Plural And Arcuately Or Circularly Arranged In Radial Plane Around Runner Axis Patents (Class 415/208.2)
  • Patent number: 10638900
    Abstract: An air blowing device includes a motor, a ring-shaped cover, an impeller, and an impeller housing. The impeller includes a base portion and moving blades. The impeller housing includes an exhaust air guide portion. The ring-shaped cover includes a ring-shaped cover upper face portion and a ring-shaped cover outer edge portion having faces disposed across a gap that configures a flow path through which a fluid is guided. The gap has a first width where a distance between the faces is shortest, and which is smaller than a flow-in opening width where the fluid flows into the gap and a flow-out opening width where the fluid flows out.
    Type: Grant
    Filed: August 24, 2016
    Date of Patent: May 5, 2020
    Inventor: Ryosuke Hayamitsu
  • Patent number: 10563543
    Abstract: The present disclosure provides an exhaust diffuser for a gas turbine engine. The exhaust diffuser may include a hub, a casing, and a strut extending between the hub and the casing. The hub may include an angled configuration about the strut and a substantially flat configuration downstream of the angled configuration.
    Type: Grant
    Filed: May 31, 2016
    Date of Patent: February 18, 2020
    Assignee: General Electric Company
    Inventors: Santhosh Kumar Vijayan, Deepesh Dinesh Nanda, Manjunath Bangalore Chengappa
  • Patent number: 10533581
    Abstract: A vane stage assembly includes an airfoil including a leading edge and a trailing edge. An inner shroud extends from the leading edge to the trailing edge for supporting the airfoil. The shroud includes a forward portion including an axial width and a forward thickness extending in a radial direction. A ratio of the forward radial thickness divided by the forward axial thickness is between 0.64 and 1.11 for defining a natural frequency of the airfoil. A gas turbine engine and method are also disclosed.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: January 14, 2020
    Assignee: United Technologies Corporation
    Inventors: William R. Edwards, Charles H. Warner
  • Patent number: 10502076
    Abstract: A turbine section is provided for a gas turbine engine. The turbine section is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least a first splitter blade disposed within the inter-turbine duct. The first splitter blade includes a pressure side facing the shroud, a suction side facing the hub, and at least one vortex generating structure positioned on the suction side.
    Type: Grant
    Filed: November 9, 2017
    Date of Patent: December 10, 2019
    Inventors: Vinayender Kuchana, Balamurugan Srinivasan, Craig Mckeever, Malak Fouad Malak
  • Patent number: 10465687
    Abstract: The disclosure describes a flow conditioning device for dampening pulses and improving performance of a compressor. In one approach, a diffuser device includes a housing member having a first end and a second end, the housing member coupled to an outlet of a compressor, and a diffuser member disposed within the housing member. The diffuser member is in fluid communication with a working fluid delivered from the compressor, and includes a core member extending along a longitudinal axis of the diffuser member, and a plurality of flutes extending radially from the core member. In some approaches, the plurality of flutes and an inner surface of the housing define a plurality of fluid channels for delivering the working fluid from the first end to the second end of the housing member. In some approaches, the diffuser member is rotatably coupled to the housing member.
    Type: Grant
    Filed: August 9, 2017
    Date of Patent: November 5, 2019
    Assignee: HOWDEN ROOTS LLC
    Inventor: Dale E. Husted
  • Patent number: 10422349
    Abstract: A propeller fan includes a rotary blade hub driven in rotation about a rotation axis, and a rotary blade installed at an outer periphery of the rotary blade hub. The rotary blade includes a rotary blade body protruding from an outer peripheral surface of the rotary blade hub, and a rib formed on an outer peripheral edge portion of a pressure surface of the rotary blade body so as to extend along an outer peripheral edge of the rotary blade body.
    Type: Grant
    Filed: July 3, 2015
    Date of Patent: September 24, 2019
    Inventors: Kazuyasu Matsui, Shimei Tei, Tooru Iwata, Shigeyuki Takaoka
  • Patent number: 10414007
    Abstract: A turbine power unit for a power tool having a turbine housing with an interior space configured to receive therein a fluid powered turbine supported for rotation on a bearing within the turbine housing. A service opening through the turbine housing into the interior space thereof, the service opening configured to permit installation and removal of a bearing into and out of the interior space of the turbine housing. A removable cover releasably securable to the turbine housing over the service opening and transitionable between an open configuration in which a bearing can be installed into and removed from the interior space of the turbine housing through the service opening and a closed configuration in which an installed bearing within the interior space is secured for operation in the turbine housing.
