Patents Examined by Dwayne J. White
  • Patent number: 10077782
    Abstract: A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing, elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing, elements have thermal properties sufficiently different to allow relative growth and geometric properties strategically selected to strategically form an interface gap therebetween (42) resulting in blade tip gaps that are dynamically adjusted operation.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: September 18, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Jiping Zhang, Barton M. Pepperman
  • Patent number: 10077757
    Abstract: A rotor blade of a wind power installation for fixing to a rotor hub and having a rotor blade longitudinal axis, including a rotor blade inner part towards the rotor hub, and a rotor blade outer part away from the rotor hub, wherein the rotor blade inner part and the rotor blade outer part are connected together by means of at least one connecting device and the connecting device includes at least one anchoring element anchored in the rotor blade outer part, at least one counterpart element anchored in the rotor blade inner part, and at least one connecting bolt which extends through the counterpart element and is fixed in the anchoring element.
    Type: Grant
    Filed: November 28, 2012
    Date of Patent: September 18, 2018
    Assignee: Wobben Properties GmbH
    Inventors: Johannes Kannenberg, Alexander Hoffmann
  • Patent number: 10072525
    Abstract: A gas turbine engine comprising a casing, a bonding patch (10, 22) bonded to a surface of the casing, and a liner attached to the bonding patch. The bonding patch (10, 22) comprising a bonding region (12) configured to receive an adhesive for bonding the patch (10, 22) to a surface. A plurality of de-bonding elements (16) is configured to be movable relative to the bonding region (12) in response to an energizing signal.
    Type: Grant
    Filed: August 20, 2015
    Date of Patent: September 11, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Christopher Benson
  • Patent number: 10072715
    Abstract: A yaw brake mechanism is described for maintaining a yawing structure, such as a nacelle of a fluid turbine, at a desired orientation or azimuthal heading about a reference or yaw axis. The yaw brake mechanism uses one or more rotor locks and one or more receptacles that cooperate with one another to achieve the locking function. One of the rotor locks is actuatable so that a portion thereof can be engaged in one of the receptacles to lock the yawing structure. The number of rotor locks and receptacles can be selected to allow the yawing structure to achieve any azimuth heading around the full 360 degrees of the yaw axis with various degrees of accuracy. The yaw brake mechanism allows the yawing structure to maintain multiple headings while being subjected to extreme moment and force loads in a low mass, low height, low cost solution.
    Type: Grant
    Filed: February 24, 2015
    Date of Patent: September 11, 2018
    Assignee: Lockheed Martin Corporation
    Inventors: Stephen Firkser, Thomas E. McGuigan
  • Patent number: 10066500
    Abstract: A system comprising a discharge valve that allows some of the fluid generated by a fluid generating source and intended for a drive torque generating member for a rotary element of a mechanical device to be removed so as to limit the corresponding rotational speed, this being done for a length of time that allows a thermal gradient to be reduced sufficiently that a phenomenon of deformation of said rotary element can be prevented.
    Type: Grant
    Filed: June 5, 2014
    Date of Patent: September 4, 2018
    Assignees: AIRBUS OPERATIONS SAS, AIRBUS SAS
    Inventors: Alexis Manneville, Norbert Hirtz, Valentin Theard
  • Patent number: 10066486
    Abstract: A method for designing a turbine having a plurality of stages disposed axially one behind the other in the direction of flow through the turbine, each stage being formed of a stationary row of a plurality of stator vanes and a rotating row of a plurality of rotor blades. The row of rotor blades of at least one of these stages has a plurality of rotor blade clusters each formed of at least two rotor blades (A1, B1; A2, B2) having different airfoil profiles and/or different distances (?A, ?B) from adjacent rotor blades following in the direction of rotation. A vane-to-blade-cluster ratio (V/(B/P)) parameter indicates the ratio of the number of stator vanes (V) to the quotient (B/P) of the number of rotor blades (B) of the stage divided by the number of rotor blades per rotor blade cluster (P).
