Patents Examined by Carlos A Rivera
  • Patent number: 10612403
    Abstract: A sliding joint in a gas turbine engine between a large exit duct of a combustor and a turbine vane assembly having a leading edge lug. The sliding joint has an elongated flexible arm extending between a first end joined to the outer surface of the large entry duct, and an opposed free second end disposed radially inward of the outer surface of the large entry duct. A spacer is joined to the second end of the arm and projects radially away therefrom toward the outer surface of the large entry duct. The spacer is spaced apart from the outer surface and defines a gap therebetween. The spacer, the arm, and the sliding joint axially displace with respect to the lug upon thermal expansion of the large entry duct.
    Type: Grant
    Filed: August 7, 2014
    Date of Patent: April 7, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza Stastny, Robert Sze
  • Patent number: 10612782
    Abstract: Nozzle for engine has coaxial arrangement of inner pilot and outer mains airblast fuel injectors and intermediate air-swirler passage sandwiched between the outer and inner air-swirler passages of the pilot and mains airblast fuel injectors, respectively. The nozzle has an annular first-splitter wall separating the pilot outer air-swirler passage from the intermediate one. An outer surface profile of the first-splitter wall defines radially inner side of the intermediate air-swirler passage. The nozzle has an annular second-splitter wall separating the intermediate air-swirler passage from mains inner air-swirler passage. An inner surface profile of second-splitter wall defines radially outer side of intermediate air-swirler passage. The outer and inner surface profile of the first and second splitters walls, respectively, have convergent sections facing each other forming convergent portion of the intermediate air-swirler passage.
    Type: Grant
    Filed: January 24, 2018
    Date of Patent: April 7, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Ian James Toon, Robert Anthony Hicks
  • Patent number: 10605086
    Abstract: A vane assembly includes first and second annular metal rings configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion. The assembly further includes a ceramic matrix composite vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring.
    Type: Grant
    Filed: November 20, 2012
    Date of Patent: March 31, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: George E. Zurmehly, Milton Ortiz, Kin Poon, Michael Vinup, Ardeshir Riahi
  • Patent number: 10598041
    Abstract: A performance measurement system of an inlet of a gas turbine engine includes a probe strut configured for installation to a case strut of an inlet case of a gas turbine engine. The probe strut includes one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes, a first attachment point configured to secure the probe strut to a hub portion of the inlet case, and a second attachment point configured to secure the probe strut to an outer case portion of the inlet case. A data acquisition module is located at a central longitudinal axis of the inlet and is operably connected to the probe to collect sensed data therefrom. The probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.
    Type: Grant
    Filed: October 20, 2017
    Date of Patent: March 24, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: William W. Rice, Alfred F. Covino, Richard C. Hendricks, Douglas H. Thomesen, Bryan J. Hackett
  • Patent number: 10598378
    Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a combustion chamber. The heat shield is connected to the shell by a bonded connection, and defines a portion of the combustion chamber. A cooling cavity is defined between the shell and the heat shield.
    Type: Grant
    Filed: October 7, 2014
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Gary D. Roberge, Grant O. Cook, III
  • Patent number: 10590856
    Abstract: A gas turbine engine including a compressor, a turbine having one or more stages and a combustor, the combustor being located between the compressor and turbine. The gas turbine engine further includes a bleed from a core defined by a core duct, the core duct surrounding and extending between the turbine and combustor at least. The bleed includes at least one inlet located downstream of the combustor and upstream of at least one of the turbine stages. The turbine is arranged in use to drive the compressor. The bleed is arranged to be controllable in use to selectively bleed air from the core through the inlet and to thereby control the power delivered by the turbine to the compressor.
    Type: Grant
    Filed: July 13, 2015
    Date of Patent: March 17, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventor: Nicholas Howarth
  • Patent number: 10577957
    Abstract: An aft frame assembly for a gas turbine transition piece has a main body with an upstream facing surface and downstream facing surface. Feed hole inlets are located on the upstream facing surface, and each feed hole inlet is coupled to a cooling channel that passes through the main body towards the downstream facing surface. Plenums are located in or near the downstream facing surface. Each cooling channel is connected to and terminates in a plenum. Microchannels are formed in or near the downstream facing surface, and each microchannel is connected to a plenum. The cooling channels are configured as inputs and the microchannels are configured as outputs of the plenums. Two or more of the cooling channels and two or more of the microchannels are connected to one plenum. Exit channels are connected to the microchannels, and exhaust flow out of an upstream facing surface of a seal slot.