    Type: Grant
    Filed: April 19, 2019
    Date of Patent: September 17, 2019
    Assignee: SFI ALPHA SPIN LTD.
    Inventor: Gerald Jay Sanders
  • Patent number: 10415392
    Abstract: A contoured turbine airfoil assembly including an end wall (30a) formed by platforms (30) located circumferentially adjacent to each other, and a row of airfoils (34a, 34b) integrally joined to the end wall (30a) and spaced laterally apart to define flow passages (46) therebetween for channeling gases in an axial direction. A trough (62) is defined between a pressure side ridge (48) and a suction side ridge (58) located forward of each pair of airfoils (34a, 34b). Each trough (62) has a direction of elongation aligned to direct flow into the flow passage (46) centrally between each pair of airfoils (34a, 34b).
    Type: Grant
    Filed: June 18, 2014
    Date of Patent: September 17, 2019
    Assignee: SIEMENS ENERGY, INC.
    Inventor: Andrew S. Lohaus
  • Patent number: 10378509
    Abstract: A fluid flow turbine having a turbine rotor with a plurality of blades (also known as “vanes”) for converting the kinetic energy of a flowing fluid into mechanical rotational energy of the turbine rotor is provided by this invention. The plurality of blades are defined by a continuously sinuous curve outer edge that results in the lateral surface of the blades having a lower concave portion for scooping up the horizontal incoming fluid flow and redirecting it to a substantially vertical fluid flow along the lateral surface of the blade. The upper portion of the lateral surfaces of the blades is convex, causing the upper edge of the blades to tail off laterally so that the fluid flow exits the turbine in a substantially vertical direction, instead of turning back upon itself to reduces turbulence of the fluid flow inside the turbine. The fluid flow turbine can comprise a small wind turbine that will produce electrical power at low wind speeds, and can be mounted to the top of a building.
    Type: Grant
    Filed: October 6, 2017
    Date of Patent: August 13, 2019
    Assignee: IAP, Inc.
    Inventor: Michael R. Theis
  • Patent number: 10364705
    Abstract: A strut assembly for a bearing compartment of a gas turbine engine includes an inner case, an outer case, and a first plurality of struts. The inner case is disposed within the bearing compartment and includes a first axis. The outer case defines an exterior of the bearing compartment and includes a second axis disposed co-axially with the first axis. The inner and outer cases define a flowpath between the inner and outer cases. Each strut of the first plurality of struts extends between and is connected to the inner and outer cases. The first plurality of struts is configured to maintain concentric positioning between the inner and outer cases and to allow relative changes in size between the inner and outer cases without deforming the inner case.
    Type: Grant
    Filed: May 4, 2017
    Date of Patent: July 30, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas O. Harris, Lubomir A. Ribarov
  • Patent number: 10316671
    Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.
    Type: Grant
    Filed: July 17, 2015
    Date of Patent: June 11, 2019
    Inventors: Pitchaiah Vijay Chakka, James D. Hill, David R. Pack
  • Patent number: 10287904
    Abstract: A turbine engine is disclosed and includes an airflow passage including an inner surface defined by a main shroud and a shroud extension. A flow splitter is disposed radially outward of the inner surface and axially overlapping the shroud extension. The turbine engine further includes a rotor including a blade proximate the shroud extension and an annular gap defined between the shroud extension and the blade of a first axial length less than a second axial length between the blade and an end of the flow splitter.
    Type: Grant
    Filed: November 4, 2014
    Date of Patent: May 14, 2019
    Assignee: United Technologies Corporation
    Inventors: Victor G. Filipenco, Anthony R. Bifulco
  • Patent number: 10227895
    Abstract: A case assembly for a gas turbine engine comprising annular case components each having a central axis. Radial struts each have a radial axis and intersect the annular case components. A stress dissipation mass projecting from a continuous surface of at least one of the struts at the intersection with a corresponding annular case component, the stress dissipation mass being on either side of a plane passing through the radial axis of the strut and the central axis of the corresponding annular case component. A method for dissipating thermal and mechanical stresses on a strut in a case assembly for a gas turbine engine is also provided.
