Method Of Operation Patents (Class 415/1)
  • Patent number: 11028711
    Abstract: According to the present invention, part of carbon dioxide heated by a heater is supplied to a dry gas seal portion of a compressor so that a device for pressurizing and heating a seal gas is not additionally required, configuration can be simplified and cost can be reduced. In addition, a seal gas flow path includes a low-temperature seal gas flow path and a high-temperature seal gas flow path so that, in an initial driving mode, carbon dioxide heated by a high-temperature portion of the heater is used as a seal gas and in a turbine-driving mode, carbon dioxide heated by a low-temperature portion of the heater is used as a seal gas and thus a more efficient operation can be performed.
    Type: Grant
    Filed: June 26, 2019
    Date of Patent: June 8, 2021
    Inventors: Jun Hyun Cho, Bong Su Choi, Ho Sang Ra, Hyung Ki Shin, Jong Jae Cho, Beom Joon Lee, Chul Woo Roh, Gil Bong Lee, Young Jin Baik
  • Patent number: 11022369
    Abstract: A booster system for increasing pressure of an object gas includes: a first compression unit that compresses the object gas to intermediate pressure equal to or higher than the critical pressure and lower than the target pressure and generates an intermediate supercritical fluid; a cooling unit that cools the intermediate supercritical fluid with a cooling medium and generates an intermediate supercritical pressure liquid; a liquid extracting and pressure reducing unit that extracts a part of the intermediate supercritical pressure liquid; a flow regulating valve that regulates a flow rate of the extracted part of the intermediate supercritical pressure liquid; a second compression unit that increases pressure of the rest of the intermediate supercritical pressure liquid to be equal to or higher than the target pressure; and a pressure sensor that detects pressure of the intermediate supercritical pressure liquid.
    Type: Grant
    Filed: February 9, 2016
    Date of Patent: June 1, 2021
    Inventors: Hideki Nagao, Masahiro Kobayashi
  • Patent number: 11015550
    Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is no more than 0.45.
    Type: Grant
    Filed: February 2, 2018
    Date of Patent: May 25, 2021
    Inventors: Wesley K. Lord, Robert E. Malecki, Yuan J. Qiu, Becky E. Rose, Jonathan Gilson
  • Patent number: 11015614
    Abstract: Variable vane devices containing rotationally-driven translating vane structures are provided, as are methods for fabricating variable vane devices. In one embodiment, the variable vane device includes a flow assembly having a centerline, an annular flow passage extending through the flow assembly, cam mechanisms, and rotationally-driven translating vane structures coupled to the flow assembly and rotatable relative thereto. The translating vane structures include vane bodies positioned within the annular flow passage and angularly spaced about the centerline. During operation of the variable vane device, the cam mechanisms adjust translational positions of the vane bodies within the annular flow passage in conjunction with rotation of the translating vane structures relative to the flow assembly.
    Type: Grant
    Filed: October 17, 2019
    Date of Patent: May 25, 2021
    Inventors: Richard David Conner, Bruce David Reynolds, Timothy Gentry, Peter Hall
  • Patent number: 11000881
    Abstract: Apparatus (200) for sorting mixed waste materials, comprising: a housing (260) configured to be vibrated to assist sorting; a screen (210) supported by the housing (260) and having an inlet end (212) for receiving waste materials and an outlet end (214) for discharging at least some waste received at the inlet end (212), the screen (210) comprising at least one portion (220) pivotally coupled adjacent the inlet end (212) to a substantially horizontal axle (222) mounted in the housing (260); and drive means (224,228) configured to pivot the at least one portion (222) of the screen (210) about the axle (222) with a controlled reciprocating action.
