Air And Diverse Fluid Discharge From Separate Discharge Outlets (e.g., Fan Jet, Etc.) Patents (Class 60/226.1)
  • Patent number: 10815892
    Abstract: A multiflow turbojet engine generally includes an upstream fan driven by a gas generator having first and second coaxial compressors, an intake case forming a mounting for the rotors of the upstream fan and the first compressor, an inter-compressor case downstream from the intake case and forming a mounting for the rotors of the second compressor, and attachment means for thrust take-up control rods arranged in the inter-compressor case. The turbojet engine also includes a structural force shroud connecting the intake case to the inter-compressor case, of the and a floating first compressor case.
    Type: Grant
    Filed: December 12, 2016
    Date of Patent: October 27, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Michel Gilbert Roland Brault, Nils Edouard Romain Bordoni, Romain Guillaume Cuvillier, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski
  • Patent number: 10814996
    Abstract: A nacelle may comprise a fan cowl and a tie rod assembly coupled to the fan cowl. The tie rod assembly may comprise a first tie rod coupled to the fan cowl and a second tie rod coupled to the first tie rod and the fan cowl. Rotational motion may be transferred between the first tie rod and the second tie rod. A retention structure may be coupled to an interior surface of the fan cowl.
    Type: Grant
    Filed: October 10, 2018
    Date of Patent: October 27, 2020
    Assignee: ROHR, INC.
    Inventors: Stuart J. Byrne, Thomas Paolini
  • Patent number: 10794273
    Abstract: A gas turbine engine according to the present disclosure includes a first compressor and a first turbine for driving the first compressor. A core section includes a second compressor and a second turbine for driving the second compressor. A third turbine is arranged fluidly downstream of the first turbine and the second turbine and configured to drive a power take-off. A first duct system is arranged fluidly between the low-pressure compressor and the core section. The first duct system is arranged to reverse fluid flow before entry into the core section.
    Type: Grant
    Filed: July 1, 2015
    Date of Patent: October 6, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Jeffery F. Perlak, Joseph B. Staubach, Gabriel L. Suciu, James D. Hill, Frederick M. Schwarz
  • Patent number: 10794272
    Abstract: A turbine engine includes a compressor section including a compressor, the compressor including an axial compressor stage, a variable outlet guide vane, and a centrifugal compressor stage, the variable outlet guide vane positioned between the axial compressor stage and the centrifugal compressor stage; a bleed assembly including a bleed airflow duct in airflow communication with the compressor and a bleed valve operable with the bleed airflow duct, the bleed valve including a bleed valve actuator; and a linkage assembly coupling the bleed valve actuator with the variable outlet guide vane such that that variable outlet guide vane is moveable with the bleed valve.
    Type: Grant
    Filed: February 19, 2018
    Date of Patent: October 6, 2020
    Assignee: General Electric Company
    Inventor: Timothy Joseph Higgins
  • Patent number: 10794218
    Abstract: A hub of an intermediate casing for a dual-flow turbine engine includes a discharge flow duct extending between an inner shroud and an outer shroud of the hub, the discharge flow duct leading into the secondary flow space through an outlet opening formed in the outer shroud, the outlet opening included in a discharge plane substantially tangential to the outer shroud; and discharge fins including an upstream fin and a downstream fin. An upstream acute angle between the discharge plane and the skeleton line of the upstream fin is smaller than a downstream acute angle between the discharge plane and the skeleton line of the downstream fin.
    Type: Grant
    Filed: March 31, 2016
    Date of Patent: October 6, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Jean-Frederic Pierre Joseph Bruhat, Philippe Jacques Pierre Fessou, Benjamin Lukowski
  • Patent number: 10787962
    Abstract: An aircraft propulsion unit including two distinct fan spools, and including a first duct and a second duct extending downstream of the two fan spools, the propulsion unit including a control ring disposed on one of the ducts, downstream of one of the fan spools, with at least one annular internal wall extending in an interior space of the duct, the control unit of the control ring being configured to modify the shape of the internal wall, and to cause an air passage cross section in the duct to vary at the ring, a device for acquiring acoustic signals generated by acoustic waves propagating downstream of the fan spools, and a device for processing the acoustic signals, configured to measure a dephasing between the acoustic waves and to control the control ring depending on the dephasing.