    Type: Grant
    Filed: December 20, 2013
    Date of Patent: March 12, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Assaf Farah
  • Patent number: 10184477
    Abstract: A series fan inclination structure includes an inclined frame body assembly, a first rotor assembly and a second rotor assembly. The inclined frame body assembly has a receiving space. The receiving space includes a first space, a second space and a flow guide passage. A first base seat is obliquely disposed in the first space. A second base seat is obliquely disposed in the second space. The flow guide passage is formed between the first and second base seats in communication with the first and second spaces. The first and second rotor assemblies are correspondingly rotatably disposed on the first and second base seats. The series fan inclination structure is able to greatly reduce the vibration and lower the noise caused by the interaction of the dipole.
    Type: Grant
    Filed: December 5, 2016
    Date of Patent: January 22, 2019
    Inventors: Bor-Haw Chang, Yu-Tzu Chen, Chung-Shu Wang
  • Patent number: 10161251
    Abstract: A rotor disk for a turbomachine includes a disk body, a rim configured to connect to or include a rotor blade disposed on a radially outward portion of the disk body, a bore defined in a radially inward portion of the disk body and configured to be radially adjacent to a shaft, and a thermal regulation aperture defined in the disk body, radially inward of the rim, for allowing flow to pass axially through the disk body when disposed in a stage of a turbomachine, and a thermal regulation aperture defined in the disk body for allowing flow to pass through the disk body when disposed in a stage of a turbomachine.
    Type: Grant
    Filed: September 11, 2015
    Date of Patent: December 25, 2018
    Inventors: Matthew E. Bintz, Matthew P. Forcier, Paul J. Hiester
  • Patent number: 10036276
    Abstract: A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.
    Type: Grant
    Filed: June 14, 2013
    Date of Patent: July 31, 2018
    Assignees: United Technologies Corporation, GKN Aerospace Sweden AB
    Inventors: Daryl B. Mountz, Theodore W. Kapustka, Glenn Levasseur, Marcus Borg, Joakim Berglund, Anders Svahn, Johan Ockborn, Bengt Pettersson
  • Patent number: 10030668
    Abstract: An axial-flow fan includes a boss and a plurality of blades integrally resin-molded with a hub. An axial hole of the boss has a shaft of a drive motor inserted. The axial hole is formed at an axial center of the hub. The hub includes an outer perimeter cylinder and a lid. The outer perimeter cylinder has an opening formed at the axial center, and the blades are formed so as to project from the outer perimeter cylinder. The lid extends from the outer perimeter cylinder toward the boss so as to cover the opening of the outer perimeter cylinder. The lid connects the boss and the outer perimeter cylinder together. Reinforcing ribs are integrally resin-molded together with the hub and the boss on both axial-direction sides of the lid. The reinforcing ribs reinforce the connection between the hub and the boss.
    Type: Grant
    Filed: December 26, 2012
    Date of Patent: July 24, 2018
    Assignee: Daikin Industries, Ltd.
    Inventors: Azumi Kojima, Yuuta Yokoyama
  • Patent number: 9989068
    Abstract: A method for controlling an inlet-adjustment mechanism in an air inlet for a compressor so as to switch the mechanism in a binary fashion between two positions P1 and P2 for adjusting a flow area of the inlet. The method includes identifying a threshold line on a compressor map of pressure ratio versus corrected flow rate for the compressor. The threshold line is a line on which the pressure ratio and flow rate of the compressor are the same for the P1 and P2 positions of the inlet-adjustment mechanism at equal speeds. When the operating point of the compressor on the compressor map crosses the threshold line, the inlet-adjustment mechanism is switched from one of its binary positions to the other.
    Type: Grant
    Filed: December 1, 2015
    Date of Patent: June 5, 2018
    Assignee: Honeywell International Inc.