    Type: Grant
    Filed: October 19, 2016
    Date of Patent: May 11, 2021
    Assignee: RCW Investments Limited
    Inventor: Roger White
  • Patent number: 10989112
    Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
    Type: Grant
    Filed: May 14, 2019
    Date of Patent: April 27, 2021
    Assignee: ROLLS-ROYCE PLC
    Inventors: Pascal Dunning, Roderick M Townes, Michael J Whittle
  • Patent number: 10989210
    Abstract: The present invention relates to a method and control system to control the speed of centrifugal compressors operating within a vacuum pressure swing adsorption process to avoid an operation at which surge can occur and directly driven by an electric motor that is in turn controlled by a variable frequency drive, while subsequently operating the vacuum pressure swing process between set limits of highest adsorption and lowest desorption pressure. In accordance with present invention an optimal speed for operation of the compressor is determined at which the compressor will operate along a peak efficiency operating line of a compressor map thereof. This speed is adjusted by a feed back speed multiplier when the flow or other parameter referable to flow through the compressor is below a minimum and a feed forward multiplier during evacuation and evacuation with purge steps that multiplies the feed back multiplier to increase speed of the compressor and thereby avoid surge.
    Type: Grant
    Filed: July 10, 2017
    Date of Patent: April 27, 2021
    Inventors: Garrett R. Swindlehurst, Andrew C. Rosinski, Michael S. Manning
  • Patent number: 10989211
    Abstract: A method is described for providing antisurge control in a system comprising a compressor having at least an upstream compressor stage, a downstream compressor stage and a side stream bringing flow into a flow passage between the upstream compressor stage and the downstream compressor stage. The method provides for estimating a temperature of a flow delivered by the upstream compressor stage using a non-dimensional performance map of the upstream compressor stage and further estimating a temperature of a flow entering the downstream compressor stage based on the mass flow and flow temperature of the flow delivered by the downstream compressor stage and the mass flow and the flow temperature of the side stream. The method further provides for performing antisurge control of the downstream compressor stage based on the temperature of the flow entering the downstream compressor stage.
    Type: Grant
    Filed: March 24, 2014
    Date of Patent: April 27, 2021
    Inventors: Daniele Galeotti, Antonio Pelagotti, Gabriele Giovani
  • Patent number: 10982565
    Abstract: A turbine housing section includes a radially inner case centered on a first axis, and a radially outer case spaced radially outwardly of the inner case, and centered on a second axis. The first and second axes are offset relative to each other. A plurality of tie rods include a threaded nut received on a tie rod, with the plurality of tie rods connecting the inner and outer cases. The plurality of tie rods are spaced circumferentially about both of the first and second axes, and extend for distinct lengths between the inner and outer cases such that the inner and outer cases are held at a position wherein the first and second axes are offset.
    Type: Grant
    Filed: January 21, 2013
    Date of Patent: April 20, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Dale William Petty, James P. Allore, Joseph T. Caprario, Steven J. Bauer
  • Patent number: 10975770
    Abstract: A heat exchanging arrangement is integrated within a gas turbine engine case that at least partially encloses a gas turbine engine. The gas turbine engine has an upstream end and a downstream end which are defined by a core fluid flow through the gas turbine engine. The heat exchanging arrangement includes at least one flow passage defined within the gas turbine engine case having an inlet port and an outlet port. The at least one flow passage is configured to direct at least a portion of a fluid flowing through the gas turbine engine from between a downstream position and an upstream position while traveling between the inlet port and the outlet port.
    Type: Grant
    Filed: December 5, 2019
    Date of Patent: April 13, 2021
    Inventor: Christopher Simpson
  • Patent number: 10975849
    Abstract: A first vibration sensor measures vibration of a bearing. A second vibration sensor for measuring background noise received by the first vibration sensor is installed so as not to receive vibration of the bearing. A data acquisition device receives a first signal that is a measurement signal of the first vibration sensor and a second signal that is a measurement signal of the second vibration sensor and outputs a third signal obtained by subtracting the second signal from the first signal as data indicating vibration of the bearing.
    Type: Grant
    Filed: March 15, 2017
    Date of Patent: April 13, 2021
    Inventors: Yosuke Suzuki, Toru Takahashi
  • Patent number: 10975802
    Abstract: A gas turbine engine generates noise during use, and one particularly important flight condition for noise generation is take-off. A gas turbine engine that has high efficiency provides low noise, in particular from the fan and the turbine that drives the fan. Values are defined for a noise parameter NP that results in a gas turbine engine having reduced combined fan and turbine noise.