    Type: Grant
    Filed: July 31, 2018
    Date of Patent: September 29, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Jean Michel Roux, Norman Bruno André Jodet, Laurent Louis Robert Baudoin
  • Patent number: 10787969
    Abstract: A front part of an aircraft turbomachine of the bypass type including a single fan, a gas generator positioned downstream of the fan, a reducer interposed between the gas generator and the fan, a flow splitter and a structure with structural outlet guide vanes. The vanes each have a root arranged upstream of the flow splitter and the reducer is also arranged at least half upstream of the flow splitter.
    Type: Grant
    Filed: November 14, 2016
    Date of Patent: September 29, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Kevin Morgane Lemarchand, Michel Gilbert Roland Brault, Guillaume Olivier Vartan Martin
  • Patent number: 10781749
    Abstract: A boundary layer ingestion engine includes a gas generator and a turbine fluidly connected to the gas generator. A fan is mechanically linked to the turbine via a shaft such that rotation of the turbine is translated to the fan. A boundary layer ingestion inlet is aligned with an expected boundary layer, such that the boundary layer ingestion inlet is configured to ingest fluid from a boundary layer during operation of the boundary layer ingestion engine.
    Type: Grant
    Filed: December 7, 2016
    Date of Patent: September 22, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler
  • Patent number: 10767559
    Abstract: A particle separator adapted for use with a gas turbine engine includes an adaptive-area hub, an outer wall, and a splitter. The splitter cooperates with the adaptive-area hub and the outer wall to separate particles suspended in an inlet flow moving through the particle separator to provide a clean flow of air to the gas turbine engine.
    Type: Grant
    Filed: June 27, 2018
    Date of Patent: September 8, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Crawford F. Smith, III, Bryan H. Lerg, Kenneth M. Pesyna
  • Patent number: 10767486
    Abstract: An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an annular shroud having a radially inner face and a radially outer face opposing the radially inner face, a radially inner array of airfoils extending from the radially inner face, and a radially outer array of airfoils extending from the radially outer face. The radially inner array of airfoils are configured to guide flow within a radially inner bypass flow passage, the radially inner bypass flow passage bypassing and being radially outward of a compressor section. At least one, but fewer than each, airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils, and the remaining airfoils in the radially inner array of airfoils are misaligned with the airfoils of the radially outer array of airfoils. A method of reducing a vibratory response of airfoils is also disclosed.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: September 8, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Richard K. Hayford, Steven J. Ford
  • Patent number: 10760439
    Abstract: A method of testing the integrity of a fluid flow regulator system for a turbine engine, the system including a fluid-passing duct associated with a movable flap; an actuator having a movable drive element suitable for delivering a movement force between a first position corresponding to the closed position of the movable flap and a second position corresponding to the open position of the movable flap; a push-pull cable interconnecting the drive element and the movable flap; and return device exerting a return force for moving the flap; the method of testing the integrity of the system including in succession: a step of supplying power to the actuator in order to place the drive element in the second position; a step of interrupting the supply of power; and a step of measuring the position of the drive element.
    Type: Grant
    Filed: June 8, 2017
    Date of Patent: September 1, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clementine Morisot, Benoit Michel Pontallier
  • Patent number: 10760501
    Abstract: To facilitate the removal of a bearing housed in an arm of a turbomachine casing, which bearing guides a transmission shaft of the turbomachine, a casing arm includes a body with a vertical portion and a base defining a portion of a shaft housing; an additional part removably attached to the body and defining a bearing housing opening in the shaft housing; and a removable shim inserted between the base and the additional part. A turbomachine including such a casing arm is also described, as well as a method for removing the bearing from such a turbomachine, including removing the shim and moving the additional part towards the base, thereby allowing access to the bearing.