    Inventors: Vit Houst, William Joseph Smith
  • Patent number: 9988942
    Abstract: A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins extending outwards in a radial plane from the annular portion, each fin forming an angle relative to the radial direction. The fins have fastener zones at their outer peripheries, the fastener zones being inclined in the axial direction of the support so as to be suitable for fastening to an exhaust cone of the turbine engine.
    Type: Grant
    Filed: November 7, 2013
    Date of Patent: June 5, 2018
    Assignee: SNECMA
    Inventors: Patrick Sultana, Boucif Bensalah, Yannick Durand, Olivier Renon
  • Patent number: 9861774
    Abstract: A blower (10) includes a housing (20) including a proximal opening (23) and a distal opening (25) that are co-axially aligned, a stator component (30) provided to the housing, an impeller (60) positioned between the proximal opening of the housing and the stator component, and a motor (40) adapted to drive the impeller. The impeller includes a plurality of impeller blades. The stator component includes a plurality of air directing grooves (35) along its exterior surface. The leading edge of the air directing grooves extend tangentially outwards from the outer tips of the impeller blades and are configured to collect the air exiting the impeller blades and direct it from a generally tangential direction to a generally radial direction by dividing the air from the impeller and directing the air along a curved path towards the distal opening so that airflow becomes substantially laminar.
    Type: Grant
    Filed: August 11, 2010
    Date of Patent: January 9, 2018
    Assignee: ResMed Motor Technologies Inc.
    Inventors: Timothy Tsun-Fai Fu, Dion Charles Chewe Martin, Philippe Auguste Chalvignac, Quangang Yang, David Creusot
  • Patent number: 9863439
    Abstract: An annular backing plate for a diffuser in a centrifugal compressor comprises an inner diameter and an outer diameter disposed radially opposite the inner diameter. The backing plate also includes a first surface extending between the inner diameter and the outer diameter of the backing plate. A step is formed on the first surface proximate the inner diameter, wherein the step shifts a portion of the first surface encompassed by the step axially aft relative a portion of the first surface not encompassed by the step.
    Type: Grant
    Filed: September 11, 2014
    Date of Patent: January 9, 2018
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Seth E. Rosen, David A. Dorman, Craig M. Beers
  • Patent number: 9835334
    Abstract: A nozzle includes a nozzle body defining longitudinal axis with a liquid circuit extending axially in a downstream direction from a liquid inlet to a spray orifice, and an air circuit, e.g. an inner air circuit, extending axially downstream from an upstream air inlet to an air outlet proximate the spray orifice. An air swirler, e.g., an inner air swirler is mounted in the air circuit, wherein at least a portion of the air swirler is flush with or protrudes axially upstream relative to the air inlet.
    Type: Grant
    Filed: September 18, 2015
    Date of Patent: December 5, 2017
    Assignee: Delavan Inc.
    Inventors: Jason A. Ryon, Philip E. Buelow
  • Patent number: 9750392
    Abstract: Dishwasher appliances and vents for dishwasher appliances are provided. The dishwasher appliance includes a chamber for the receipt of articles for cleaning, and a door for selectively opening and closing the dishwasher appliance, the door having an interior wall and a bottom. The dishwasher appliance further includes a conduit disposed within the door. The dishwasher appliance further includes a vent for controlling the egress of fluid from the chamber through the first end, the vent received into the door. The vent includes a generally planer body, and a plurality of aperture assemblies defined in the body. Each of the plurality of aperture assemblies extends generally radially within the plane. The vent further includes a plurality of ribs extending from the body.
    Type: Grant
    Filed: February 28, 2014
    Date of Patent: September 5, 2017
    Inventors: Wilbur Carl Bewley, Jr., Paul Edward Newsom, II, Aaron Daniel Mink
  • Patent number: 9745984
    Abstract: A fan includes a frame and an impeller including a hub, a plurality of first blades, a first ring-shaped structure, and a plurality of second blades. The first blades are disposed around the hub. The hub and the first blades are surrounded by the first ring-shaped structure connected with the ends of the first blades, and a central area is structured therebetween. The second blades are connected with an outer rim of the first ring-shaped structure. The frame includes a base, an axle tube portion disposed on the base, and a receiving portion. The impeller is disposed on the axle tube portion. The receiving portion includes plural third blades disposed around the base corresponding to the central area. The first and third blades are matched to each other to be assembled for transforming a tangent velocity into a static pressure to increase the pressure generated by the central area.
