Patents Examined by Eldon T Brockman
  • Multi-material vane for a gas turbine engine
    Patent number: 11572796
    Abstract: A multi-material vane includes an airfoil extending longitudinally between a leading edge and a trailing edge. The airfoil extends spanwise between an inner end and an outer end. The airfoil extends laterally between a first side and a second side. The airfoil includes a base section, a first side section, a second side section and a sheath. The base section extends along the span line between the inner end and the outer end. The base section is laterally between the first side section and the second side section. The first side section is connected to the base section and partially forms the first side of the airfoil. The second side section is connected to the base section and partially forms the second side of the airfoil. The sheath at least partially forming an edge of the airfoil. The edge is the leading edge or the trailing edge of the airfoil.
    Type: Grant
    Filed: April 17, 2020
    Date of Patent: February 7, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Arun K. Theertham, Andrew Pope
  • Bearing housing and method of making
    Patent number: 11572922
    Abstract: A bearing housing for supporting a bearing of a gas turbine engine. The bearing housing comprises an annular body extending around an axis and having an oil inlet and an oil outlet. The bearing housing further comprises an oil manifold integrated into the annular body, the oil manifold having an inner oil channel defined in the annular body and extending circumferentially around the axis, the inner oil channel in fluid communication with the oil inlet and at least one oil jet directed towards the bearing.
    Type: Grant
    Filed: December 16, 2020
    Date of Patent: February 7, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • Turbomachine ring
    Patent number: 11566540
    Abstract: Turbomachine ring as well as a turbomachine comprising such a ring and a method for repairing such a ring, the turbomachine ring comprising an essentially cylindrical support, including a frontal surface wherein a notch is formed, one or more sectors forming an annulus configured to embody a segment of air stream, each sector comprising a hook portion protruding in the direction of the support and engaging in the notch of the support, and an anti-wear device having a U shaped portion, provided in the notch of the support and pressed at least against the radially external surface of the notch, and a tab portion, continuously extending the U shaped portion, pressed and fastened against the frontal surface of the support.
    Type: Grant
    Filed: January 9, 2019
    Date of Patent: January 31, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Quentin Pierre Hubert Bomberault, Martin Jubien, Julien Michel Auguste Robert
  • Component with cooling passage for a turbine engine
    Patent number: 11560803
    Abstract: An engine component for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising a wall defining an interior and having an outer surface over which flows the combustion airflow, the outer surface defining a first side and a second side. The engine component further comprising at least one cooling conduit provided in the interior and having conduit sidewalls and a set of cooling passages formed in the wall and fluidly coupling the at least one cooling conduit to the outer surface, at least one of the cooling passages in the set comprising a primary cooling passage portion and a secondary cooling passage portion. A diffusion slot located in the primary cooling passage portion and an impingement zone fluidly coupled to the diffusion slot.
    Type: Grant
    Filed: November 5, 2021
    Date of Patent: January 24, 2023
    Assignee: General Electric Company
    Inventors: Daniel Endecott Osgood, Kirk Douglas Gallier, Zachary Daniel Webster, Gregory Terrence Garay, Daniel Lee Durstock, Ricardo Caraballo
  • Fan blade with internal magnetorheological fluid damping
    Patent number: 11560801
    Abstract: An airfoil for use in a gas turbine engine is formed to define a cavity formed in the airfoil. The airfoil further includes at least one obstructing member arranged within the cavity and a magnetorheological fluid disposed in the cavity. A viscosity of the magnetorheological fluid increases in response to a magnetic field being generated proximate to the fluid in response to the airfoil experiencing an aeromechanic response or vibrations. As such, the obstruction of the movement of the thicker fluid by the obstructing member dampens the vibrations of the airfoil and reduces negative effects of a dynamic response of the airfoil.
    Type: Grant
    Filed: December 23, 2021
    Date of Patent: January 24, 2023
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Robert W. Heeter, Daniel E. Molnar, Jr., Christopher D. Hall
  • Turbine nozzle assembly
    Patent number: 11560806
    Abstract: A turbine nozzle assembly for use in a turbine engine is provided. The assembly includes an inner barrel and a turbine nozzle support ring. The inner barrel has a forward end and an aft end. The turbine nozzle support ring includes an annular body that defines a forward end, an opposite aft end, an inner surface, and an opposite outer portion. The forward end of the annular body is coupled to the aft end of the inner barrel. The annular body includes a first arcuate segment and a second arcuate segment removably coupled to the first arcuate segment. The first arcuate segment has a first arcuate length and the second arcuate segment has a second arcuate length. The second arcuate length is shorter than the first arcuate length.
    Type: Grant
    Filed: December 27, 2021
    Date of Patent: January 24, 2023
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Christopher Paul Cox
  • Oil system of a gas turbine engine
    Patent number: 11549398
    Abstract: An oil system of a gas turbine engine, has first and second oil circuits. The oil circuits include. Respectively, first and second oil reservoirs, first and second oil consumers of the engine, and first and second heat exchangers for temperature control. The first oil consumer is impinged with oil from the first oil reservoir. The second oil consumer is impinged with oil from the second oil reservoir. The first oil consumer is connected to the first oil reservoir, and the second oil consumer is connected to the second oil reservoir. The operating temperature of oil in the first oil circuit is lower than in the second oil circuit. The first oil reservoir is connected to the second oil reservoir. Oil from each oil reservoir can be guided into the other oil reservoir via the connection.