    Type: Grant
    Filed: April 30, 2019
    Date of Patent: April 13, 2021
    Assignee: ROLLS-ROYCE PLC
    Inventors: Alastair D Moore, Robert J Telling
  • Patent number: 10968767
    Abstract: A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system including: a variable vane; a vane stem operably associated with the variable vane, wherein the variable vane is configured to rotate with the vane stem; a vane arm having vane stem end and a vane pin end opposite the vane stem end, the vane arm being operably connected to the vane stem at the vane stem end; and a rotational variable differential transformer operably connected to the vane stem, the rotational variable differential transformer configured to detect an amount of rotation of the vane stem.
    Type: Grant
    Filed: May 1, 2018
    Date of Patent: April 6, 2021
    Inventors: William S. Pratt, Martin Richard Amari, Steven D. Roberts, Ryan M. Stanley
  • Patent number: 10961919
    Abstract: Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A pressure ratio between a first pressure at an inlet of the engine and a predetermined reference pressure is determined. An output power for the engine is determined. The output power is adjusted based at least in part on the pressure ratio to obtain a corrected output power. A position control signal for a variable geometry mechanism of the engine is generated based on the corrected output power and the pressure ratio. The position control signal is output to a controller of the engine to control the variable geometry mechanism.
    Type: Grant
    Filed: July 11, 2018
    Date of Patent: March 30, 2021
    Inventors: Philippe Beauchesne-Martel, Poi Loon Tang, Andrew Thompson, Ghislain Plante
  • Patent number: 10962016
    Abstract: A centrifugal compressor according to an exemplary aspect of the present disclosure includes, among other things, an impeller provided in a main flow path and configured to pressurize a main flow of fluid. The compressor also includes a secondary flow path configured to provide a secondary flow by recirculating a portion of the main flow. The amount of the main flow that becomes the secondary flow is less than or equal to 15%. A method is also disclosed.
    Type: Grant
    Filed: February 4, 2016
    Date of Patent: March 30, 2021
    Inventors: Joost Brasz, William Bilbow, Farrukh Alvi, Erik Fernandez, Jennifer Gavin
  • Patent number: 10961850
    Abstract: A gas turbine engine including a torque frame is provided. The torque frame includes an inner shroud defined circumferentially around the axial centerline, an outer shroud surrounding the inner shroud and defined circumferentially around the axial centerline, and a structural member extended along the radial direction and coupled to the inner shroud and the outer shroud. The torque frame is configured to rotate around the axial centerline.
    Type: Grant
    Filed: September 19, 2017
    Date of Patent: March 30, 2021
    Assignee: General Electric Company
    Inventors: Gert Johannes van der Merwe, Darek Tomasz Zatorski, Richard Alan Wesling, Jeffrey Donald Clements
  • Patent number: 10947859
    Abstract: A clearance control arrangement (26) for a rotor (28) comprising a segment assembly (33) spaced radially inwards from a casing (32) and defining a radial clearance (42) between the rotor (28) and the segment assembly (33). A front carrier (35a) and a rear carrier (35b) supporting the segment assembly (33). A heat transfer cavity (48) formed between the carriers (35a, 35b), the segment assembly (33) and the casing (32). A settling chamber (60) formed adjacent to the casing (32) and upstream of the heat transfer cavity (48). The clearance control arrangement (26) is configured to receive air into the settling chamber (60) and thence to deliver it to the heat transfer cavity (48).
    Type: Grant
    Filed: June 1, 2018
    Date of Patent: March 16, 2021
    Assignee: ROLLS-ROYCE plc
    Inventors: Leo V. Lewis, Vinod Gopalkrishna
  • Patent number: 10920610
    Abstract: A casting plug for a vane of a gas turbine engine includes a plug body a flow control feature and a support that extends between the plug body and the flow control feature.
    Type: Grant
    Filed: June 11, 2018
    Date of Patent: February 16, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Jaime G. Ghigliotty
  • Patent number: 10920671
    Abstract: A gas turbine engine includes a first spool including a first compressor coupled to a first turbine through a first shaft, a second spool including a second compressor coupled to a second turbine through a second shaft. A first tower shaft is coupled to the first shaft through a first gear assembly and a second tower shaft is coupled to the second shaft through a second gear assembly. A first load generating device is driven by the first tower shaft and a second load generating device is driven by the second tower shaft. A controller controls each of the first load generating device and the second load generating device to vary a proportion of the total load applied to each of the first spool and the second spool to bias a direction of an axial load on each of the first spool and the second spool.
