Patents Examined by Maxime M Adjagbe
  • Turbine shroud segment having a seal segment perimeter seal with separated buffer cavities
    Patent number: 11286802
    Abstract: A turbine shroud segment of a gas turbine engine includes a carrier segment, a blade track segment, and a plurality of seals arranged between the carrier segment and the blade track segment. The plurality of seals are arranged between the carrier segment and the blade track segment to block gases from passing between the carrier segment and the blade track segment.
    Type: Grant
    Filed: October 9, 2019
    Date of Patent: March 29, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, Aaron D. Sippel, Jeffrey M. Crutchfield, Jeffrey A. Walston
  • Turbine ring assembly having indexed flanges
    Patent number: 11286813
    Abstract: A turbine ring assembly includes ring segments forming a turbine ring and a ring support structure, each segment having a part forming an annular base with, in the radial direction, an inner face and an outer face from which project a first and a second hooking tab, the structure including a shroud from which project a first and a second radial flange between which are retained the first and second tabs, a first annular flange made of one part and a second annular flange disposed upstream of the ring. The first flange includes an annular shoulder and the second flange includes an annular recess forming an axial stop cooperating with the shoulder.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: March 29, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Claude Michel Etienne Danis, Clément Jean Pierre Duffau, Clément Jarrossay, Nicolas Paul Tableau, Lucien Henri Jacques Quennehen
  • Turbomachine with axial force recovery at the fan via pressurized gas feed
    Patent number: 11274554
    Abstract: A turbomachine having a fan shaft supported by a first bearing positioned downstream of the fan, the first bearing including an outer ring attached to an annular support secured to the stator. The turbomachine includes at least one gas feed duct leading into an enclosure positioned against the disc, the gas feed duct being adapted to be fed at a second end with pressurized gas taken from an airstream of a high-pressure compressor of the turbomachine, so that the gas applies an axial force towards upstream on the disc during some operating phases of the turbomachine. The turbomachine further includes a ferrule imperviously sealing the enclosure.
    Type: Grant
    Filed: August 27, 2019
    Date of Patent: March 15, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Michel Gilbert Roland Brault, Julien Fabien Patrick Becoulet, Amelie Argie Antoinette Chassagne, Didier Jean-Louis Yvon
  • Assembly of vane units
    Patent number: 11274561
    Abstract: A vane assembly includes a plurality of vane units and a connecting part. Each vane unit includes a base having a through-hole positioned between opposing longitudinal faces of the base. The connecting part includes a lacing bar that is insertable into and through the through-holes for coupling at least two adjacent vane units into the vane assembly. In the vane assembly the connecting part is arranged through the through holes of the plurality of vane units clamping the vane units on the lacing bar.
    Type: Grant
    Filed: September 17, 2018
    Date of Patent: March 15, 2022
    Assignee: SULZER MANAGEMENT AG
    Inventors: Jozef H. G. Mattheij, Twan Antonius Martinus Althuizen
  • Vane retention feature
    Patent number: 11268393
    Abstract: An airfoil assembly includes an airfoil. The airfoil has first and second platforms and an airfoil between the first and second platforms. A support ring is configured to retain the first platform. The support ring has a lip which extends radially inward from the support ring. The lip is configured to engage an axial face of the first platform. The lip has a primary retention feature and a secondary retention feature. The primary and secondary retention features are configured to retain the first face of the first platform with respect to the annular ring. A support structure for an airfoil and a method of retaining an airfoil assembly are also disclosed.
    Type: Grant
    Filed: November 20, 2019
    Date of Patent: March 8, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Howard J. Liles, Bryan P. Dube, Bryan H. Farrar
  • Intermediate case supporting removable panels fitted with retaining elements
    Patent number: 11261758
    Abstract: An intermediate turbojet case comprises a hub that supports removable panels and bleed lines, the hub comprising a flank provided with openings, each bleed line having an upstream end engaged in an opening in the flank and a downstream end terminated by a base plate through which it is fixed to an internal face of a removable panel by way of screws, each removable panel having a front edge at which it is fixed to an external lip of the hub by screws. At least one removable panel comprises a downstream edge supporting a retaining element close to the internal face to hold the base plate in contact with the internal face during a phase in which the removable panel is fixed to the hub by screwing, this phase preceding attachment of the base plate to the removable panel by screwing.