    Type: Grant
    Filed: December 8, 2021
    Date of Patent: January 10, 2023
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Wolfram Kurz-Hardjosoekatmo
  • Airfoil assembly with composite rings and sealing shelf
    Patent number: 11549378
    Abstract: An airfoil assembly includes first and second fiber-reinforced composite airfoil rings each having inner and outer platform sections. A sealing shelf extends from a suction side wall of one of the first and second fiber-reinforced composite airfoil rings, and towards the pressure side wall of the other of the rings. A first seal is captured radially inwardly of the sealing shelves on outer platforms of each of the first and second fiber-reinforced composite airfoil rings. A second seal is captured inward of the sealing shelves on the inner platforms of each of the first and second fiber-reinforced composite rings to provide a seal between the respective first and second fiber-reinforced composite airfoil rings, and a captured internal component. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: June 3, 2022
    Date of Patent: January 10, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: Jon E. Sobanski
  • Airfoil assembly with seal plate and seal
    Patent number: 11549385
    Abstract: An airfoil assembly includes an airfoil fairing, a spar, a seal plate, and a seal. The airfoil fairing has a fairing platform and a hollow airfoil section that extends from the fairing platform. The spar has a spar leg that extends in the hollow airfoil section. The spar leg defines a spar leg periphery. The seal plate is secured with the fairing platform. The seal plate has an opening, and the opening has an opening periphery that is complementary to the spar leg periphery. The spar leg extends through the opening. The seal is between the seal plate and the spar leg. The seal seals around the spar leg periphery.
    Type: Grant
    Filed: May 4, 2021
    Date of Patent: January 10, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Robert A. White, III, Bryan P. Dube
  • Hybrid seal dual runner
    Patent number: 11549444
    Abstract: A turbomachine has a bearing in a bearing compartment. A first seal system isolates the bearing compartment and has: a first runner; a second runner; an inner seal encircling the first runner; and an outer seal encircling the second runner. The inner seal has a static clearance with the first runner. The outer seal has a static clearance with the second runner, greater than the inner seal static clearance. The first runner has an inner portion cantilevered inward. The second runner has an outer portion cantilevered outward.
    Type: Grant
    Filed: February 5, 2021
    Date of Patent: January 10, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Michael A. Beinor, Timothy J. Castaldo, Christopher M. Valva, Nasr A. Shuaib, Mitchell D. Panton
  • Centrifugal fan noise-lowering structure
    Patent number: 11542960
    Abstract: A centrifugal fan noise-lowering structure includes a frame having an upper and a lower cover and a sidewall, which together internally define a receiving space communicable with an air inlet and an air outlet of the frame; a stator assembly located in the receiving space and fixedly mounted on the lower cover; and a rotor assembly correspondingly assembled to the stator assembly. The receiving space is internally defined a high pressure zone and a low pressure zone. The upper cover is provided with an airflow passage, which has an inlet located at a position corresponding to the high pressure zone, and an outlet located at a position corresponding to the low pressure zone. With the airflow passage, air in the high pressure zone can be guided to jet out to the low pressure zone to thereby reduce noise produced by the centrifugal fan during its operation.
    Type: Grant
    Filed: September 7, 2021
    Date of Patent: January 3, 2023
    Assignee: ASIA VITAL COMPONENTS CO., LTD.
    Inventors: Yu-Tzu Chen, Chung-Shu Wang
  • Labyrinth seals
    Patent number: 11542826
    Abstract: A labyrinth seal including: an annular seal body having an inner wall and an outer wall spaced apart from one another by an annulus; a nested dampener system disposed along the outer wall, the nested dampener system including: a first dampening element; and a second dampening element, wherein opposite axial ends of the nested dampener system are defined by the first dampening element, and wherein the second dampening element is disposed outside of at least a portion of the first dampening element in a radial direction.
    Type: Grant
    Filed: March 18, 2021
    Date of Patent: January 3, 2023
    Assignee: General Electric Company
    Inventors: Scott Francis Wolfer, Richard Alan Wesling
  • Endwall cooling scheme
    Patent number: 11536143
    Abstract: An endwall assembly disposed at one end of a vane assembly may comprise an endwall spar that includes an cold side, an hot side, a leading edge, a trailing edge, and an axis extending from the leading edge to the trailing edge perpendicular to the leading edge. The endwall assembly may include a coversheet on the hot side of the endwall spar and a cooling channel that includes a cooling fluid inlet disposed in the endwall spar, and a cooling fluid outlet. The endwall assembly may include a structure protruding from the cold side of the endwall spar, wherein the structure is located between the cooling fluid inlet and the cooling fluid outlet along the axis; and a cooling fluid source cavity on the cold side of the wall, the cooling fluid source cavity in fluid communication with the cooling fluid channel via the cooling fluid inlet.