    Type: Grant
    Filed: September 25, 2018
    Date of Patent: February 16, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Gary D. Roberge
  • Patent number: 10920600
    Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. The blade outer air seal has a lip at an axial end engaged with the support structure. A seal structure has a seal portion and a wear liner portion joined by a radially extending portion. The seal portion is radially outward of the lip and the wear liner is radially inward of the lip.
    Type: Grant
    Filed: September 5, 2018
    Date of Patent: February 16, 2021
    Inventors: Ken F. Blaney, Paul M. Lutjen, Thomas E. Clark
  • Patent number: 10907508
    Abstract: A ceramic matrix composite (“CMC”) center body may be positioned around an austenitic nickel-chromium-based superalloy attachment ring. The attachment ring may be integrally formed with a turbine engine case. The attachment ring may have a greater coefficient of thermal expansion than the center body. A plurality of pins may be inserted through apertures in the center body and coupled to the attachment ring. The pins may slide within the apertures, allowing the attachment ring to expand without applying a load on the center body.
    Type: Grant
    Filed: February 2, 2016
    Date of Patent: February 2, 2021
    Assignee: Rohr, Inc.
    Inventors: Michael Knight, Fadi Iskander, Narek Geghamyan
  • Patent number: 10907642
    Abstract: A compressor system including: a first compressor having a compressor suction side and a compressor delivery side; an anti-surge line having an inlet and an outlet; an anti-surge valve arranged along the anti-surge line and controlled for recirculating a gas flow from the compressor delivery side back to the compressor suction side; a gas temperature manipulation arrangement, functionally connected to the inlet of the anti-surge line, configured to reduce or prevent liquid phase in the anti-surge line when the anti-surge valve is open.
    Type: Grant
    Filed: July 7, 2016
    Date of Patent: February 2, 2021
    Inventors: Lorenzo Gallinelli, Marco Pelella
  • Patent number: 10907501
    Abstract: Shroud assemblies and methods for cooling gas turbine engine shrouds are provided. For example, a shroud assembly comprises a shroud segment having hot and cold side portions. The hot side portion faces a gas flow path, and the cold side portion faces a cooling fluid flow path. The shroud assembly further comprises a shroud hanger for mounting the shroud segment in the gas turbine engine. The shroud hanger includes a conduit for receipt of a flow of cooling fluid that defines an outlet configured for the flow of cooling fluid to exit the conduit substantially tangential to the cold side portion of the shroud segment. The shroud and shroud hanger together define an annular cavity that forms the cooling fluid flow path, and fluid exits a plurality of conduits defined in the shroud hanger into the cavity substantially tangential to the shroud cold side to cool the shroud cold side.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: February 2, 2021
    Assignee: General Electric Company
    Inventors: Sergio Filippi, Ryan Nicholas Porter, Craig Alan Gonyou, Scott Alan Schimmels
  • Patent number: 10900409
    Abstract: A device for controlling an air flow in a motor vehicle compartment. The device includes: a frame defining an opening; a plurality of slats extending across the frame, arranged above one another; and an actuator connected to each of the slats by a respective fastener. Each slat extends in a respective air deflection plane, and is movable via the actuator, between: a closed position, in which the slats cooperate with one another to block the passage of the air through the opening, and an open position, in which the slats allow the air to flow through the opening, the deflection planes of the slats intersecting upstream from the frame. Each fastener is mounted rotatably only on the actuator, around a respective actuating axis.
    Type: Grant
    Filed: June 1, 2018
    Date of Patent: January 26, 2021
    Inventors: Yann Clapie, Bertrand Thoulouze, Daniel Eichlinger
  • Patent number: 10900414
    Abstract: There is disclosed a fan assembly including a fan rotor including a hub and fan blades. The fan blades have a leading edge and a trailing edge. A fan stator downstream of the fan rotor relative to a direction of an airflow through the fan assembly. The fan stator includes vanes extending between radially inner ends and radially outer ends. A flow recirculation circuit has an inlet downstream of radially inner ends of the vanes of the fan stator and an outlet upstream of radially inner ends of the vanes. A recirculation stator has a plurality of stationary guide vanes circumferentially distributed around the axis and located in the flow recirculation circuit between the inlet and the outlet A method of operating the fan assembly is also disclosed.