    Type: Grant
    Filed: March 14, 2013
    Date of Patent: August 29, 2017
    Inventor: Shun-Chen Chang
  • Patent number: 9551498
    Abstract: An indoor unit of an air conditioner having improved structures of suction, discharge and/or flow passages which may increase operation efficiency, reduce noises and realize a compact size. The indoor unit includes a housing comprising a front panel and a rear panel coupled to a rear portion of the front panel, at least one discharge outlet exposed to a front of the front panel, at least one suction inlet formed in the rear panel at a position corresponding to the discharge outlet, at least one heat exchanger disposed at a front portion of the suction inlet to absorb heat from air introduced through the suction inlet or transfer heat to the air introduced through the suction inlet, and at least one diagonal flow fan disposed between the heat exchanger and the discharge outlet to suction air passing through the heat exchanger and discharge the air through the discharge outlet.
    Type: Grant
    Filed: June 27, 2013
    Date of Patent: January 24, 2017
    Inventors: Jung Ho Kim, Jin Baek Kim, Yeon Seob Yun, Tae Duk Kim, Woo Seog Song, Moon Sun Shin, Hae Gyun Shin, Ki Pyo Ahn, Joon Ho Yoon, Min Gi Cho, Jae Youn Cho, Sun Muk Choi, Hyoung Seo Choi, Dong Gi Han, Jin Woo Hong, Jun Hwang
  • Patent number: 9470091
    Abstract: A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade.
    Type: Grant
    Filed: February 6, 2013
    Date of Patent: October 18, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Sergio Elorza Gomez, Alexander Hergt, Ulrich Siller, Tim Schneider
  • Patent number: 9453496
    Abstract: Aspects of the manufacturing of Flow Deflection Devices (FDDs) for wind turbines are presented as a system that requires adjustments in order to improve power output and adjust for changes in different conditions yet provides stability of shape.
    Type: Grant
    Filed: May 26, 2010
    Date of Patent: September 27, 2016
    Inventors: Daniel Farb, Gadi Hareli, Joe Van Zwaren, Ken Kolman, Avner Farkash
  • Patent number: 9371836
    Abstract: A mixed flow fan assembly uses induced reverse ambient air flow through the in-line motor enclosure for motor cooling, motor segregation from primary exhaust contamination, and augmentation of volumetric flow rate. Induced ambient airflow through openings in and/or around the base of the fan housing balances low pressure around the fan wheel and the inlet cone to inhibit primary exhaust recirculation and increase volumetric flow rate. Straightening vanes downstream of the fan wheel are used to axially reorient radial and tangential velocity components of primary effluent flow. Airfoil impeller blades have a scalloped and/or perforated single-thickness trailing edge to attenuate fan noise.
    Type: Grant
    Filed: October 24, 2013
    Date of Patent: June 21, 2016
    Assignee: Dyna-Tech Sales Corporation
    Inventors: Brian J. Mornan, Frank J. Beitz
  • Patent number: 9291150
    Abstract: A system to generate electricity using a flow of air of the present disclosure, the system comprises a turbine assembly comprising a cylindrical blade drum comprising a plurality of vertical blades, a cone positioned at least substantially within the cylindrical blade drum, the cone defining an upper cone aperture and a lower cone aperture having a larger diameter than the upper cone aperture, and a fan blade positioned at or below the lower cone aperture, the fan capable of rotation to force air in an upward vertical direction, an exterior housing assembly surrounding the turbine assembly, and a vertical shaft having a first end and a second end, the first end positioned at or near the turbine assembly and the second end positioned within an alternator/generator in an interior portion of a building, wherein rotation of the cylindrical blade drum causes the alternator/generator to generate electricity.
    Type: Grant
    Filed: November 5, 2010
    Date of Patent: March 22, 2016
    Inventor: Clifford Bassett
  • Patent number: 9057387
    Abstract: A series fan assembly structure includes a first fan frame and a second fan frame. The first fan frame has a first latch section, a second latch section, a first engagement recess, a second engagement recess, a first retainer section and a second retainer section. The second fan frame has a third latch section, a fourth latch section, a third engagement recess, a fourth engagement recess, a third retainer section and a fourth retainer section. The first and second engagement recesses are respectively connected with the third and fourth latch sections, the first and second latch sections are respectively connected with the third and fourth engagement recesses and the first and second retainer sections are respectively connected with the third and fourth retainer sections. Accordingly, the first and second fan frames can be quickly assembled and securely connected in both axial direction and radial direction.