    Type: Grant
    Filed: April 27, 2017
    Date of Patent: September 1, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sebastien Nicolas Juigne, Kevin Michael Robert Contal, Mathieu Gaillot, Francois Marie Paul Marlin, Steve Marcel Nicaise
  • Patent number: 10753315
    Abstract: The present disclosure relates to a rear assembly of a turbojet engine nacelle that includes a thrust reverser fixed structure having at least one half-cowl mounted on a beam pivotally hinged by at least one hinge, a suspension mast on which the fixed structure is movably mounted, a hatch for access to the hinge of the half-cowl, and a fireproof sealing device which includes a sealing gasket adapted to provide sealing between a median section of the nacelle and the beam area. The sealing gasket includes a tubular gasket type lower portion which extends at least partially over a seal bearing edge of the half-cowl that is adapted to cooperate with a seal bearing wall of the mast and an upper portion including an elastically deformable sealing sheet extending from the seal bearing wall of the mast to the rear face of the hatch for access to the hinge.
    Type: Grant
    Filed: January 14, 2019
    Date of Patent: August 25, 2020
    Assignee: Safran Nacelles
    Inventors: Jean-Philippe Joret, Jérôme Corfa, Serge Bunel, Xavier Bouteiller
  • Patent number: 10737801
    Abstract: A fan module for an aircraft is disclosed herein. The fan module includes a fan rotor, a vane ring, and an optional power supply system. The fan rotor is configured to discharge thrust in an aft direction when rotated about a central axis. The vane ring is located aft of the fan rotor along the central axis and mounted for rotation about the central axis. The vane ring includes a plurality of airfoils arranged to interact with the thrust discharged by the fan rotor so that the thrust drives rotation of the vane ring.
    Type: Grant
    Filed: October 31, 2016
    Date of Patent: August 11, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Jonathan S. Sands, Richard K. Keller
  • Patent number: 10738694
    Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a fan including a plurality of fan blades rotatable about an axis, a plurality of inlet guide vanes mounted forward of the plurality of fan blades, the plurality of inlet guide vanes selectively rotatable about the axis independent of the plurality of fan blades; and a motor for controlling rotation of the plurality of inlet guide vanes about the axis.
    Type: Grant
    Filed: August 23, 2018
    Date of Patent: August 11, 2020
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Dmitriy B. Sidelkovskiy, Neil Terwilliger, William G. Sheridan
  • Patent number: 10738703
    Abstract: A gas turbine engine includes a plurality of rotating components housed within a main compressor section and a turbine section. A first tap is connected to the main compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A cooling air valve is configured to selectively block flow of cooling air across the heat exchanger. A cooling compressor is connected downstream of the heat exchanger. A shut off valve stops flow between the heat exchanger and the cooling compressor. A second tap is configured to deliver air at a second pressure which is higher than the first pressure. A mixing chamber is connected downstream of the cooling compressor and the second tap. The mixing chamber is configured to deliver air to at least one of the plurality of rotating components. A system stops flow between the cooling compressor and the plurality of rotating components.
    Type: Grant
    Filed: March 22, 2018
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, Nathan Snape
  • Patent number: 10731560
    Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap and configured to deliver air to an aircraft fuselage. A cooling compressor is connected downstream of the heat exchanger. A high pressure feed is configured to deliver air at a second pressure which is higher than the first pressure. The cooling compressor is configured to deliver air to at least one of the plurality of rotating components. A valve assembly that can select whether air from the first tap or air from the high pressure feed is delivered to the aircraft pneumatic system.
    Type: Grant
    Filed: February 28, 2018
    Date of Patent: August 4, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Nathan Snape, Gabriel L. Suciu, Brian Merry, Jesse M. Chandler, Frederick M. Schwarz
  • Patent number: 10730636
    Abstract: An integrated aircraft cooling system comprising a turbine engine and a plurality of secondary cooling streams, wherein the turbine engine core exhaust stream drives the plurality of secondary cooling streams. A core exhaust stream outlet has a periphery and a composite secondary outlet positioned around the periphery of the core exhaust stream outlet, and the composite secondary outlet is segregated between the plurality of secondary streams. Each of the secondary flows are in fluid isolation from each other upstream of the composite secondary outlet.
