Patents Examined by Igor Kershteyn
  • Gas turbine engine with inlet pre-swirl features
    Patent number: 11480063
    Abstract: A gas turbine engine may include a fan, a plurality of inlet pre-swirl features disposed upstream of a fan, and an outlet guide vane assembly disposed downstream of the fan. The outlet guide vane assembly includes a plurality of outlet guide vanes that may define an outlet guide vane solidity profile, wherein the outlet guide vane solidity profile is achieves a minimum solidity at a radial position between an inner boundary and seventy percent of an outlet guide vane span. The fan includes a plurality of fan blades that may define a fan solidity profile, wherein the fan solidity profile maintains a solidity of greater than 1.1 between a radial position at seventy percent of the fan blade span and an outer boundary.
    Type: Grant
    Filed: September 27, 2021
    Date of Patent: October 25, 2022
    Assignee: General Electric Company
    Inventors: Brandon Wayne Miller, Tsuguji Nakano
  • Modular casing manifold for cooling fluids of gas turbine engine
    Patent number: 11480055
    Abstract: A modular casing manifold for cooling fluids of a gas turbine engine is presented. The modular casing manifold has an annular shape including an axial inner plate, an axial outer plate, a radial forward plate and a radial aft plate. The forward plate is attached to the inner and outer plates at forward end. At least a portion of the aft plate is attachable to and removable from the inner and outer plates at aft end for enabling cooling fluid to cool turbine blades of the gas turbine engine. The modular casing manifold includes preswirler segments. At least a number of the preswirler segments are attachable to and removable from the forward plate for enabling cooling fluid to cool turbine blades of the gas turbine engine. The modular casing manifold enables alternative cooling fluids to cool turbine blades of the gas turbine engine with minimal cost and assembly flexibility.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: October 25, 2022
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventors: John William Farabow, III, Santiago R. Salazar
  • Turbomachine housing having at least one cover, turbomachine, method for producing a cover
    Patent number: 11466592
    Abstract: A turbomachine housing, in particular of a radial turbomachine which transfers technical work to a process fluid or from a process fluid, includes: an opening extending along an axis, for the axial feed-through of a shaft extending along said axis; a contact surface extending along a circumferential direction with respect to the axis, for contact with a housing jacket of the turbomachine housing. A flow line provided as an inflow or outflow of the process fluid is designed as an integral part of the cover.
    Type: Grant
    Filed: August 6, 2019
    Date of Patent: October 11, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Lars Korbmacher, Marcus Meyer, Steffen Petri, Kai Schickmann
  • Turbine shroud assembly with sealed pin mounting arrangement
    Patent number: 11466586
    Abstract: A shroud assembly adapted for use with a gas turbine engine includes a seal segment, a carrier, and a mount system. The seal segment extends circumferentially at least partway around an axis to define a gas path boundary of the shroud assembly. The carrier is configured to support the seal segment in position radially relative to the axis. The mount system couples the seal segment with the carrier.
    Type: Grant
    Filed: June 29, 2021
    Date of Patent: October 11, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, Alexandra Baucco, Jeffrey A. Walston
  • Overall engine efficiency rating for turbomachine engines
    Patent number: 11466624
    Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 3.2-4.0. The overall engine efficiency rating is within a range of 0.57-8.0.
    Type: Grant
    Filed: March 14, 2022
    Date of Patent: October 11, 2022
    Assignees: General Electric Company
    Inventors: Andrea Piazza, Jeffrey D. Clements
  • Mid-turbine frame with intermediary plenum
    Patent number: 11466590
    Abstract: A gas turbine engine has: a high-pressure turbine; a low-pressure turbine (LPT) having a LPT outer case and a LPT plenum extending around a central axis; a mid-turbine frame (MTF) assembly connecting the low-pressure turbine and the high-pressure turbine, the MTF assembly having: a MTF outer case defining an inlet for connection to a source of the cooling air, an intermediary plenum fluidly connected to the source of cooling air via the inlet, the intermediary plenum having a first air outlet and a second air outlet, and a MTF plenum disposed radially inwardly of the MTF outer case and fluidly connected to the source of the cooling air via the first air outlet of the intermediary plenum; and a cooling air conduit fluidly connecting the second air outlet of the intermediary plenum to the LPT plenum while bypassing the MTF plenum.