    Type: Grant
    Filed: June 22, 2012
    Date of Patent: June 16, 2015
    Inventors: Sung-Wei Sun, Zuo Zhi, Xiang-Ping Zhang
  • Publication number: 20150147169
    Abstract: A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor vane, has a decreased surface area over a portion of the airfoil chord length. The decreased surface area compressor vane operates in conjunction with a compressor blade having an increased surface area.
    Type: Application
    Filed: November 22, 2013
    Publication date: May 28, 2015
    Inventors: EDWARD LEN MILLER, STEPHEN WAYNE FIEBIGER, WES Carl SMITH, Reiner Jochen Digele, Wilm Philipp Hecker, Andreas Martin Mattheiss
  • Patent number: 9039364
    Abstract: A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.
    Type: Grant
    Filed: June 29, 2011
    Date of Patent: May 26, 2015
    Assignee: United Technologies Corporation
    Inventors: Ioannis Alvanos, Gabriel L. Suciu
  • Publication number: 20150125287
    Abstract: A generator system that includes an engine and an alternator which is driven by the engine to generate electrical power. A radiator is connected to the engine and an axial fan directs air toward the radiator to cool the radiator. A plurality of static vanes is located between the axial fan and the radiator. Each static vane includes an inner end and an outer end, the inner ends of the static vanes being joined together. The static vanes are curved in a plane orthogonal to the rotation axis in order to direct the air towards the axis, thereby counterbalancing the centrifugal forces. The static vanes may be twisted, the pitch angle increasing from 0 degree at hub to ca. 45 degrees at tip. Additionally, each static vane is attached to the shroud via a third member that extends axially, thereby allowing an axial offset between shroud and static vanes.
    Type: Application
    Filed: April 26, 2013
    Publication date: May 7, 2015
    Inventor: Marcel Briand
  • Publication number: 20150118038
    Abstract: A vane pack assembly is provided that can remove the spacers between the upper and lower vane rings to a location outside of the exhaust flow through the vane ring. In particular, the spacers are located within the vanes. Further, the assembly can effectively retain the small blocks used in varying the angle of the vanes on their associated vane pivot posts. A vane pack with such a configuration can use inexpensive parts, eliminate the need for welding of the vane pack and/or simplify the vane pack assembly process. Further, the vane pack can be decoupled from the turbine housing, thereby avoiding problems with differential thermal expansion.
    Type: Application
    Filed: April 11, 2013
    Publication date: April 30, 2015
    Inventor: Daniel N. Ward
  • Publication number: 20150110618
    Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.
    Type: Application
    Filed: October 23, 2013
    Publication date: April 23, 2015
    Applicant: General Electric Company
    Inventors: Alexander Stein, Joe Timothy Brown, Ravichandran Meenakshisundaram
  • Publication number: 20150071777
    Abstract: A turbine stator wheel of a gas turbine with a plurality of stator vanes spaced apart around the circumference is provided. Two adjacent stator vanes form a passage each between the suction side of the one stator vane and the pressure side of the other stator vane starting from the vane trailing edge, which includes a constant passage portion in which the passage has a substantially constant passage cross-section. The constant passage portion has an inlet area and an outlet area. Each stator vane forms on the pressure side a rear area that extends, starting from the vane trailing edge adjoining the constant passage portion as far as the inlet area of the passage portion, and on the pressure-side forms a front area that extends upstream of the rear area. Each stator vane has on the pressure side a convex pressure-side contour.