    Type: Grant
    Filed: July 18, 2016
    Date of Patent: August 4, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Bryan H. Lerg, Kenneth M. Pesyna, Nilesh Shah, Douglas J. Snyder
  • Patent number: 10724402
    Abstract: A duct liner assembly for a gas turbine engine includes a first ring and a second ring. Also included is a first duct liner having a first end and a second end, the first duct liner mounted proximate the first end of the first duct liner to the first ring. Further included is a second duct liner having a first end and a second end, the second duct liner mounted proximate the second end of the second duct liner to the second ring. Yet further included is a coupling assembly including a threaded insert, a retaining bracket, and a threaded fastener extending through the retaining bracket and in threaded engagement with the threaded insert to couple the retaining bracket to the second duct liner.
    Type: Grant
    Filed: June 26, 2017
    Date of Patent: July 28, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Rigels Bejleri, Patrick M. Devaney
  • Patent number: 10718271
    Abstract: A power extraction and amplification system for a gas turbine engine is disclosed. In various embodiments, the power extraction and amplification system includes a low spool tower shaft configured for engagement with a low speed spool, a high spool tower shaft configured for engagement with a high speed spool, a first motor, a generator, a differential gear box operably coupled to the low spool tower shaft, to the first motor and to the generator, and a second motor operably coupled to the generator and the high spool tower shaft.
    Type: Grant
    Filed: May 29, 2018
    Date of Patent: July 21, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, William G Sheridan
  • Patent number: 10717543
    Abstract: Apparatus and methods for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft are disclosed. The apparatus includes a rotor shaft coupled the bladed rotor of the aircraft and driven by a turbine shaft of the engine via a speed-reducing gear train. A speed-augmenting power transfer device has an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device. An electric generator disposed in a hub of the bladed rotor is coupled to the output of the speed-augmenting power transfer device and configured to generate electrical power for the device associated with the bladed rotor.
    Type: Grant
    Filed: October 30, 2017
    Date of Patent: July 21, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lazar Mitrovic, Richard Ullyott
  • Patent number: 10703475
    Abstract: An unmanned aerial vehicle includes a tubular base structure, a motor having a stator, the stator being connected to the tubular base structure, an energy storage module configured to supply power to the motor, and at least one propeller driven by the motor, wherein the tubular base structure houses at least one cable for routing power or signals, or a fuel conduit or wire conduit.
    Type: Grant
    Filed: April 21, 2017
    Date of Patent: July 7, 2020
    Assignee: UVIONIX AEROSPACE CORPORATION
    Inventors: Yordan Iskrev, Boris Iskrev
  • Patent number: 10697374
    Abstract: A gas turbine engine includes an inlet duct to guide a core engine flow to a compressor and an engine section stator arranged in the inlet duct upstream of the compressor including vanes with leading edges defining a first annulus area in the inlet duct, a mid-span leading edge point of the engine section stator vanes being arranged at a first radius. The compressor includes a first rotor with a row of first blades with leading edges defining a second annulus area; a mid-span leading edge point of the compressor first blades being arranged at a second radius and an axial distance from the engine section stator vane mid-span leading edge point. The ratio of the second to the first annulus area is equal or greater than 0.75, and the ratio of a difference between the first and second radius to the axial distance is equal or greater than 0.23.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: June 30, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventor: Ian J Bousfield
  • Patent number: 10677158
    Abstract: A gas turbine engine system and method of operating gas turbine engines are provided. The gas turbine engine assembly includes a gas turbine engine includes a power shaft configured to rotate about an axis of rotation. The gas turbine engine assembly also includes a first fan and a second fan coupled to the power shaft coaxially with the gas turbine engine. The gas turbine engine assembly also includes a first fan duct configured to direct a first stream of air to the first fan. The gas turbine engine assembly also includes a second fan duct configured to direct a second stream of air to the second fan. The gas turbine engine assembly also includes an exhaust duct configured to direct a stream of exhaust gases of the gas turbine engine in a direction of the axis of rotation.