    Type: Grant
    Filed: March 13, 2015
    Date of Patent: September 4, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Dominik Broszat, Nicolas Thouault
  • Patent number: 10054055
    Abstract: A platform is disclosed. The platform may include an airfoil section with a cooling passage and a platform. The platform may have various cooling features, such as a platform cooling apparatus. The platform cooling apparatus may have a cooling passage forming a channel disposed at least partially through the platform and the platform cooling apparatus may have an inflow channel in fluidic communication with the channel and the cooling passage so that cooling air may travel from the cooling cavity of the blade airfoil section and into the platform cooling apparatus. Moreover, the platform cooling apparatus may have a cooling cover apparatus at least partially fluidically sealing the platform cooling apparatus.
    Type: Grant
    Filed: November 19, 2015
    Date of Patent: August 21, 2018
    Assignee: United Technology Corporation
    Inventors: Brandon W. Spangler, Edward F. Pietraszkiewicz
  • Patent number: 10053997
    Abstract: A gas turbine engine comprising in axial flow series: a fan having a fan rotor; a series passages defined between adjacent outlet guide vanes for guiding flow from the fan; and a bifurcation. The gas turbine engine further comprises a substantially annular fluid passageway extending from the fan to the bifurcation, the outlet guide vanes being positioned within the passageway. The passageway includes a profiled region.
    Type: Grant
    Filed: October 13, 2015
    Date of Patent: August 21, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Stephane Michel Marcel Baralon
  • Patent number: 10047765
    Abstract: A bushing for use in a stator vane assembly that includes an annular body that extends between a first end and a second end. The bushing is configured to be removable from the stator vane assembly without disassembly of the stator vane assembly.
    Type: Grant
    Filed: December 3, 2014
    Date of Patent: August 14, 2018
    Assignee: General Electric Company
    Inventors: Aaron David Williamson, Harry McFarland Jarrett, Jr.
  • Patent number: 10041357
    Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: August 7, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Benjamin F. Hagan, Ryan Alan Waite, Bryan P. Dube, Dominic J. Mongillo, Jr.
  • Patent number: 10041474
    Abstract: A wind turbine system may be configured with at least one wind turbine having an exterior surface. A distribution pipe positioned between the exterior surface and a drag feature with the drag feature connected to the exterior surface via at least one attachment feature. At least one nozzle can continuously extend from the distribution pipe through the drag feature. A controller connected to the distribution pipe may selectively activate the at least one nozzle to eject compressed fluids from the turbine blade to modify a preexisting radial velocity of the at least one turbine blade.
    Type: Grant
    Filed: February 23, 2015
    Date of Patent: August 7, 2018
    Inventor: Larry Jeffus
  • Patent number: 10041371
    Abstract: A robotically articulated inspection scope (56, 69) inserted into a pilot fuel nozzle port (58) of a turbine engine (20) for in-situ measurement of gaps (59) between tips of turbine blades (40A) and the surrounding shroud (44). A non-contact gap measuring device (52) on a distal end (79) of the scope may be navigated through a combustor (28) and transition duct (34) into a position proximate a blade tip gap. The scope may be controlled via computer (68) via a robotic drive (66) affixed to the pilot fuel nozzle port. Multiple scopes may be used to measure gaps (59A-D) at multiple azimuths of the turbine simultaneously. The turbine disk (37) may be rotated on its operating turning gear to sequentially measure each blade at each azimuth. The computer may memorize an interactively navigated path for subsequent automated positioning.
    Type: Grant
    Filed: February 6, 2015
    Date of Patent: August 7, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Joshua DeAscanis, David Letter, Alejandro Bancalari, Clifford Hatcher, Jr.
  • Patent number: 10036277
    Abstract: A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connected to the metal part by an axial connection and a second fixing portion connected to the composite part by an axial connection, the connecting element including an axially extending free end; and a rigid locking element including a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the connecting element to limit deformation of the connecting element while the engine is in operation.
    Type: Grant
    Filed: June 12, 2013
    Date of Patent: July 31, 2018
    Assignee: SNECMA
    Inventors: Antoine Jean-Philippe Beaujard, Jacques Rene Bart
  • Patent number: 10036273
    Abstract: A bleed valve for a gas turbine engine, the bleed valve comprising: an inlet coupled to an air source; and an outlet coupled to an air sink. The bleed valve also comprises a first stage of flow area modulation between the inlet and the outlet. Also a second stage of flow area modulation between the first stage and the outlet. The pressure can be equalized between the first and second stages. There is also an arrangement comprising a plurality of bleed valves and a controller to control the flow areas of at least one of the first and second stages of each bleed valve.