    Type: Grant
    Filed: November 23, 2018
    Date of Patent: January 26, 2021
    Inventors: Hien Duong, Karan Anand, Vijay Kandasamy, Rakesh Munlyappa
  • Patent number: 10896512
    Abstract: An aerial vehicle outfitted with one or more cameras captures a sequence of images of a rotating propeller. The images are processed according to one or more techniques to recognize a position of the propeller, or an angle of orientation of the propeller, in each of the images. The positions or angles of the rotating propeller are used to calculate a rotational speed of the propeller, or a direction of rotation of the propeller. The cameras used to capture the images are also available for use in other applications such as navigation, monitoring or collision avoidance. The propeller may include one or more stripes, colors, characters, symbols or other markings to enhance its visibility and facilitate the determination of positions or angles of the propeller within images.
    Type: Grant
    Filed: August 28, 2018
    Date of Patent: January 19, 2021
    Assignee: Amazon Technologies, Inc.
    Inventors: Joseph Rutland, Demian Shaft Raven
  • Patent number: 10883510
    Abstract: A control method of a centrifugal compressor (C) mechanically coupled to an expansion turbine (TorC), the centrifugal compressor (C) being provided with at least a control system (20) of the absorbed power. The control method of the rotation speed of the turbine-centrifugal compressor group performs the following steps: —acting on the centrifugal compressor control system (20) of the absorbed power by means of a first controller (PID-f), in order to keep constant the rotational speed of the compressor mechanically coupled to the expansion turbine; —ensuring that the centrifugal compressor (C) remains in a stable operating condition by means of an admission valve (Vi) of the expansion turbine (TorC).
    Type: Grant
    Filed: July 25, 2017
    Date of Patent: January 5, 2021
    Assignee: TURBODEN S.P.A.
    Inventors: Roberto Bini, Mario Gaia
  • Patent number: 10871144
    Abstract: The present disclosure is directed to a method for reducing loads of a wind turbine. The method includes monitoring, via a turbine controller, a rotor blade of the wind turbine for faults. If a fault is detected, the method includes determining an operational status of the wind turbine. If a predetermined operational status is present at the same time the fault is present, the method also include actively yawing a nacelle of the wind turbine away from an incoming wind direction until either the fault is corrected or cleared and/or the operational status changes.
    Type: Grant
    Filed: May 21, 2018
    Date of Patent: December 22, 2020
    Assignee: General Electric Company
    Inventors: Santiago Tomas, Jeffrey Alan Melius, Ramy Michael Souri, Jignesh Govindlal Gandhi, Edward Way Hardwicke, Jr., Darren John Danielsen
  • Patent number: 10865803
    Abstract: An impeller wheel of a turbocompressor, for rotation about an axis, has an inflow cross-section for inflow of a process fluid into the impeller wheel, an outflow cross-section for outflow of the process fluid from the impeller wheel, a wheel disk that defines a hub-side deflection contour from the axial flow direction into the radial flow direction. Blades are applied to the wheel disk, which define flow channels through the impeller wheel, each blade defining a linear inner track and a linear outer track. A meridional angle is defined for each position of a track as the upstream included angle between a meridional plane through the position and a tangent on the track. So that the flow passes through the impeller wheel with improved efficiency, as far as possible without separation, a local extremum of the meridional angle of the inner track is defined.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: December 15, 2020
    Inventor: Christian Woiczinski
  • Patent number: 10858996
    Abstract: A gas turbine startup method and device wherein low-pressure, medium-pressure, and high-pressure air bleed flow paths supply compressed air bled from low-pressure, medium-pressure, and high-pressure air bleed chambers, respectively, of a compressor as cooling air to a turbine. Low-pressure, medium-pressure, and high-pressure exhaust flow paths discharge the compressed air in the low-pressure, medium-pressure, and high-pressure air bleed flow paths, respectively to the turbine exhaust system, and the low-pressure, the medium-pressure, and the high-pressure exhaust flow paths are provided respectively with a low-pressure exhaust valve, a medium-pressure exhaust valve, and a high-pressure exhaust valve. When the gas turbine starts up, the high-pressure exhaust valve is opened before the startup state of the gas turbine reaches a region in which rotation stall occurs.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: December 8, 2020
    Inventors: Hidetaka Okui, Kentaro Suzuki, Toshishige Ai, Tatsuya Iwasaki, Yoshifumi Okajima
  • Patent number: 10859087
    Abstract: A method of preventing surge in a dynamic compressor is disclosed. The method includes providing an anti-surge valve having an adjustable opening for increasing the flow through a dynamic compressor. The next step is sensing process conditions in the dynamic control to determine a compressor load variable. A control system estimates a process disturbance model using the compressor load variable. The control system then adjusts a safety margin using a rate limited response and initiates a closed loop response using process feedback based on the process disturbance model. The control system adjusts the opening of the anti-surge valve according to the safety margin and closed loop response.
