets are located on a sidewall of the pump chamber and extend in a direction substantially tangential to an outer circumference of the pump chamber. Each outlet has a first end near the pump chamber, and a second end remote from the pump chamber. A cross-sectional area S1 of the first end is smaller than a cross-sectional area S2 of the second end, forming a diffuser within the outlet.
    Type: Grant
    Filed: May 21, 2014
    Date of Patent: December 4, 2018
    Assignee: JOHNSON ELECTRIC S.A.
    Inventors: Chuan Jiang Guo, Chuan Hui Fang, Hay Tak Tsang
  • Patent number: 10094234
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: January 22, 2016
    Date of Patent: October 9, 2018
    Assignees: Rolls-Royce North America Technologies Inc., Rolls-Royce Corporation
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman
  • Patent number: 10060440
    Abstract: A centrifugal fan includes: a casing having an upper casing with an air suction opening, a lower casing, and a plurality of support members disposed between the lower casing and the upper casing with air discharge openings provided between the support members; an impeller disposed between the upper and lower casings, and including an annular upper shroud provided on an upper casing side, a base plate integrally formed with the annular upper shroud, and a plurality of blades arranged along a circumferential direction between the annular upper shroud and the base plate; and a fan motor which rotates the impeller. A plurality of recesses are provided on the upper surface of the upper casing, and formed to surround the air suction opening, and a plurality of ribs are radially provided around the air suction opening and between the adjacent recesses.
    Type: Grant
    Filed: November 5, 2015
    Date of Patent: August 28, 2018
    Assignee: Minebea Co., Ltd.
    Inventors: Seiya Fujimoto, Takako Otsuka, Yuzuru Suzuki, Masaki Ogushi
  • Patent number: 10041398
    Abstract: A turbine comprises a turbine housing defining a turbine inlet upstream of a turbine wheel and a turbine outlet downstream of the turbine wheel; a wastegate passage connecting the turbine inlet and the turbine outlet; and a wastegate valve comprising a movable valve member. The wastegate valve has an open state and a closed state. The valve member is mounted to an actuation member passing through an actuator conduit of the turbine housing, and movable so as to move the wastegate valve between the open and closed states. The turbine further comprises a sealing arrangement configured to provide a seal arranged to substantially prevent gas from passing from the turbine outlet into the actuator conduit. The sealing arrangement is configured such that when the valve member is urged into the closed state by the actuator member the sealing effectiveness of the sealing arrangement is increased.
    Type: Grant
    Filed: July 10, 2014
    Date of Patent: August 7, 2018
    Assignee: Cummins Ltd.
    Inventor: James Alexander McEwen
  • Patent number: 9999162
    Abstract: A circuit layout includes two or more high performance processing nodes that are cooled by a cooling fan. The cooling fan resides in a cooling fan assembly that relies on principles of aerodynamics to maximize airflow. The cooling fan assembly is coupled to the opposite side of a backplane to which the circuit layout is mounted. The backplane includes large ventilation holes to permit the cooling fan to induce significantly more airflow across the circuit layout than possible with conventional designs. At least one advantage of the approaches discussed herein is circuit layouts can be constructed to meet the competing objectives of high node performance and high node density. Accordingly, data centers can be built that offer high performance computing without requiring a significant increase in physical real estate.
    Type: Grant
    Filed: January 14, 2015
    Date of Patent: June 12, 2018
    Assignee: SUPER MICRO COMPUTER, INC.
    Inventors: Richard S. Chen, Andy Chen, Jonathan M. Lee, Wenjuan Yu
  • Patent number: 9920772
    Abstract: A system may include a reversible fan module that creates an airflow. The reversible fan module may include a set of attachment members, disposed on a face of the reversible fan module, that secure the reversible fan module a first orientation or a second orientation. The system may further include a chassis that include a divider that divides an interior region of the chassis into a front compartment and a rear compartment, a window, disposed on the divider, that allows airflow between the front compartment and the rear compartment, a first opening in the chassis that opens the front compartment to a first external region, a second opening in the chassis that opens the rear compartment to a second external region, and a bay that receives the reversible fan module.
    Type: Grant
    Filed: August 29, 2016
    Date of Patent: March 20, 2018
    Assignee: Arista Networks, Inc.