    Type: Grant
    Filed: October 13, 2015
    Date of Patent: July 31, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Michael Georg Kozuch, Zahid Muhammad Hussain, Kevin Mark Britchford
  • Patent number: 10029781
    Abstract: Shape memory alloy-actuated propeller blades and shape memory alloy-actuated propeller assemblies are disclosed. An example propeller blade includes a propeller body, a plate coupled to the propeller body, a torque transfer member, and a shape memory alloy (SMA) actuator. The torque transfer member has a distal end attached to the plate such that the torque transfer member applies to the plate at least a portion of a torque applied to the torque transfer member at a proximal end of the torque transfer member. The SMA actuator has a distal end and a proximal end. The distal end of the SMA actuator is attached to the torque transfer member. The proximal end of the SMA actuator is coupled to the propeller body such that the distal end is mated to the propeller body. The SMA actuator is configured to apply the torque to the proximal end of the torque transfer member in response to an application of heat to the SMA actuator.
    Type: Grant
    Filed: August 3, 2015
    Date of Patent: July 24, 2018
    Assignee: The Boeing Company
    Inventors: William J. Bigbee-Hansen, Dan J. Clingman, James H. Mabe
  • Patent number: 10029336
    Abstract: A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor.
    Type: Grant
    Filed: November 5, 2015
    Date of Patent: July 24, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Anthony R. Bifulco, Damon K. Brown, Nicholas Aiello
  • Patent number: 10024234
    Abstract: An aircraft gas turbine with a fan disk on which are fastened fan blades spread over the circumference and forming an intermediate space with one another, with a sealing disk arranged at the rear of the fan disk and with an inlet cone mounted at the front of the fan disk, as well as with filler elements arranged in the intermediate spaces, where the sealing disk has an annular groove and where the filler elements are at the rear inserted into the annular groove and at the front held underneath a rim area of the inlet cone, characterized in that the filler elements are designed as bending beams and that on the radially inner side of the filler element at least one rib-like reinforcing area is provided, extending in the axial direction and longitudinally to the filler element.
    Type: Grant
    Filed: September 11, 2015
    Date of Patent: July 17, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Pierangelo DuĆ³, Karl Schreiber
  • Patent number: 10018048
    Abstract: Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.
    Type: Grant
    Filed: December 16, 2013
    Date of Patent: July 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Andrew G. Alarcon, Christopher M. Quinn, James Glaspey, Matthew A. Turner
  • Patent number: 10006372
    Abstract: A ventilation inlet including a conduit (104) arranged to convey flow from a first flow zone to a second flow zone. The conduit has a mouth region (106) presenting to the first flow zone an entrance aperture to receive the flow therefrom. The conduit has a baffle (114) spanning a portion of the conduit to define a throat region (116), the throat region being narrower than the entrance aperture. The throat region (116) is movable along the conduit (104) to control the flow through the ventilation inlet.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: June 26, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Zahid M Hussain, Nityabh Mishra, Peter T Ireland
  • Patent number: 10001132
    Abstract: An axially split pump for conveying a fluid has an axially split housing that includes a bottom part and a cover. The bottom part has a first sealing surface and the cover has a second sealing surface, the bottom part and the cover being fastened so that the two sealing surfaces have direct contact. A first sealing groove for the reception of a first string-like sealing element is in the sealing surfaces, and a second sealing groove is provided for the reception of a second string-like element, the second sealing groove being connected to the first sealing groove via an opening. A connection element is in the opening that has two lateral cut-outs respectively for the reception of a one of the string-like sealing elements. The cut-outs are arranged and configured so that the two string-like sealing elements run substantially in parallel in the region of the connection element.
    Type: Grant
    Filed: November 19, 2015
    Date of Patent: June 19, 2018
    Assignee: SULZER MANAGEMENT AG
    Inventors: Thomas Welschinger, Heike Tischler, Berthold Vogel