Patents Examined by Christopher Verdier
  • Trailing edge cooling for a turbine blade
    Patent number: 11208901
    Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.
    Type: Grant
    Filed: May 28, 2019
    Date of Patent: December 28, 2021
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Zachary Daniel Webster
  • Cooling assembly for a turbine assembly
    Patent number: 11208899
    Abstract: A cooling assembly comprises a pin disposed inside a first chamber of an airfoil. The first chamber is disposed inside the tip end comprising a tip floor. The pin extends from a first end to a second end along a pin axis. The first end is coupled with a first surface of the first chamber and the second end is coupled with an inner floor surface of the tip floor such that the pin increases a structural load support level of the tip floor. A cooling conduit is placed inside the pin through which coolant flows. The cooling conduit is elongated along and extends around a conduit axis and is fluidly coupled with conduit channels disposed between the first and second ends of the pin. The conduit channels direct coolant out of the cooling conduit or direct coolant into the cooling conduit.
    Type: Grant
    Filed: March 14, 2018
    Date of Patent: December 28, 2021
    Assignee: General Electric Company
    Inventors: Thomas Earl Dyson, Nicholas William Rathay, Gustavo Ledezma
  • Turbomachine blade with trailing edge having improved cooling
    Patent number: 11199100
    Abstract: A turbine blade includes a root and an airfoil extending from a base, through which it is connected to the root, to a tip. The airfoil includes an intrados wall and an extrados wall, connected by a leading edge and by a trailing edge with a cooling circuit. The cooling circuit includes a conduit with a duct and a manifold prolonging this conduit. The conduit collects air from the blade root to supply the duct and the manifold that is located downstream from the duct and that supplies the slits in the trailing edge with air. The duct supplies air to one end of the manifold close to the tip. The manifold is separated from the duct by a partition including a portion close to the tip that is curved to be concave when seen from the trailing edge.
    Type: Grant
    Filed: May 15, 2020
    Date of Patent: December 14, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Léandre Ostino, Vianney Simon, Vincent Keciyan
  • Blade containment device
    Patent number: 11199106
    Abstract: A shroud having an annular member extending along an axis from a first end to a second end. The annular member has an inside surface radially inward from an outside surface that diverges from the first end towards the second end relative to the axis. The shroud further includes a flange that extends radially outward from the outside surface and a recess, each located at the second end. The recess extends radially outward from the inside surface and circumferentially about the axis. An axial extent of the recess at least partially coincides with an axial extent of the flange.
    Type: Grant
    Filed: August 21, 2020
    Date of Patent: December 14, 2021
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Yiwei Jiang, Michael D. Schelonka, Erik D. LeBeau
  • Turbine vane assembly having ceramic matrix composite components with sliding support
    Patent number: 11193381
    Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.
    Type: Grant
    Filed: May 17, 2019
    Date of Patent: December 7, 2021
    Inventor: Michael J. Whittle
  • Turbine section assembly with ceramic matrix composite vane
    Patent number: 11193393
    Abstract: A turbine assembly adapted for use in a gas turbine engine with a turbine vane comprising ceramic matrix composite materials. The turbine vane is configured to redirect air moving through a primary gas path of the gas turbine engine. The turbine assembly includes a vane-stage support for holding the turbine vane in place relative to a turbine case.
    Type: Grant
    Filed: April 23, 2019
    Date of Patent: December 7, 2021
    Inventors: Michael J. Whittle, Anthony G. Razzell, Roderick M. Townes, David J. Shepherd, Duncan Forbes
  • Kinetic disassembly of support structure system for additively manufactured rotating components
    Patent number: 11179895
    Abstract: A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.
    Type: Grant
    Filed: October 5, 2018
    Date of Patent: November 23, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Lawrence Binek, Matthew B. Kennedy, Evan Butcher, Jesse R. Boyer, Vijay Narayan Jagdale, Dmytro Mykolayovych Voytovych
  • Vane comprising a structure made of composite material and a metal stiffening part
    Patent number: 11174740
    Abstract: The invention relates to a vane (7) comprising: a structure made of composite material, a vane (7) root (16) attachment (9) comprising a base having a radial outer face (20) and in which a slot (24) configured to receive the vane (7) root (16) is formed and two platforms (26), extending on either side of the blade (18) opposite the radial outer face (20), and two stiffening parts (30), added and fixed on the radial outer face (20) on either side of the stilt (17) so as to tightly abut against the stilt (17).