    Inventors: Robert Wilcox, Richard Hibbs, Jiayi Wu
  • Patent number: 9909447
    Abstract: A method for manufacturing a turbomachine casing from composite material including: creating a semi-rigid protective layer from dry glass fibers that protects against galvanic corrosion, arranging the protective layer on a profiled mandrel by applying the protective layer against the annular radial flange thereof, forming and densifying the fibrous reinforcement on the mandrel while covering the protective layer.
    Type: Grant
    Filed: July 8, 2013
    Date of Patent: March 6, 2018
    Assignee: SNECMA
    Inventors: Timothee Elisseeff, Sylvain Corradini
  • Patent number: 9879680
    Abstract: A multi-stage centrifugal pump assembly includes at least two impellers (2, 6) and two impeller groups (4, 8) which are consecutive in a flow direction and each with at least one impeller (2, 6). A backflow channel (24) connects an exit side of the first impeller group (4) to an entry side thereof is located in a first impeller group (4) of the two impeller groups (4, 8).
    Type: Grant
    Filed: March 29, 2012
    Date of Patent: January 30, 2018
    Assignee: Grundfos Management a/s
    Inventors: Steen Mikkelsen, Aage Bruhn, Bo Møller Jensen
  • Patent number: 9810225
    Abstract: A turbocharger is of reduced size and easy to assemble. A rotor blade upstream flow channel space has a cylindrical portion that is gradually reduced in the downstream direction of exhaust gas flow corresponding with a reduction in volume of the scroll chamber. A back plate is formed so as to swell out toward the rotor blade gradually in the downstream direction corresponding with the reduction in volume of the scroll chamber. The back plate, at a termination end thereof, approaches the rotor blade and reaches a position adjacent to a leading edge of the rotor blade whereby the flow channel space disappears substantially at this termination end.
    Type: Grant
    Filed: October 17, 2012
    Date of Patent: November 7, 2017
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Takao Yokoyama, Motoki Ebisu
  • Patent number: 9797268
    Abstract: Aspects of the disclosure are directed to a shaft of an engine of an aircraft, an oil scoop coupled to the shaft, a first portion of a sensor integrated with the oil scoop, and a second portion of the sensor coupled to a structure of the engine. In some embodiments, the first portion of the sensor comprises at least one tooth.
    Type: Grant
    Filed: March 27, 2015
    Date of Patent: October 24, 2017
    Assignee: United Technologies Corporation
    Inventor: James L. Lucas
  • Patent number: 9790958
    Abstract: A housing of an air cycle machine compressor is provided. The housing includes a body defining an aperture therethrough and one or more bosses located circumferentially around the body, the body having a general wall thickness. A duct is configured on a portion of the body. The body includes a first angle defining an area extending over a circumferential direction of the body having a first wall thickness different from the general wall thickness. The first angle is configured with the first wall thickness having a ratio of 1.565 as compared to the general wall thickness.
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: October 17, 2017
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Darryl A. Colson, Brent J. Merritt
  • Patent number: 9776707
    Abstract: The invention relates to an aircraft turboprop engine having two unducted propellers, coaxial about a rotation axis (LL), respectively upstream (12) and downstream (14?), each propeller comprising an annular row of blades, the blades of the downstream propeller (14?) each having a truncated head and each comprising a leading edge (20?) and a trailing edge (22?), the radially external ends (A2, B1) of which are distant from each other and are connected by a terminal edge (21?), characterised in that the terminal edge (21?) of each blade of the downstream propeller (14?) has, at at least two points, tangents in a meridian plane having different slopes, the upstream end (A) of the terminal edge defining a maximum radial dimension (R2) of the blade and its downstream end (B1) defining a minimum radial dimension (R3) of the terminal edge.
    Type: Grant
    Filed: May 28, 2015
    Date of Patent: October 3, 2017
    Assignee: SNECMA
    Inventors: Anthony Pascal Eloi Louet, Clement Marcel Maurice Dejeu, Jonathan Evert Vlastuin
  • Patent number: 9651917
    Abstract: A cooling device includes a fan main body, a first housing, a second housing, a drive portion, and a rotation control portion. The second housing is configured to be rotatable between a predetermined first rotation position P1 and a second rotation position P2 reached through a rotation by a predetermined angle about a shaft from the first rotation position P1. The rotation control portion controls the drive portion to move the second housing to the first rotation position P1 or the second rotation position P2.
    Type: Grant
    Filed: May 20, 2016
    Date of Patent: May 16, 2017
    Assignee: KYOCERA Document Solutions Inc.