    Type: Grant
    Filed: March 31, 2020
    Date of Patent: March 1, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Frédéric Jacques Eugène Goupil, Rémi Abarrou, Azath Mohamed
  • Impingement cooling arrangement for airfoils
    Patent number: 11255197
    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.
    Type: Grant
    Filed: January 6, 2020
    Date of Patent: February 22, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jason Shenny, Jeffrey T. Morton, Alberto A. Mateo, San Quach, Gregory Anselmi
  • Multi-piece carrier assembly for mounting ceramic matrix composite seal segments
    Patent number: 11255211
    Abstract: A turbine shroud assembly adapted for use in a gas turbine engine includes a blade track segment and a carrier. The blade track segment includes a runner that extends circumferentially partway around a central axis and an attachment post that extends radially from the runner. The carrier is coupled with the attachment post to support the blade track segment relative to the central axis.
    Type: Grant
    Filed: November 10, 2020
    Date of Patent: February 22, 2022
    Assignees: Rolls-Royce Corporation
    Inventors: Jeffrey A. Walston, Andrew Hurst
  • Shroud assembly for centrifugal compressor and method
    Patent number: 11255213
    Abstract: The centrifugal compressor can have a shroud engaged to a case via a plurality of circumferentially interspaced slots and lugs, the slots extending in at least one of a radial direction and an axial direction relative to a rotation axis of the compressor, the lugs slidingly received in a corresponding slot and configured for sliding in the slot in response to thermal growth of the case relative to the shroud.
    Type: Grant
    Filed: July 15, 2019
    Date of Patent: February 22, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Dave Menheere
  • Aluminum airfoil
    Patent number: 11231046
    Abstract: An airfoil includes a first airfoil piece and a second airfoil piece that is bonded to the first airfoil piece at a joint. The first airfoil piece and the second airfoil piece are formed of aluminum alloys. At least one of the aluminum alloys is an aluminum alloy composition that has greater than 0.8% by weight of zinc. The joint includes a braze element of magnesium, zinc, or combinations thereof in a higher concentration than in other portions of the first airfoil piece and the second airfoil piece.
    Type: Grant
    Filed: March 17, 2020
    Date of Patent: January 25, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Thomas J. Watson, Daniel A. Bales
  • Turbine shroud assembly with dovetail retention system
    Patent number: 11230937
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier. The turbine outer case is arranged circumferentially around an axis. The blade track segment includes an arcuate runner that extends circumferentially partway around the axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner. The carrier is configured to couple the blade track segment to the turbine outer case.
    Type: Grant
    Filed: May 18, 2020
    Date of Patent: January 25, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, Alexandra Baucco, Anthony Razzell, Michael J. Whittle, Jeffrey Crutchfield
  • Assembly with pin-mounted ceramic matrix composite material components
    Patent number: 11220930
    Abstract: A turbine shroud assembly includes a carrier, a blade track segment, and an attachment pin. The carrier is arranged to extend circumferentially at least partway around an axis. The blade track segment includes a runner that faces the axis to define a portion of a primary gas path of the gas turbine engine and an attachment flange that extends radially away from the runner. The attachment pin is configured to mount the blade track segment to the carrier.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: January 11, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Shaling Starr, Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Gas turbine engine rotor balancing
    Patent number: 11215055
    Abstract: A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.