    Type: Grant
    Filed: July 21, 2015
    Date of Patent: December 8, 2020
    Assignee: Energy Control Technologies, Inc.
    Inventors: Krishnan Narayanan, Paul Reinke, Nikhil Dukle
  • Patent number: 10830053
    Abstract: An apparatus and method regarding an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction, at least one cooling passage extending radially within the interior and defining a primary cooling airflow, and at least one cooling hole having an inlet in communication with the cooling passage and an outlet in communication with the exterior of the outer wall.
    Type: Grant
    Filed: November 20, 2017
    Date of Patent: November 10, 2020
    Assignee: General Electric Company
    Inventors: Gregory Terrence Garay, Zachary Daniel Webster, Kirk D. Gallier
  • Patent number: 10830254
    Abstract: A blower having high efficiency and low noise by actively controlling airflow in the blower, and an air conditioner having the blower is provided. The air conditioner has a blower. The blower includes a fan having a hub and at least one blade provided on an outer circumferential surface of the hub, a motor to rotatably drive the hub, a shroud configured to surround the periphery of the fan and at least one actuator installed in the shroud and configured to form an airflow along an inner circumferential surface of the shroud.
    Type: Grant
    Filed: May 11, 2018
    Date of Patent: November 10, 2020
    Inventor: Shinji Goto
  • Patent number: 10823196
    Abstract: The diffuser pipe assembly for a compressor of a gas turbine engine includes diffuser pipes circumferentially distributed around a central axis and configured for distributing a flow of compressed air from the compressor to the combustor. Each of the diffuser pipes curving between an inlet end and an outlet end. A first subset of the diffuser pipes has a natural vibration frequency different than a natural vibration frequency of at least a second subset of the diffuser pipes. A method of operating a compressor including the diffuser pipe assembly is also disclosed.
    Type: Grant
    Filed: August 10, 2018
    Date of Patent: November 3, 2020
    Inventors: Ignatius Theratil, Krishna Prasad Balike, Aldo Abate
  • Patent number: 10823184
    Abstract: A turbine engine with a stator having axially spaced first and second structural elements along with a rotor and a face seal between the rotor and the stator including a non-rotating gas bearing face coupled to the first and second structural elements, and a rotating gas bearing face coupled to the rotor and confronting the non-rotating gas bearing surface. Introducing airflow to one or multiple parts of the seal.
    Type: Grant
    Filed: July 28, 2016
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Arnab Sen, Mohamed Musthafa Thoppil, Nathan Evan McCurdy Gibson
  • Patent number: 10823054
    Abstract: The invention is applicable to industrial gas turbines to reduce the load consumed by the gas turbine compressor and to maximize the turbine mass flow.
    Type: Grant
    Filed: May 30, 2013
    Date of Patent: November 3, 2020
    Inventor: Fuad Al Mahmood
  • Patent number: 10801349
    Abstract: A blade outer air seal (BOAS) includes a tube of a ceramic matrix composite (CMC) material. A preform within the shell defines a mount for the BOAS. The preform is of a CMC material. A gas turbine engine and a method of forming a blade outer air seal (BOAS) are also disclosed.