    Type: Grant
    Filed: October 29, 2019
    Date of Patent: November 16, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Vivien Mickaël Courtier, Anthony Binder, Christophe Paul Jacquemard
  • Control method for a wind turbine
    Patent number: 11174838
    Abstract: The invention relates to a method of controlling a wind turbine comprising a wind direction sensor, a yawing system, and a control system for yawing the wind turbine rotor relative to the wind. The method comprises obtaining an estimate for a wind power parameter as a function of a relative wind direction, where the wind power parameter is determined as one of a power, a torque, a blade load, or a blade pitch angle of the wind turbine. At time intervals, a data set is established comprising a wind power parameter and a wind direction parameter as measured by the wind direction sensor. Over time a group of data sets is then obtained for a number of pre-defined wind direction intervals, and a wind direction offset is determined for each interval by comparing the average wind power parameter for that interval with the estimate of the wind power parameter.
    Type: Grant
    Filed: September 27, 2017
    Date of Patent: November 16, 2021
    Assignee: VESTAS WIND SYSTEMS A/S
    Inventor: Johnny Nielsen
  • Segmented non-contact seal assembly for rotational equipment
    Patent number: 11168574
    Abstract: An assembly is provided for rotational equipment. The assembly includes a circumferentially segmented stator and a rotor radially within the stator. The assembly also includes a seal assembly configured for substantially sealing a gap radially between the stator and the rotor. The seal assembly includes a carrier and a non-contact seal seated with the carrier. The carrier includes a plurality of discrete carrier segments circumferentially arranged around the non-contact seal.
    Type: Grant
    Filed: March 28, 2019
    Date of Patent: November 9, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, William K. Ackermann
  • Axial flow turbine
    Patent number: 11168576
    Abstract: To provide an axial flow turbine that can eliminate a circumferential velocity component of a leakage flow effectively, and attempt to collect motive power. A shroud of the axial flow turbine includes: an annular first protruding portion protruding toward the upstream side in a rotor's axis direction; an annular second protruding portion that is positioned on the outer side in the rotor's radius direction relative to the first protruding portion, protrudes toward the upstream side in the rotor's axis direction, and is longer than the first protruding portion; a circulating-flow generating chamber formed between the first protruding portion and the second protruding portion; and guide plates positioned in the circulating-flow generating chamber.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: November 9, 2021
    Assignee: Mitsubishi Power, Ltd.
    Inventor: Takanori Shibata
  • Blades having tip pockets
    Patent number: 11168569
    Abstract: A rotor blade for use in a turbine of a combustion turbine engine comprises an airfoil, which includes a concave pressure and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between base and outboard tip end. The rotor blade further including at least one mid-span shroud engages a corresponding mid-span shroud on at least one neighboring rotor blade. The airfoil includes an inboard region between the at least one mid-span shroud and base of the blade—and an outboard region between at least one mid-span shroud and outward tip. The outboard region includes at least two cavities extending from the outboard tip end inboard toward the at least one mid-span shroud; and inboard of the at least one mid-span shroud, the inboard region is substantially solid.
    Type: Grant
    Filed: April 17, 2020
    Date of Patent: November 9, 2021
    Assignee: General Electric Company
    Inventors: Neil Devin Ristau, Michael Anthony Wondrasek
  • Transfer bearing collapsing device
    Patent number: 11161598
    Abstract: A system for feathering a propeller assembly disposed within a housing of the propeller assembly has a sleeve defining an outer wall and one or more sleeve tabs extended outward in a radial direction along at least a circumferential portion of the sleeve, wherein the one or more sleeve tabs is separated from the outer wall in an axial direction, a retainer defining one or more retainer tabs extended inward in the radial direction, wherein the one or more retainer tabs is disposed between the outer wall and the one or more sleeve tabs of the sleeve along the axial direction, and a beta tube assembly extended through the sleeve along the axial direction. The beta tube assembly defines one or more internal walls. The one or more internal walls defines a hydraulic fluid transfer cavity in fluid communication with one or more hydraulic fluid transfer orifices.
    Type: Grant
    Filed: January 26, 2018
    Date of Patent: November 2, 2021
    Assignee: GE AVIO S.R.L.
    Inventors: Marco Garabello, Paolo Altamura, Gian Mario Bragallini, Davide Lauria
  • Airfoil cooling system
    Patent number: 11156122
    Abstract: An airfoil cooling system may include an airfoil that defines a first cooling chamber and a second cooling chamber. The first cooling chamber may be configured to receive a first cooling airflow from a first fluid source and the second cooling chamber may be configured to receive a second cooling airflow from a second fluid source that is different from the first fluid source. The airfoil may be a vane of a gas turbine engine. For example, the vane may be a first vane of a plurality of vanes of a turbine section of the gas turbine engine. The first cooling chamber may be a leading edge chamber of the first vane and the second cooling chamber may be an aft chamber of the first vane that is positioned aft of the leading edge chamber.