    Type: Grant
    Filed: June 17, 2021
    Date of Patent: October 11, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Gabriel St-Laurent
  • Turbine stator blade
    Patent number: 11459900
    Abstract: According to an embodiment, a turbine stator blade disposed in a working fluid flow path in a casing of a gas turbine, includes: a blade effective part disposed in the working fluid flow path; an outer circumferential sidewall having a plate-shaped part that is connected to a radially outer end portion of the blade effective part, and hooks each extending radially outward and circumferentially from the plate-shaped part and having a tip engaged with the casing; and an inner circumferential sidewall connected to a radially inner end portion of the blade effective part. At least one slit is formed at the rear hook or front hook to divide the hook in a circumferential direction, and the hook has a seal member to seal the slit.
    Type: Grant
    Filed: June 9, 2021
    Date of Patent: October 4, 2022
    Assignee: TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION
    Inventors: Norikazu Takagi, Tsuguhisa Tashima, Daisuke Nomura, Yoshifumi Iwasaki, Shogo Iwai, Takahiro Ono
  • Gas turbine engine with non-epicyclic gear reduction system
    Patent number: 11459957
    Abstract: A gas turbine engine comprises a fan drive turbine driving a shaft. The shaft engages a gear reduction. The gear reduction drives a fan rotor at a speed that is less than the speed of the fan drive turbine. The gear reduction is a non-epicyclic gear reduction.
    Type: Grant
    Filed: November 16, 2021
    Date of Patent: October 4, 2022
    Assignee: Raytheon Technologies Corporation
    Inventor: William G. Sheridan
  • Compressor stator vane airfoils
    Patent number: 11459892
    Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape having has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, Table IX, Table X, Table XI, or Table XII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: November 9, 2021
    Date of Patent: October 4, 2022
    Assignee: General Electric Company
    Inventors: Matthew John McKeever, Michael James Healy, Wilfried Rick, Rozila Nausheen, Sabarinath Devarajan, Moorthi Subramaniyan, Vsevolod Yuriyevich Ostrovskiy, Kumaran Vale Mudaliar, Damir Novak, Thomas Sommer, Aditya Rajeshbhai Shah, Uday Krishna Pappala, Kevin Michael Barnett, Josip Galic, Gurulakshmi Polisetty, Paul G. Deivernois, Dejan Mikasinovic
  • Blade root shank profile
    Patent number: 11454126
    Abstract: Turbine components, such as blades, having a shank portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, Table 2, or Table 1 and Table 2. X and Y are distances in inches which, when connected by smooth continuing arcs, define shank portion profile section edges at each Z distance in inches. The shank portion profile section edges at the Z distances are joined smoothly with one another to form a complete shank shape.
    Type: Grant
    Filed: August 24, 2021
    Date of Patent: September 27, 2022
    Assignee: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.
    Inventors: Andres Jaramillo, Clinton Mayer, Jinwoo Song
  • Gas turbine
    Patent number: 11454174
    Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a static structure on the input side of the gearbox device, an inter-shaft bearing system being positioned radially between the input shaft device and the planet carrier of the gearbox device.
    Type: Grant
    Filed: January 13, 2021
    Date of Patent: September 27, 2022
    Assignee: Rolls-Royce PLC
    Inventor: Alan R Maguire
  • Multifunctional nanocellular single crystal nickel for turbine applications
    Patent number: 11453955
    Abstract: A nanocellular single crystal nickel based material is provided having a thermal diffusivity in the range of 0.0002 cm{circumflex over (?)}2/s to 0.02 cm{circumflex over (?)}2/s and a thermal conductivity in the range of 0.024 W/mK to 9.4 W/mK. The nanocellular single crystal nickel based material may be used to form turbine engine components. The nanocellular single crystal nickel based material may be produced by providing a first solution containing a nickel precursor and deionized water, providing a second solution containing a structure controlling polymer/surfactant and an alcohol, mixing the first and second solutions into a solution containing a reducing agent to form a third solution, and processing the third solution to create the nanocellular single crystal based material.
    Type: Grant
    Filed: November 12, 2019
    Date of Patent: September 27, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Michael J. Birnkrant, Weina Li
  • Internal core profile for a turbine nozzle airfoil
    Patent number: 11454119
    Abstract: An internal core profile for a second stage turbine nozzle airfoil of a gas turbine is provided. The turbine nozzle may include an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections at each Z distance, and the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.