    Inventors: Noriko Masuta, Kaori Harada
  • Patent number: 9605552
    Abstract: A cover plate adapted to axially overlie root or shank portions of one or more buckets or blades secured to a turbomachine wheel, includes an arcuate cover plate body adapted to be secured to the turbomachine wheel so as to cover a root portion of at least one of the turbine buckets or blades; and at least one arcuate angel-wing seal segment detachably secured to one side of the arcuate cover plate body.
    Type: Grant
    Filed: June 10, 2013
    Date of Patent: March 28, 2017
    Assignee: General Electric Company
    Inventors: Michael Anthony Wondrasek, Nicholas Alvin Hogberg
  • Patent number: 9568009
    Abstract: A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side. The cylindrical upstream side can extend from a leading edge of the bladed component, or a point upstream of it, to a location between the leading edge and trailing edge of the component. The conical downstream side can extend past the trailing edge of the bladed component. The bladed component can be a fan blade or a compressor blade.
    Type: Grant
    Filed: November 27, 2013
    Date of Patent: February 14, 2017
    Assignee: Rolls-Royce Corporation
    Inventors: Bronwyn Power, Roy D. Fulayter, Jonathan M. Rivers
  • Patent number: 9556879
    Abstract: A compressor is provided with a substantially tubular compressor casing, a substantially circular lid that is provided inside an inner periphery of the compressor casing so as to close off an end surface of the compressor casing, a space that is enclosed by the lid and an inner circumferential surface of the compressor casing so as to accommodate a blade, and seal member that is provided in a circumferential direction on the space side of an outer circumferential surface of the lid, wherein a slit part is provided on the lid, radially inside the outer circumferential surface, where the seal member is provided, so as to extend in the axial direction from the space side of the lid.
    Type: Grant
    Filed: July 21, 2011
    Date of Patent: January 31, 2017
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Hitoshi Shinohara, Mitsuhiko Ota
  • Patent number: 9512848
    Abstract: A turbine assembly mounted to a pump rotor via mounting bolts. The turbine includes fins extending therefrom for pumping gasses and suspended particles from a semiconductor processing chamber. The tops of the bolts are recessed from the top surface of the turbine in a bolt cavity having an open end. A cap member is mounted over and seals the open end of the bolt cavity via a center bolt. The cap member has a shaped upper surface (conical, parabolic, squared, rounded) for deflecting particles away from the center of the turbine and toward the turbine's fins. The cap member's upper surface can include particle deflecting features such as fins, channels or asymmetric shapes to enhance particle deflection as the cap member rotates.
    Type: Grant
    Filed: September 10, 2012
    Date of Patent: December 6, 2016
    Assignee: Texas Capital Semiconductor, Inc.
    Inventor: Roger L. Bottomfield
  • Patent number: 9470093
    Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge 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. Facing pressure and suction sides of adjacent airfoils 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 airfoils. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side. The width diverges without converging along the channel for at least some of the span positions.
    Type: Grant
    Filed: April 29, 2015
    Date of Patent: October 18, 2016
    Assignee: United Technologies Corporation
    Inventors: Edward J. Gallagher, Sue-Li Chuang
  • Patent number: 9266425
    Abstract: The air guide plate includes a plate body formed of a resin material and deformable skirt portions which are formed of the same resin material as the plate body and integrally formed on an outer periphery of the plate body. The air guide plate is arranged such that the plate body is disposed at a front of an automobile without connecting to automobile parts, thereby forming a gap between the outer periphery of the plate body and the automobile parts arranged around the plate body. The deformable skirt portions are disposed so as to be in contact with the automobile parts under flexural deformation, thereby closing the gap by the deformable skirt portions to prevent the air from leaking through the gap.
    Type: Grant
    Filed: September 19, 2014
    Date of Patent: February 23, 2016
    Assignee: Kojima Press Industry Co., Ltd.
    Inventor: Hiroshi Kawahira
  • Patent number: 9175567
    Abstract: An airfoil platform comprises a leading edge portion and a trailing edge portion. The trailing edge portion comprises a first region having a convex flowpath contour, a second region having an intermediate flowpath contour extending downstream from the convex flowpath contour, and a third region having a concave or linear flowpath contour extending downstream from the intermediate flowpath contour to a downstream end of the trailing edge portion of the platform.