    Type: Grant
    Filed: October 13, 2017
    Date of Patent: March 3, 2020
    Assignee: General Electric Company
    Inventors: Charles Lewis Davis, III, David Kenton Felling
  • Patent number: 10578305
    Abstract: A burner assembly with a combustion chamber, a plurality of mixing ducts leading into the combustion chamber, where combustion air and introduced fuel are mixed. The mixing ducts are formed by mixing tubes extending axially through an annular space between a tubular outer wall, a tubular inner wall arranged radially at a distance from the outer wall, a ring-shaped end plate arranged upstream and a ring-shaped end plate arranged downstream. The end plates have through-openings, which accommodate and/or extend the mixing tubes, and the end plates have, both radially inside and outside, a circumferential edge extending in the direction of the annular space, with axial bores in the edge of the ring-shaped end plate arranged downstream. The axial bores extend from the annual space into the end plate, and at least one opening is for removing cooling air, the opening branching from the axial bore.
    Type: Grant
    Filed: October 29, 2015
    Date of Patent: March 3, 2020
    Assignee: Siemens Aktiengesellschaft
    Inventors: Olga Deiss, Thomas Grieb, Patrick Lapp, Jens Kleinfeld, Matthias Chlebowski, Fabian Sander, Christian Beck, Andreas Böttcher, Patrick Ronald Flohr, Thomas Hauser, Simon Purschke, Günther Walz
  • Patent number: 10571127
    Abstract: The gas turbine combustor includes a swirler lip on the air hole plate periphery, protruding toward a chamber, and a spring seal in an area for fitting the liner and the plate/lip. The spring seal has an air hole for passage of part of the combustion air introduced in the gap between the outer periphery of the air hole plate and the liner. The swirler lip has an air hole which introduces part of the combustion air passing through the spring seal air hole into the chamber. The liner has an air hole facing the spring seal air hole, to introduce part of air from outside the liner into the gap between the outer periphery of the air hole plate and the liner. A turn guide for rectifying a combustion air flow is provided at the liner end portion on the side for fitting the liner and air hole plate.
    Type: Grant
    Filed: October 23, 2017
    Date of Patent: February 25, 2020
    Assignee: Mitsubishi Hitachi Power Sytems, Ltd.
    Inventors: Keisuke Miura, Yasuhiro Akiyama, Tomohiro Asai, Kazuki Abe, Mitsuhiro Karishuku, Satoshi Dodo, Akinori Hayashi, Yoshitaka Hirata, Noboru Okuyama
  • Patent number: 10570824
    Abstract: A system is provided for a turbine engine. This turbine engine system includes a rotating assembly, a bearing and a lubrication system. The bearing is configured with the rotating assembly. The lubrication system is configured to lubricate the bearing. The lubrication system includes a lubricant pump and a lubricant reservoir. The lubricant pump is mechanically coupled with and driven by the rotating assembly. The lubricant pump is configured with the lubricant reservoir so as to be at least partially submersed in lubricant contained within the lubricant reservoir.
    Type: Grant
    Filed: November 23, 2015
    Date of Patent: February 25, 2020
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Michael E. McCune
  • Patent number: 10563593
    Abstract: A method of extracting work from a convertible gas turbine engine having a core flowpath and a bypass flowpath. The method comprises operating the convertible gas turbine engine at a first volumetric flow rate through the core flowpath and a second volumetric flow rate through the bypass flowpath to produce a first work output of the convertible gas turbine engine; extracting the first work output via an unshrouded fan and a shaft at a first fan to shaft extraction ratio; altering the second volumetric flowrate through the bypass flowpath while maintaining the first work output; and extracting the first work output via an unshrouded fan and a shaft at a second fan to shaft extraction ratio.
    Type: Grant
    Filed: January 4, 2016
    Date of Patent: February 18, 2020
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC.
    Inventors: Charles L. McNeil, John Kusnierek
  • Patent number: 10563579
    Abstract: An air-inlet duct includes a particle separator and an agglomerator. The particle separator is configured to receive atmospheric air laden with particles and to direct the particles into a scavenge passageway while allowing the atmospheric air to move into a compressor passageway thereby reducing the number of particles that enter the compressor passageway. The agglomerator is configured to cause the particles to be attracted to one another and cluster together.
    Type: Grant
    Filed: October 13, 2016
    Date of Patent: February 18, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Robert T. Duge, Crawford F. Smith, III
  • Patent number: 10563530
    Abstract: An intershaft seal assembly including first and second or forward and aft carbon face seal rings supported on an annular housing and having first and second seal faces facing in opposite directions. Forward and aft springs operably disposed between housing and carbon face seal rings for biasing or urging carbon face seal rings in opposite directions. Annular forward and aft carriers mounted on and supported by annular housing and supporting carbon face seal rings. Forward and aft springs operably disposed between housing and the forward and aft carriers respectively. The springs may be wave springs. Inner and outer secondary seals may include inner and outer O rings disposed in annular inner and outer grooves in annular inner and outer surfaces in housing respectively and in sealing engagement with the forward and aft carriers. Carriers may be integral with carbon face seal rings in monolithic combined seal and carrier elements.