    Type: Grant
    Filed: August 25, 2017
    Date of Patent: October 13, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Michael G. McCaffrey
  • Patent number: 10801355
    Abstract: A turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor.
    Type: Grant
    Filed: October 29, 2018
    Date of Patent: October 13, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, William G. Sheridan, Michael E. McCune, Gabriel L. Suciu
  • Patent number: 10794213
    Abstract: A compressor shroud assembly in a turbine engine having a dynamically moveable shroud for encasing a rotor segment. The rotor segment comprises a bladed disc. The compressor shroud assembly maintains a clearance gap between the shroud and the blade tips of the bladed disc. The assembly comprises a static compressor casing, a shroud mounted to the casing, and an actuator mounted to the casing. The shroud comprises a flowpath boundary member spaced radially inward from the casing, the flowpath boundary member being moveable relative to the casing in a radial direction. The actuator is coupled to the shroud for effecting the movement of the flowpath boundary member.
    Type: Grant
    Filed: January 4, 2017
    Date of Patent: October 6, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Douglas D. Dierksmeier, Edward C. Rice, Ryan C. Humes
  • Patent number: 10774661
    Abstract: An interlocking shroud assembly for a turbine engine includes at least two shroud elements, each having confronting radial ends that define a split interface with axial fore, aft, and circumferential portions.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: September 15, 2020
    Inventors: Fatih Sari, Alkim Deniz Senalp, Sang Yeng Park
  • Patent number: 10760580
    Abstract: Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.
    Type: Grant
    Filed: February 26, 2018
    Date of Patent: September 1, 2020
    Inventors: Bruce David Reynolds, Nick Nolcheff
  • Patent number: 10746041
    Abstract: A shroud assembly may comprise a first ring, a second ring aft of the first ring, and a shroud disposed between the first ring and the second ring. The shroud may comprise a plurality of circumferentially adjacent shroud segments. Each shroud segment of the plurality of circumferentially adjacent shroud segments may extend axially from the first ring to the second ring.
    Type: Grant
    Filed: January 10, 2019
    Date of Patent: August 18, 2020
    Inventors: Tushar M. Patel, Valeriy Krutiy, Ahamed Foliq Ahamed Laikali, Saikumar Jupally, Gurjeet Singh, Sidda Basha Dudekula
  • Patent number: 10746036
    Abstract: A low-pressure compressor for a turbine engine, such as an aircraft turbojet engine includes a rotor with two rows of rotor blades between which two annular ribs are positioned; and one annular row of stator blades between the rotor blades. An internal shroud is connected to the stator blades. The internal shroud includes abradable material collaborating with the annular ribs, and annular teeth made of an abradable material and which extend radially towards the rotor, so as to provide sealing. The system may be used in a method for manufacturing a bypass turbojet engine compressor.
    Type: Grant
    Filed: May 31, 2018
    Date of Patent: August 18, 2020
    Inventor: Stéphane Hiernaux
  • Patent number: 10738698
    Abstract: A method of operating a multi-engine, rotary wing aircraft in a single engine, in-flight mode, the method includes stopping a first engine while operating a second engine; closing variable inlet guide vanes on the first engine; and turning a gas generator of the first engine at a reference rotational speed.
    Type: Grant
    Filed: March 22, 2016
    Date of Patent: August 11, 2020
    Inventor: Joseph Lawrence Simonetti
  • Patent number: 10731504
    Abstract: An electric actuator for inlet guide vanes of a gas turbine engine, the electric actuator including a fixed portion secured to a stationary portion of the engine and a movable portion that is mechanically connected to the inlet guide vanes, stationary electromagnets distributed at regular intervals around the periphery of the movable portion and fastened to the fixed portion, and movable electromagnets arranged between the stationary electromagnets, each movable electromagnet being secured on either side to first and second piezoelectric elements, the movable electromagnets and the first and second piezoelectric elements having a degree of freedom of movement relative to the movable portion and having inside faces forming a common line of contact that is tangential to the movable portion.