    Type: Grant
    Filed: December 22, 2021
    Date of Patent: December 27, 2022
    Assignees: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE CORPORATION
    Inventors: Jack Moody, Jerry Layne, Jeffrey F. Rhodes, Brett Barker, Eric Koenig
  • Vane arc segment with thermal insulation element
    Patent number: 11536148
    Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a first platform radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the first platform radial flange. A thermal insulation element is situated adjacent the first platform radial flange. The support hardware supports the airfoil piece through the thermal insulation element.
    Type: Grant
    Filed: November 24, 2020
    Date of Patent: December 27, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Raymond Surace, Mark F. Zelesky
  • Vane arc segment with flange and gusset
    Patent number: 11536147
    Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.
    Type: Grant
    Filed: March 30, 2021
    Date of Patent: December 27, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jon E. Sobanski, Bryan P. Dube
  • Rotatable forged disc for a bladed rotor wheel and a method for manufacturing thereof
    Patent number: 11530613
    Abstract: The present invention provides a bladed rotor wheel for a gas turbine engine comprising at least a rotatable forged disc, the rotatable forged disc comprising a front surface and a back surface, at least one rim surface, and a plurality of projections located on at least a portion of at least one of the front or back surface and/or on the rim surface; wherein the projections are 3D printed features protruding outwards from the front, back and/or rim surface; the projections are arranged forming a pattern so that a heat transfer capability is created at the front, back and/or rim surface; and the ratio of the distance between projections to the forged disc external radius is lower than 0.15. Furthermore, the present invention also provides a method for manufacturing a rotatable forged disc for a bladed rotor wheel.
    Type: Grant
    Filed: March 29, 2021
    Date of Patent: December 20, 2022
    Assignee: ITP ENGINES UK LTD
    Inventors: Quentin Luc Balandier, Vinod Kakade
  • Compact axial fan
    Patent number: 11525456
    Abstract: An axial fan has an inner-rotor motor which includes a drive end, a non-drive end and a shaft which extends axially from the drive end; and an impeller which includes a cylindrical impeller cup and a number of impeller blades that extend radially from the impeller cup. The impeller cup has an open upstream end and a closed downstream end which is connected to the shaft. In operation, the motor spins the impeller to generate an airflow in a direction from the non-drive end of the motor to the drive end of the motor. The impeller cup is configured to receive the motor therein and surround the drive end of the motor but not the non-drive end of the motor. As a result, the non-drive end of the motor is exposed to the airflow during operation of the fan.
    Type: Grant
    Filed: July 8, 2016
    Date of Patent: December 13, 2022
    Assignee: Bascom Hunter Technologies, Inc.
    Inventors: John Decker, Ralph Carl, David Gonzales Campos
  • Turbomachine with serrated-profile flow-splitter nose
    Patent number: 11525365
    Abstract: A front fan turbomachine includes an annular separating wall having a slat for separating an air flow between a primary flow and a secondary flow, the slat having a leading edge; inlet guide vanes (IGV) for guiding the primary flow and outlet guide vanes (OGV) blades for guiding the secondary flow. The leading edge of the slat has a serrated profile having a succession of teeth and depressions.
    Type: Grant
    Filed: February 15, 2019
    Date of Patent: December 13, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Fernando Gea Aguilera, Matthieu Fiack, Mathieu Simon Paul Gruber
  • Flow straightener unit comprising a centering and attachment plate
    Patent number: 11525366
    Abstract: The invention concerns a flow straightener unit (1) for a fan module of a turbomachine, the straightener unit (1) comprising a plurality of blades (2) distributed about an axis of rotation, each blade (2) is made of a composite material and comprises an aerofoil (21) and a root (22) intended to be assembled on a hub (4) of the turbomachine. The unit (1) comprises a centring and attachment plate (3) of the blade (2) on the turbomachine intended to be attached to the hub (4) at a determined azimuthal position and to the root (22) of the blade (2), the plate (3) is designed to be screwed to the hub (4) by screws (51a) that are longitudinal with respect to the axis of rotation of the unit (1) and screwed to the root (22) of the blade (2) by screws (52) that are radial with respect to the axis of rotation of the unit (1).
    Type: Grant
    Filed: November 8, 2019
    Date of Patent: December 13, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Alexandre Bernard Marie Boisson, Kaëlig Merwen Orieux
  • Sealing between a rotor disc and a stator of a turbomachine
    Patent number: 11525367
    Abstract: Assembly including a rotor disc, an adjacent stator and a plurality of sealing elements secured to the rotor disc, the stator including an inner platform and a root bearing at least one abradable element configured to cooperate with the sealing elements, the sealing elements being placed in an enclosure formed by the abradable element, the enclosure being open to the inside and delimited axially by an upstream abradable edge and a downstream abradable edge, the enclosure being delimited radially by an outer abradable edge, at least one of the sealing elements including a first lip configured to cooperate with the upstream abradable edge or the downstream abradable edge, and a second, separate lip configured to cooperate with the outer abradable edge.
    Type: Grant
    Filed: November 6, 2019
    Date of Patent: December 13, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Xavier Trappier, Joao Antonio Amorim, Maxime Aurelien Rotenberg