    Type: Grant
    Filed: December 29, 2015
    Date of Patent: June 9, 2020
    Assignee: General Electric Company
    Inventors: Brandon Wayne Miller, Narendra Digamber Joshi, Ian Francis Prentice, Kurt David Murrow
  • Patent number: 10677103
    Abstract: The present invention is a system and method of power medium expansion that functions with a rate of efficiency higher than systems found in prior art. Novel features of the system increase the overall efficiency with the use of a power medium that begins the cycle in the liquid state and enters the gaseous state. An additional novel feature is the use of additional heat that may also increase the overall cycle efficiency. Another additional novel feature is recuperating energy that can supplement the phase change of the power medium along with isolating the components from the ambient.
    Type: Grant
    Filed: September 5, 2018
    Date of Patent: June 9, 2020
    Inventor: Mark Cann
  • Patent number: 10676205
    Abstract: A propulsion system for an aircraft includes an electric propulsion engine. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis of the electric propulsion engine by the electric motor. The electric propulsion engine also includes a bearing supporting rotation of the fan and a thermal management system. The thermal management system includes a lubrication oil circulation assembly and a heat exchanger thermally connected to the lubrication oil circulation assembly. The lubrication oil circulation assembly is configured for providing the bearing with lubrication oil. Such an electric propulsion engine may be a relatively self-sufficient engine.
    Type: Grant
    Filed: August 19, 2016
    Date of Patent: June 9, 2020
    Assignee: General Electric Company
    Inventors: Daniel Alan Niergarth, Randy M. Vondrell, Brandon Wayne Miller, Patrick Michael Marrinan, Lawrence Chih-hui Cheung, Nikolai N. Pastouchenko
  • Patent number: 10663036
    Abstract: The present disclosure is directed to a gas turbine engine, wherein the gas turbine engine defines a longitudinal direction, a radial direction, and a circumferential direction, and an axial centerline extended along the longitudinal direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes an annular stationary turbine frame centered around the axial centerline; an engine shaft extended generally along the longitudinal direction; an input shaft extended generally along the longitudinal direction; and a gear assembly including a first gear coupled to the input shaft, a second gear coupled to the turbine frame, and an inner spool coupling the first gear and the second gear, in which the inner spool defines a gear axis extended therethrough. The inner spool, the first gear, and the second gear are together rotatable about the gear axis. The gear axis is rotatable about the axial centerline of the engine.
    Type: Grant
    Filed: June 13, 2017
    Date of Patent: May 26, 2020
    Assignee: General Electric Company
    Inventors: Alan Roy Stuart, Darek Tomasz Zatorski
  • Patent number: 10655538
    Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.
    Type: Grant
    Filed: September 27, 2018
    Date of Patent: May 19, 2020
    Assignee: United Technologies Corporation
    Inventors: Jonathan Gilson, Bruce L. Morin, Ramons A. Reba, David A. Topol, Wesley K. Lord
  • Patent number: 10648356
    Abstract: A bypass turbine engine is described. The engine includes a system for bleeding gas from a primary stream to a secondary stream. The system may include two coaxial rings extending one around the other. A perforated internal first ring may be situated at the level of an outer casing and may extend substantially in a continuation of the outer casing. A perforated external second ring may be mounted such that it slides circumferentially on the first ring between a first position in which the perforations of the rings do not communicate with one another and a second bleed position in which the perforations of the rings communicate with one another.
    Type: Grant
    Filed: November 16, 2017
    Date of Patent: May 12, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Eric Pierre Georges Le Marechal, Xavier Jean Yves Alain Agneray, Thierry Georges Paul Papin, Mathieu Daniel Marie Van Gansen, Cédric Zaccardi
  • Patent number: 10640222
    Abstract: The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.
    Type: Grant
    Filed: October 10, 2017
    Date of Patent: May 5, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nora El Ghannam, Matthieu Etienne Attali, Romain Jean-Claude Ferrier, Caroline Marie Frantz, Thomas Gerard Daniel Riviere, Nicolas Xavier Trappier
  • Patent number: 10641128
    Abstract: A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. An oil tank is mounted to at least one of the fan case or the front and aft mount flanges. The oil tank has a cooling structure integrated into an outer surface such that the oil tank is subjected to cooling air flow from a plurality of air sources.