    Type: Grant
    Filed: August 24, 2017
    Date of Patent: August 4, 2020
    Inventors: Jean-Julien Camille Vonfelt, Thomas Klonowski, Antoine Moutaux
  • Patent number: 10724542
    Abstract: An air moving device includes a housing member, an impeller assembly, and a nozzle assembly. The nozzle assembly can include one or more angled vanes set an angle with respect to a central axis of the air moving device. The air moving device can output a column of moving air having an oblong and/or rectangular cross-section. A dispersion pattern of the column of moving air upon the floor of an enclosure in which the air moving device is installed can have an oblong and/or rectangular shape. The dimensions of the dispersion pattern may be varied by moving the air moving device toward or away from the floor, and/or by changing the angles of the stator vanes within the nozzle assembly.
    Type: Grant
    Filed: January 17, 2019
    Date of Patent: July 28, 2020
    Assignee: Airius IP Holdings, LLC
    Inventor: Raymond B. Avedon
  • Patent number: 10704391
    Abstract: A small aero gas turbine engine with an axial thrust limiter device that uses compressed air acting on a rotating disk extending from a rotor of the engine in which a forward pressure chamber and an aft pressure chamber applies a pressure to both sides of the rotating disk. When rotor is shifted, one side of the rotating disk has an increase in pressure acting on it to shift the rotor in an axial direction. Each pressure chamber includes an upper variable restriction and a lower variable restriction in which the restriction varies due to axial movement of the rotor. A forward and an aft foil bearing can also be used in addition to axial balance the rotor when not enough pressure is available such as at engine startup.
    Type: Grant
    Filed: May 24, 2017
    Date of Patent: July 7, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Joseph Brostmeyer
  • Patent number: 10697423
    Abstract: A method to dispose at least one air guiding tube between a penstock and a water turbine installed on a dam to form negative pressure at an outlet of the air guiding device by the water kinetic energy produced from high speed of water flow to take in external air for pressurizing, so as to produce a plurality of pressured air bubbles mixed into the water. The water with pressured air bubbles would be decompressed when flowing to an exit of the penstock and has their volumes increased, so as to enhance the water kinetic energy for driving the water turbine more efficiently; meanwhile the method can prevent from production of cavities and further avoid damages of the components of the water turbine from cavitation.
    Type: Grant
    Filed: November 6, 2018
    Date of Patent: June 30, 2020
    Inventor: Zuei-Ling Lin
  • Patent number: 10690081
    Abstract: Diagnostic systems and methods for a surge valve that selectively bypasses a compressor of a turbocharger of an engine involve receiving, by a controller, a barometric pressure signal indicative of a barometric pressure external to the engine, receiving, by the controller, a throttle inlet pressure (TIP) signal indicative of an air pressure at an inlet of a throttle valve of the engine and downstream from the surge valve and the compressor, and performing, by the controller, a diagnostic technique on the surge valve, the diagnostic technique comprising generating a pressure ratio signal that is a ratio of the TIP signal to the barometric pressure signal, applying a high-pass filter to the pressure ratio signal to obtain a filtered pressure ratio signal, and based on a quantity of detected pulses in the filtered pressure ratio signal that exceed the diagnostic threshold, detecting a malfunction of the surge valve.
    Type: Grant
    Filed: April 23, 2018
    Date of Patent: June 23, 2020
    Assignee: FCA US LLC
    Inventors: Scott E Henson, Amarjeet Singh Sahota, Dhaval D Shah
  • Patent number: 10683798
    Abstract: The present invention provides a turbocharger including: a rotating shaft; a turbine wheel; a compressor wheel; a rolling bearing including an inner race fixed to an outer circumferential surface of the rotating shaft, an outer race surrounding the inner race from the outside in a radial direction, and rolling bodies arranged between the inner and outer races and that supports the rotating shaft to be rotatable about an axis; a housing that covers the rolling bearing from an outer circumferential side via a gap between the housing and an outer circumferential surface of the rolling bearing; and a lubricant supply line configured to supply a lubricant into the housing. The turbocharger includes an operating state detection unit that detects an operating state of the turbocharger and a lubricant regulating unit configured to regulate the flow rate of the lubricant flowing through the lubricant supply line depending on the operating state.
    Type: Grant
    Filed: December 4, 2015
    Date of Patent: June 16, 2020
    Inventors: Yoshitomo Noda, Motoki Ebisu, Hiroshi Suzuki