    Type: Grant
    Filed: February 29, 2012
    Date of Patent: November 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Andrew S. Aggarwala, Thomas J. Praisner
  • Patent number: 9074576
    Abstract: This invention consists of special structures, methods and devices, which make up a system to provide controlled capture of the full ocean wave cycle, at or near the ocean shore, which includes, surface and some sub-surface energy, the backwash and the undertow. And, it does it in a dynamic and somewhat continuous flow (with the exception of some small storage). The system adjusts for low wave and high wave activity, and also for variations in the tide. The main structure has a barrier wall inside, which can also adjust for variations in the tide, the amount of energy to be collected at high wave activity and in the period/frequency of the waves. The structure includes a small reservoir to help capture more water during low wave activity. The captured water flow is transported to a suitable turbine/generating device for producing electrical energy. A method and some devices are available for controlling the influx of water into the turbine.
    Type: Grant
    Filed: January 29, 2014
    Date of Patent: July 7, 2015
    Inventor: Jon Selby Potts
  • Patent number: 9039359
    Abstract: A device for converting the kinetic energy of molecules into useful work includes an actuator configured to move within a fluid or gas due to collisions with the molecules of the fluid or gas. The actuator has dimensions that subject it to the Brownian motion of the surrounding molecules. The actuator utilizes objects having multiple surfaces where the different surfaces result in differing coefficients of restitution. The Brownian motion of surrounding molecules produce molecular impacts with the surfaces. Each surface then experiences relative differences in transferred energy from the kinetic collisions. The sum effect of the collisions produces net velocity in a desired direction. The controlled motion can be utilized in a variety of manners to perform work, such as generating electricity or transporting materials.
    Type: Grant
    Filed: December 23, 2011
    Date of Patent: May 26, 2015
    Inventor: Lee Ervin
  • Publication number: 20150139795
    Abstract: In various implementations, a plug fan assembly may include a plug fan housing and a blower wheel. The plug fan housing may include angled corner(s) and/or a flared portion. The plug fan may be utilized in an air conditioning system.
    Type: Application
    Filed: November 21, 2013
    Publication date: May 21, 2015
    Applicant: LENNOX INDUSTRIES INC.
    Inventors: H. Gene Havard, Jr., Bryan Smith, Miguel Montemayor
  • Patent number: 9022730
    Abstract: A supersonic compressor includes a fluid inlet, a fluid outlet, a fluid conduit extending therebetween, and at least one supersonic compressor rotor disposed within the fluid conduit and including a fluid flow channel that includes a throat portion. The supersonic compressor also includes a fluid control device coupled in fluid communication with at least one fluid source and an inlet of the fluid flow channel. The fluid control device channels a first fluid to the fluid flow channel inlet. The first fluid has a first plurality of fluid properties that facilitate attainment of supersonic flow of the first fluid in the throat portion during a first operational mode. The fluid control device further channels a second fluid to the fluid flow channel inlet. The second fluid has a second plurality of fluid properties that permit maintenance of supersonic flow of the second fluid in the throat portion.
    Type: Grant
    Filed: October 8, 2010
    Date of Patent: May 5, 2015
    Assignee: General Electric Company
    Inventors: Martin Vysohlid, Douglas Carl Hofer
  • Publication number: 20150110613
    Abstract: A cowl for use in a nacelle is provided. The nacelle at least partially surrounds an engine that extends circumferentially about an axially-extending engine centerline. The cowl includes a first side portion and a second side portion. The first and second side portions each are pivotably connected to the nacelle proximate a top of the nacelle. The first and second side portions are configured so that they abut one another to form an external split line proximate the top of the nacelle.
    Type: Application
    Filed: October 18, 2013
    Publication date: April 23, 2015
    Applicant: Rohr, Inc.
    Inventor: Michael Aten
  • Patent number: 8998569
    Abstract: A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure.
    Type: Grant
    Filed: August 17, 2011
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventor: Russell B. Witlicki
  • Patent number: 8985942
    Abstract: An exhaust duct comprises a shroud body, a forward flange assembly, an aft flange assembly, an intermediate flange assembly, and a first plurality of bleed ports. The forward flange assembly extends radially inward from a forward shroud end for securing the forward shroud end downstream of a final turbine stage. The aft flange assembly extends circumferentially around and radially inward from an aft shroud end for securing the aft shroud end to an engine tail cone. The intermediate flange assembly is disposed forward of the aft flange assembly, and extends circumferentially around and radially inward from the shroud body for securing the shroud body to an engine bearing housing. The first plurality of bleed ports is disposed around the shroud body forward of a junction with the intermediate flange.