    Type: Grant
    Filed: October 12, 2015
    Date of Patent: February 18, 2020
    Assignee: General Electric Company
    Inventor: Mark Gregory Wotzak
  • Patent number: 10557475
    Abstract: In a rotor for a fluid pump which is made radially-compressible and expandable and has a hub (4) and at least one conveying element (10, 11, 19, 20) which has a plurality of struts (12, 13, 14, 15, 16, 21, 22, 27, 28) and at least one membrane (18) which can be spanned between them, provision is made for a design in accordance with the invention which is as simple and inexpensive as possible that at least one first group of struts is pivotable in a pivot plane, starting from a common base, and can thus be spanned open in the manner of a fan, wherein the conveying element lies along the hub and contacts it over its full length in the expanded state to avoid a pressure loss at the margin of the conveying element between it and the hub and thus to realize an optimum efficiency.
    Type: Grant
    Filed: January 12, 2018
    Date of Patent: February 11, 2020
    Assignee: ECP ENTWICKLUNGSGESELLSCHAFT MBH
    Inventor: Daniel Roehn
  • Patent number: 10557368
    Abstract: An active clearance control system of a gas turbine engine includes a radially adjustable blade outer air seal system movable between a radially contracted Blade Outer Air Seal (BOAS) position that defines a first air volume and a radially expanded Blade Outer Air Seal (BOAS) position that defines a second air volume, the second air volume different than the first air volume. An accumulator system accommodate a difference in air volume between the first air volume and the second air volume.
    Type: Grant
    Filed: February 6, 2014
    Date of Patent: February 11, 2020
    Assignee: United Technologies Corporation
    Inventors: Ken F. Blaney, Todd M. LaPierre
  • Patent number: 10550729
    Abstract: A gas turbine exhaust diffuser is configured to be at least partially disposed within an exhaust collector. The diffuser also includes an inner wall configured to extend to a back wall of the exhaust collector, an outer wall circumferentially disposed about the inner wall along a portion of the collector, and an inlet between the upstream end of the inner and outer walls. The inlet is configured to receive an exhaust flow from a gas turbine engine. An outlet for the exhaust is located between the inner wall and a downstream end of the outer wall. The outer wall is asymmetrically shaped so that an opening between the outlet and the back wall of the exhaust collector is larger on a first lateral side of the diffuser adjacent an exhaust exit of the collector than an opposite lateral side of the diffuser.
    Type: Grant
    Filed: February 22, 2017
    Date of Patent: February 4, 2020
    Assignee: General Electric Company
    Inventors: Przemyslaw Sebastian Drezek, Marcin Rafal Abramowicz, Fernando Lopez Parra, Balakrishnan Ponnuraj
  • Patent number: 10550705
    Abstract: A turbine housing assembly seal can include a cylindrical portion that defines an opening having an axis where the cylindrical portion is disposed at a cylinder radius from the axis; a lower edge disposed at a lower edge radius that exceeds the cylinder radius; an sloped annular portion that extends radially inwardly from the lower edge; a lower bend that extends from the sloped annular portion to a lower axial position of the cylindrical portion; an upper bend that extends from an upper axial position of the cylindrical portion; and an upper edge that extends radially outwardly from the upper bend to an upper edge radius that exceeds the cylinder radius and that is less than the lower edge radius.
    Type: Grant
    Filed: December 10, 2014
    Date of Patent: February 4, 2020
    Assignee: Garrett Transportation I Inc.
    Inventors: Shankar Pandurangasa Solanki, Pierre Barthelet, Arnaud Gerard, Vincent Eumont, Nicolas Morand, Francis Abel
  • Patent number: 10550709
    Abstract: A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.
    Type: Grant
    Filed: April 1, 2016
    Date of Patent: February 4, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce plc, Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Steven M. Hillier, Peter Broadhead, Joseph Doyle, Michael Jacquinto, Wesley Thibault, Jun Shi, Roderick Townes
  • Patent number: 10544808
    Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism operable to move between an open position and a closed position. The inlet-adjustment mechanism includes a plurality of blades disposed about the compressor air inlet and located within an annular space within the air inlet wall. The blades are pivotable about respective pivot points such that the blades extend radially inward from the annular space into the air inlet when the blades are in the closed position so as to form an orifice of reduced diameter relative to a nominal diameter of the inlet. Downstream surfaces of the blades include vortex reducers that are structured and arranged to reduce a strength of an unsteady vortex generated from the radially inner edges of the blades.
    Type: Grant
    Filed: February 28, 2018
    Date of Patent: January 28, 2020
    Assignee: Garrett Transportation I Inc.
    Inventors: Hani Mohtar, Stephane Pees, Stephane Doise, Alain Lombard
  • Patent number: 10544692
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: January 28, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Guillaume Jochen Scholl, Pierre Hervé Fernand Marche, Thomas Michel Julien Mervant, Ludovic Pintat, Renaud Gabriel Constant Royan