    Type: Application
    Filed: September 8, 2014
    Publication date: March 12, 2015
    Inventors: Lars WILLER, Knut LEHMANN, Philipp AMTSFELD
  • Publication number: 20150071776
    Abstract: A fan for a motor vehicle includes an impeller formed by multiple blades (3) extending radially from a hub (4), and a base supporting the impeller. The impeller is rotated about an axis of rotation by an actuator means and is positioned inside a hollow cylindrical cavity having the same axis and formed by an axial wall (25) attached to the base. The base includes an upstream front wall (22) extending externally in a radial plane with reference to the axis, and an outer wall (23) extending axially from the front wall (22). The front wall (22) has a protrusion (24) bordering the impeller, with the protrusion extending axially upstream with respect to the plane of the front wall (22). The upstream end of the protrusion is situated further upstream than the upstream end of the blades (3) of the impeller.
    Type: Application
    Filed: March 22, 2013
    Publication date: March 12, 2015
    Inventor: Denis Scouarnec
  • Patent number: 8966755
    Abstract: A disclosed fixture for assembling a stator vane assembly for a gas turbine engine includes an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing and an inner locating ring including a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing. A clamp section includes a clamp portion and a clamp pin that define an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings, and an inner locating section supporting a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings.
    Type: Grant
    Filed: May 30, 2012
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Michael E. McMahon, Steven J. Feigleson, Dennis R. Tremblay
  • Patent number: 8956105
    Abstract: A turbine vane for a gas turbine engine may include a composite airfoil structure. The composite airfoil structure may have an opening. The turbine vane may include a spar. The spar may have a body, which may be disposed within the opening. A standoff structure may be disposed within the opening. In some non-limiting embodiments, a cooling air gap may be defined between the body and an internal surface of the composite airfoil structure.
    Type: Grant
    Filed: December 21, 2009
    Date of Patent: February 17, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Richard C. Uskert, Ted Joseph Freeman, David J. Thomas
  • Patent number: 8939718
    Abstract: A turbocharger has a rotor housing. Said rotor housing has an insertion element. Said insertion element is configured such that the same forms an over-hanging spiral together with said rotor housing.
    Type: Grant
    Filed: July 3, 2009
    Date of Patent: January 27, 2015
    Assignee: Continental Automotive GmbH
    Inventors: Hartmut Claus, Holger Fäth, Andre Kaufmann, Stefan Krauβ
  • Patent number: 8938975
    Abstract: An inner combustion chamber casing of a turbomachine, which is intended to be placed downstream of a centrifugal compressor, is provided. The casing has the shape of a disc, pierced by a central circle, and includes on its disc at least one guide vane of the drawn-off air. The guide vane extends longitudinally over the disc between the periphery of the disc and the central circle and spreads out axially from the disc so as to form with the downstream face of the centrifugal compressor a guide channel for the air which is drawn off upon exit from the said compressor. The guide vane has a curved shape orienting in a radial direction at the level of its most central end.
    Type: Grant
    Filed: June 7, 2011
    Date of Patent: January 27, 2015
    Assignee: SNECMA
    Inventors: Laurent Donatien Behaghel, Frederic Dallaine, Delphine Leroux, Benjamin Philippe Pierre Pegouet
  • Publication number: 20150016986
    Abstract: A stator vane assembly for a compressor of a gas turbine, in particular of an aircraft engine, including a plurality of stator vanes whose airfoil sections form a stagger angle with an axis of rotation of the compressor, which stagger angle varies along a duct height of the stator vane assembly. Along the duct height from the inside to the outside, the stagger angle increases to a local maximum in a second section adjoining a first, radially innermost section, and decreases to an outer local minimum in a third section adjoining this second section and, along the duct height from the inside to the outside, the stagger angle decreases from the initial value to an inner local minimum in the first, radially innermost section and/or increases from the outer local minimum to a final value in a fourth, radially outermost section adjoining the third section.
    Type: Application
    Filed: July 15, 2014
    Publication date: January 15, 2015
    Inventor: Sergio Elorza GOMEZ
  • Publication number: 20150010395
    Abstract: The present application relates to a stator blade sector configured to be fixed to a housing of an axial turbomachine, the sector having a plurality of blades with platforms juxtaposed, so as to describe an arc of a circle. At least one of the platforms comprises on its outer face a fixing screw and at least one other platform has no fixing screws, the platforms being fixed together at their adjacent edges. The application also relates to a stator or portion of stator having a housing forming a generally circular wall and blade sectors arranged along the wall. The housing includes several parts connected to each other by longitudinal flanges. Platforms with no fixing screws are located opposite the flanges.