    Type: Grant
    Filed: July 16, 2021
    Date of Patent: September 27, 2022
    Inventors: Jinuk Kim, Kwangil Kim, Barry Brown, Jeff Greenberg, Darryl Eng, David Day
  • Gas turbine nozzle
    Patent number: 11448079
    Abstract: The present invention provides a gas turbine nozzle capable of reducing stress related to thermal elongation caused by a rise in gas turbine nozzle temperature and thus reducing stress produced when thermal deformation occurs in the gas turbine nozzle. The gas turbine nozzle according to the present invention includes nozzles formed integrally through an inner perimeter end wall and an outer perimeter end wall. The inner perimeter end wall has an upstream connection portion and a downstream connection portion. The upstream connection portion extends radially inward to be connected to an inner perimeter diaphragm. The downstream connection portion is located downstream from the upstream connection portion and extends radially inward to be connected to the inner perimeter diaphragm.
    Type: Grant
    Filed: July 1, 2021
    Date of Patent: September 20, 2022
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Hiroyuki Tate, Hironori Tsukidate, Kunihiro Oga, Yasuhiro Horiuchi
  • Spherical bearing centrifugal force retention link
    Patent number: 11440651
    Abstract: A spherical bearing centrifugal force retention link includes an inboard spherical bearing to attach to a rotor hub and an outboard spherical bearing to attach to a rotor blade. In use, the inboard spherical bearing and the outboard spherical bearing react centrifugal force radially and a torsional moment of the centrifugal force link is substantially constant throughout the rotor blade pitch range.
    Type: Grant
    Filed: March 1, 2021
    Date of Patent: September 13, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Andrew Paul Haldeman, Paul Wayne Woolbright, Timothy McClellan Mosig, George Matthew Thompson
  • Turbine shroud with split pin mounted ceramic matrix composite blade track
    Patent number: 11441441
    Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.
    Type: Grant
    Filed: June 18, 2021
    Date of Patent: September 13, 2022
    Assignee: Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, David J. Thomas
  • Lubricated enclosure for an aircraft turbine engine, limiting the retention of lubricant during pitching
    Patent number: 11441439
    Abstract: A lubricated enclosure for an aircraft turbine engine, including a drained roller bearing provided with drainage orifices, as well as a lubricant ejector intended to limit the retention of lubricant in a critical zone of the enclosure, the ejector being intended to be passed through by a primary lubricant flow in order to drive a secondary lubricant flow located around a nozzle of the ejector housed in the critical zone of the enclosure. The enclosure includes a device for establishing communication between the drainage orifices and the ejector, such that the lubricant that escapes from the drainage orifices supplies the ejector in order to form the primary flow.
    Type: Grant
    Filed: September 27, 2017
    Date of Patent: September 13, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Serge Rene Morreale
  • Linkage supporting a door of an aircraft propulsion system
    Patent number: 11427341
    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes an inner cowl door, an outer cowl door and a flexible linkage. The outer cowl door is radially outboard of and overlaps the inner cowl door. The flexible linkage is configured to connect to and thereby link the inner cowl door and the outer cowl door.
    Type: Grant
    Filed: September 30, 2020
    Date of Patent: August 30, 2022
    Assignee: Rohr, Inc.
    Inventor: Sean Pretty
  • Clip fan for plant tent
    Patent number: 11428245
    Abstract: A clip-on fan includes a specialized clamping clip 56 that is attached to rectangular or cylindrical tent poles that are commonly used for grow tents; wherein fans are essential components for growing in tents and the current designs clip-on fans do not meet the needs of indoor growers; the clip-on fan comprising a fan assemblage and clip clasp assemblage arranged at the base of the complete product, wherein the clip 5 is able to grasp to the vertical tubular structure of a grow tent; the grasping clasp 5 assembly consisting of: a left clip plate 51, a right clip plate 52, a clip plate rotation shaft 53, a clip spring 54, a fan connection hole 55 and, a clip clamp opening 56; the left and right clip plates are connected in a bilateral symmetry through the clip plate rotation shaft at the central connection position.
    Type: Grant
    Filed: June 9, 2020
    Date of Patent: August 30, 2022
    Assignee: Sinowell (Shanghai) Co., Ltd.
    Inventors: Jia Luo, Yan Yang
  • Turbine blade
    Patent number: 11428109
    Abstract: A turbine blade for a turbomachine includes a turbine blade with a leading edge and a trailing edge. The blade includes a radially outer platform with at least one lip extending radially towards the outside. The radially outer end of the leading edge and/or of the trailing edge of the turbine blade airfoil extending axially upstream and/or downstream, respectively, in relation to the platform. The blade has at least one partition extending radially towards the outside from the radially outer end of the turbine blade airfoil and axially between the leading edge and the upstream end of the platform and/or between the trailing edge and the downstream end of the platform.
    Type: Grant
    Filed: July 23, 2019
    Date of Patent: August 30, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Renaud James Martet, Thomas Langevin, Cyril Verbrugge