    Type: Grant
    Filed: June 19, 2018
    Date of Patent: October 26, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Daniel Bernard Kupratis
  • Low speed fan for gas turbine engines
    Patent number: 11156090
    Abstract: A fan section for a gas turbine engine is disclosed herein. The fan may include a rotor disk and a plurality of airfoils fixedly attached to and supported by the rotor disk as a single unitary piece. The airfoils may extend radially outward from the rotor disk with respect to an engine axis. The rotor disk may be made of metal and the airfoils may each be made at least partially of an organic matrix composite.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: October 26, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Gary D. Roberge
  • Multi-blade vane for a turbomachine rotor and rotor comprising same
    Patent number: 11156108
    Abstract: A vane (1) for a turbomachine rotor having a first blade (2) and a second blade (3). A platform (4) forms an angular wall sector in an axial direction (X), with the two blades (2, 3) connected to the platform (4). Two individual supports (12, 13), extend from the platform (4), and bear an attachment member (16, 17) at an end opposite the platform (4). The attachment member extends parallel to the axial direction (X) and has at least one surface (S1, S2) facing the platform (4) with a constant cross-sectional profile perpendicular to the axial direction (X) to form a bearing surface for retaining the vane (1) in a radial direction (R) oriented from the platform to the blades (2, 3).
    Type: Grant
    Filed: December 12, 2018
    Date of Patent: October 26, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Arnaud Nicolas Negri
  • Turbomachine blade
    Patent number: 11156107
    Abstract: A turbomachine blade includes a root intended to be mounted in a recessed pocket of a turbomachine rotor disc, the root having two side faces extending radially and longitudinally, each of the side faces including at least one seating intended to be inserted against a side wall of the recessed pocket, along an axis of longitudinal direction and to be in contact with the side walls of the recessed pocket, a radially inner face intended to face the bottom of the recessed pocket when the root is mounted in the recessed pocket, the radially inner face connecting the two side faces, the radially inner face including at least one curved concave surface and two curved convex surfaces, the curved concave surface extending from one end of each of the two curved convex surfaces.
    Type: Grant
    Filed: October 23, 2019
    Date of Patent: October 26, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Aurélien Gaillard, Pascal Grégory Casaliggi, Francis Gabriel Michel
  • Ceramic matrix composite load transfer roller joint
    Patent number: 11149567
    Abstract: An airfoil assembly includes a roller joint formed between a ceramic airfoil portion and a carrier allowing sliding (rolling) radial movement therebetween to accommodate thermal growth disparity.
    Type: Grant
    Filed: September 17, 2018
    Date of Patent: October 19, 2021
    Assignees: Rolls-Royce Corporation
    Inventors: Michael J. Whittle, Daniel Kent Vetters, Eric Koenig
  • Method of reducing manufacturing variation related to blocked cooling holes
    Patent number: 11149548
    Abstract: A cooling circuit for a gas turbine engine includes a gas turbine engine component having at least one internal cooling cavity defined by an internal wall surface and a plurality of turbulent flow features extending outwardly from the internal wall surface. Each turbulent flow feature is spaced apart from an adjacent turbulent flow feature in a first direction. At least one trench extends through the turbulent flow features in the first direction, and a plurality of cooling holes are formed within the at least one trench. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine component are also disclosed.
    Type: Grant
    Filed: October 24, 2014
    Date of Patent: October 19, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: James M. Koonankeil, Edward F Pietraszkiewicz, Francis M Tamiso, Kirk D Hlavaty
  • Fan including a platform and a locking bolt
    Patent number: 11143047
    Abstract: A fan includes: a fan disc; an inter-blade platform including a base and a radial tab, a second orifice being formed in the tab of the platform; and a lock having a downstream edge configured to bear against the tab of the platform. The one among the downstream edge and the yoke of the fan disc includes a pin, the other includes a first orifice, the pin being configured to enter the first orifice and the second orifice so as to block the platform relative to the fan disc.
    Type: Grant
    Filed: June 20, 2019
    Date of Patent: October 12, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jeremy Guivarc'h, Fabrice Michel Francois Rene Aubert, Pierre Martin Michelsen