    Type: Grant
    Filed: July 2, 2012
    Date of Patent: March 24, 2015
    Assignee: United Technologies Corporation
    Inventors: William A. Daniels, John J. Korzendorfer, David A. Debyah, Scott A. Ladd
  • Publication number: 20150078889
    Abstract: A casing for a turbine engine compressor, including: cavities in a thickness of the casing, extending in parallel to one another from an inner face of the casing along a circumference thereof, the cavities not being in communication with one another. The cavities, which are elongate and extend along a main direction of orientation between two side walls, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the inner face of the casing. The upstream border of the cavities takes a form of a wavy line including at least two alternate undulations over a length thereof between the side walls.
    Type: Application
    Filed: April 15, 2013
    Publication date: March 19, 2015
    Applicant: SNECMA
    Inventors: Thierry Jean-Jacques Obrecht, Olivier Stephane Domercq
  • Publication number: 20150033730
    Abstract: A component of an air cycle machine includes a fan housing portion, a compressor housing portion, a main bore housing radius, a static seal radius, a shroud pilot housing radius, and an insulator seal plate housing radius. The fan housing portion includes a shroud for a fan section. The compressor housing portion includes a shroud for a compressor air inlet, a shroud portion for a compressor blade section, and a shroud portion for a compressor air outlet. The main bore housing radius is arranged about a central axis and is configured to circumscribe a shaft arranged along the central axis, the main bore housing radius being between 1.9400 and 1.9440 inches. The static seal portion is arranged about the central axis and positioned longitudinally adjacent to the main bore housing portion. The static seal portion is configured to circumscribe a static seal defined by the shaft, and has a radius between 2.0420 and 2.0440 inches. The shroud pilot housing radius is arranged about the central axis.
    Type: Application
    Filed: August 2, 2013
    Publication date: February 5, 2015
    Applicant: Hamilton Sundstrand Corporation
    Inventors: Craig M. Beers, Brent J. Merritt
  • Patent number: 8939717
    Abstract: A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion to which a row of vanes is affixed for providing structural support for the vanes in the engine section, and an aft hook extending from an aft side of the main body portion with reference to a direction of air flow through the engine section. The aft hook is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The support ring does not include a forward hook having a flange that extends axially from a forward or aft side of the forward hook with reference to the direction of air flow through the engine section.
    Type: Grant
    Filed: October 25, 2013
    Date of Patent: January 27, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Ching-Pang Lee, Mrinal Munshi, Adam C. Pela, Paul Bradley Davis, Matthew H. Lang
  • Publication number: 20150023782
    Abstract: A flow generator includes a housing, a blower structured to generate a flow of pressurized breathable air, and a suspension device to support the blower within the housing and provide a pressure seal between low and high pressure sides of the blower. The suspension device includes a bellows-like portion provided along the perimeter of the blower to absorb shock applied at least radially to the blower and one or more cones provided along upper and/or lower sides of the blower to absorb shock applied at least axially to the blower.
    Type: Application
    Filed: December 20, 2012
    Publication date: January 22, 2015
    Inventors: Allan Freas Velzy, Samuel Aziz Mebasser, Roman Vinokur, Kevin Gene McCulloh, Michael David Bednar, Karl Yutaka Iwahashi, David Brent Sears, Peter Jeffrey Thomas, Yeu-chuan Hsia, Hiroshi Suzuki, Benjamin An Shing Chao
  • Publication number: 20150016977
    Abstract: A turbomachine and a method for the assembly of the turbomachine with a housing and with a rotor, in which at least one cover of the housing is fastened to the rotor, and the combination is placed into a lower part of the housing and is then enclosed by an upper part of the housing, is provided. To attain centered mounting of the cover assembly and to thus prevent damage to the shaft seal, it is proposed that the combination, as it is placed in, is supported on at least one guide means in the housing, and the guide means forms a guide for the cover in the housing, by means of which guide the placed-in cover is held spaced apart from the housing lower part and the housing upper part with a radial assembly gap.
    Type: Application
    Filed: February 15, 2013
    Publication date: January 15, 2015
    Applicant: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Erich Muranyi, Dieter Nass, Gregor Senyk