    Type: Application
    Filed: July 2, 2014
    Publication date: January 8, 2015
    Inventor: Jean-François Cortequisse
  • Publication number: 20150003968
    Abstract: A gas turbine engine includes a compressor section and a nosecone assembly. The compressor section includes an inlet guide vane assembly including an inner shroud, an outer shroud, and an inlet guide vane extending from the inner shroud to the outer shroud. The nosecone assembly is attached to the inner shroud.
    Type: Application
    Filed: December 26, 2013
    Publication date: January 1, 2015
    Inventors: David Maliniak, Daniel J. Monahan, Jonathan D. Little, Veerachari J. Mayachari, Rakesh Sharma N. Dumavath, Arun Kumar Jayasingh, Herbert L. Walker
  • Publication number: 20140360160
    Abstract: Embodiments may provide variable geometry turbine, a nozzle vane for a variable geometry turbine, and a method. The variable geometry turbine that may include a turbine wheel and a plurality of adjustable vanes radially positioned around the turbine wheel. The turbine may also include a flow disrupting feature on one or more outside surfaces of one or more of the plurality of adjustable vanes.
    Type: Application
    Filed: June 11, 2013
    Publication date: December 11, 2014
    Inventors: Harold Huimin Sun, Liangjun Hu, Ben Zhao, Dave R. Hanna
  • Publication number: 20140356157
    Abstract: A wind turbine device may include turbine blades being radially spaced and extending vertically, diverter panels being respectively adjacent and radially outward of the turbine blades, an inner support ring coupled to the turbine blades, and an axle coupled to the turbine blades.
    Type: Application
    Filed: May 23, 2014
    Publication date: December 4, 2014
    Inventors: Rafael D. Mayor, Richard T. Barcia, JR., Michael O'Donnell
  • Publication number: 20140341761
    Abstract: A variable-nozzle turbocharger includes a turbine housing and a center housing, and a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. The vanes extend between the nozzle ring and an opposite wall of the nozzle. An axially floating vane sealing ring is disposed in an annular recess formed in the face of the nozzle ring adjacent proximal ends of the vanes. The vane sealing ring is urged by exhaust gas pressure differential toward the proximal ends of the vanes, and the vanes are thus urged toward the opposite nozzle wall so that distal ends of the vanes are close to or abutting the wall, resulting in a reduction or closing of the gaps at the proximal and distal ends of the vanes.
    Type: Application
    Filed: June 15, 2011
    Publication date: November 20, 2014
    Inventors: Emmanuel Severin, Pierre Barthelet
  • Patent number: 8882439
    Abstract: Embodiments relate to a guiding apparatus, a wind turbine system, and methods related thereto. In an embodiment, a guiding apparatus for guiding a flow of a fluid for use with a rotor, the rotor comprising an annular radial vane assembly surrounding a central space which is enclosed save via the vane assembly and being arranged to rotate about a vertical axis, includes a screening for guiding the fluid to circulate substantially about the vertical axis within the central space in the same direction as the rotor during use, wherein the screening comprises an inner guide array concentrically surrounded by the vane assembly.
    Type: Grant
    Filed: July 19, 2013
    Date of Patent: November 11, 2014
    Inventor: Guy Andrew Vaz
  • Patent number: 8876485
    Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: November 28, 2011
    Date of Patent: November 4, 2014
    Assignee: General Electric Company
    Inventors: Ross James Gustafson, Aaron Gregory Winn
  • Publication number: 20140321975
    Abstract: The invention relates to a wind power station (1) for energy generation with an axial-flow, rotating, vortex-generating wind concentrator (2) pivot-mounted on a shaft (3), covered by a ring-shaped outer jacket (4) which on its outside features flow channels distributed over 360° and which is equipped concentrator blades (7) in a circular arrangement between the shaft (3) and the ring-shaped outer jacket (4). To create favourable conditions, it is proposed to include sawtooth-shaped, curved edge-vortex-generating guide profiles (5) producing a downstream vortex coil across the entire cross-section of the ring-shaped outer jacket (4).
    Type: Application
    Filed: November 16, 2012
    Publication date: October 30, 2014
    Inventor: Gudrun WIESER