    Type: Grant
    Filed: February 13, 2020
    Date of Patent: January 4, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Paul Stone
  • Turbine shroud assembly with ceramic matrix composite components having stress-reduced pin attachment
    Patent number: 11215065
    Abstract: A turbine shroud assembly is adapted to extend around a turbine wheel mounted for rotation about a central reference axis of a gas turbine engine. The turbine shroud assembly includes a carrier segment made from metallic materials and a blade track segment made from ceramic matrix composite materials. The carrier extends at least partway about the axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: April 24, 2020
    Date of Patent: January 4, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Shaling H. Starr, Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Static seal arrangement and turbomachine
    Patent number: 11208908
    Abstract: Disclosed is a static seal arrangement for sealing a gap between a first static component and a second static component of a turbomachine such as an aircraft engine or a static gas turbine, having a brush seal held distant from a hot gas, this brush seal being arranged standing or vertical with its clamping section that can be surrounded by cooling air in a radially outer clamping space relative to the gap, and forming a radial sealing site with the first component and an axial sealing site with the second component; also disclosed is a turbomachine.
    Type: Grant
    Filed: December 5, 2019
    Date of Patent: December 28, 2021
    Assignee: MTU Aero Engines AG
    Inventors: Manfred Feldmann, Simon Schmalfuss
  • Turbine shroud ring segments with ceramic matrix composite components
    Patent number: 11208911
    Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: April 23, 2020
    Date of Patent: December 28, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Keith Sadler, Ted J. Freeman, Aaron D. Sippel, Alexandra Baucco
  • Boundary layer turbomachine
    Patent number: 11208890
    Abstract: A boundary layer turbomachine can include a housing defining an interior space and having an inlet opening and an outlet opening to facilitate movement of a fluid through the housing. The boundary layer turbomachine can also include a rotor assembly disposed in the rotor chamber and configured to rotate about an axis of rotation. The rotor assembly can have a plurality of disks spaced apart along the axis of rotation and defining an interior opening along the axis of rotation. The fluid can pass through gaps between the disks and the interior opening as the fluid moves through the housing.
    Type: Grant
    Filed: January 8, 2016
    Date of Patent: December 28, 2021
    Inventors: Billy W. Helton, Mark W. Jones
  • Connection between a ceramic matrix composite stator sector and a metallic support of a turbomachine turbine
    Patent number: 11208906
    Abstract: A turbine of a turbomachine includes a ceramic matrix composite sector of a stator includes an outer platform and an inner platform connected via at least one vane. The outer platform has means for attaching to a sector of a metallic support, the attachment means having at least one central rim and two lateral rims. The central rim is radially offset with respect to said lateral rims along a directrix line such that the central rim is radially on one side of said directrix line and the lateral rims on the other. The central rim and said central hook bear radially against one another and are located radially on either side of said directrix line. The lateral rim and said corresponding lateral hook bear radially against one another and are located radially on either side of said directrix line.
    Type: Grant
    Filed: December 3, 2018
    Date of Patent: December 28, 2021
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN HELICOPTER ENGINES
    Inventors: Nicolas Paul Tableau, Sébastien Serge Francis Congratel, Lucien Henri Jacques Quennehen, Gilles Gérard Claude Lepretre, Denis Daniel Jean Boisseleau
  • Linear pump control
    Patent number: 11199194
    Abstract: A demand-based load balancing function may be provided by one or more drive controllers that takes advantage of the affinity laws to linearize the control of the variable of interest (e.g., flow, pressure, etc.). Each drive controller may be set up by the user simply inputting a few values into the drive controller. Based on the inputs, the drive controllers may interpolate control points using an assumed linear relationship between the variable to be controlled (e.g., pressure) and the current driven to the pump. Feedback data from the system may be used to continually update the drive controllers so as to potentially allow them to better balance power usage to each pump.
    Type: Grant
    Filed: March 12, 2019
    Date of Patent: December 14, 2021
    Assignee: Toshiba International Corporation
    Inventors: Kurt Allen Bihler, David Liu, Mark Douglas Rayner
  • Turbine shroud assembly with hangers for ceramic matrix composite material seal segments
    Patent number: 11187098
    Abstract: An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a supported component, illustratively used as a heat shield. The assembly includes a mounting system for coupling the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.
    Type: Grant
    Filed: December 20, 2019
    Date of Patent: November 30, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.
    Inventors: David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel, Daniel K. Vetters, Alexandra Baucco, Jeffrey M. Crutchfield