    Type: Grant
    Filed: March 7, 2018
    Date of Patent: May 5, 2020
    Assignee: United Technologies Corporation
    Inventors: Nathan Snape, Gabriel L. Suciu, Simon Pickford
  • Patent number: 10619853
    Abstract: A micro turbine generator includes a compressor, a guide channel, an expansion chamber, and a recuperator. The expansion chamber includes an air inlet, an air outlet, and a guide vane structure. The air inlet is disposed at one end of the expansion chamber, connected with the compressor through the guide channel, and receives an air compressed by the compressor. The air outlet is disposed at the other end of the expansion chamber, connected with the recuperator, and discharges the air, allowing the air to enter the recuperator. The guide vane structure extends inward from an inner wall of the expansion chamber to allow the air to pass the guide vane structure before being discharged from the air outlet to enter the recuperator.
    Type: Grant
    Filed: December 20, 2016
    Date of Patent: April 14, 2020
    Assignee: NATIONAL CHUNG SHAN INSTITUTE OF SCIENCE AND TECHNOLOGY
    Inventors: Yung-Mao Tsuei, Chih-Chuan Lee
  • Patent number: 10605165
    Abstract: An aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan from outside in a radial direction of the rotating shaft; a nose cone (13) disposed upstream of the fan; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) that transmits motive force of the rotating shaft to the fan; and a support member (12) disposed inward of the first motive force transmitter in the radial direction, the support member coupling the nose cone to the casing such that the support member supports the nose cone in a stationary state.
    Type: Grant
    Filed: November 4, 2015
    Date of Patent: March 31, 2020
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Akihito Abe, Tatsuhiko Goi, Masahide Kazari, Hidenori Arisawa
  • Patent number: 10591047
    Abstract: An epicyclic gear train for a gas turbine engine according to an example of the present disclosure includes, among other things, a gutter having an annular channel, a sun gear rotatable about an axis, intermediary gears arranged circumferentially about and meshing with the sun gear, and a carrier supporting the intermediary gears, and a ring gear arranged about and intermeshing with the intermediary gears, the ring gear having an aperture axially aligned with the annular channel. The ring gear includes axially spaced apart walls that extend radially outward to define a passageway, and the passageway is arranged radially between the aperture and the annular channel such that the walls inhibit an axial flow of an oil passing from the aperture toward the annular channel.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: March 17, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael E. McCune, Lawrence E. Portlock
  • Patent number: 10584660
    Abstract: An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.
    Type: Grant
    Filed: January 20, 2017
    Date of Patent: March 10, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: William G. Sheridan, Michael E. McCune
  • Patent number: 10577965
    Abstract: A turbine engine according to an example of the present disclosure includes, among other things, a fan shaft, at least one tapered bearing mounted on the fan shaft, the fan shaft including at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing, a fan mounted for rotation on the at least one tapered bearing. An epicyclic gear train is coupled to drive the fan, the epicyclic gear train including a carrier supporting intermediate gears that mesh with a sun gear, and a ring gear surrounding and meshing with the intermediate gears, wherein the epicyclic gear train defines a gear reduction ratio of greater than or equal to 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train, the turbine section having a fan drive turbine that includes a pressure ratio that is greater than 5. The fan includes a pressure ratio that is less than 1.45, and the fan has a bypass ratio of greater than ten (10).
    Type: Grant
    Filed: May 21, 2018
    Date of Patent: March 3, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael E. McCune, Lawrence E. Portlock, Fredercik M. Schwarz
  • Patent number: 10570855
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbo fan shaft and a turbo fan supported on the fan shaft, a compressor section having compressor hubs with blades driven about an axis, and an epicyclic gear system driving the fan shaft. The gear system includes a carrier supporting intermediate gears that mesh with a sun gear, a ring gear surrounding and meshing with the intermediate gears, the ring gear including first and second portions each having an inner periphery with teeth, the first and second portions abutting one another at a radial interface, each of the first and second portions including a flange extending radially outward, and the first and second portions having grooves at the radial interface which form a hole that expels oil through the ring gear to a gutter, and an input shaft driving the fan shaft through the gear system, the input shaft connected to the sun gear.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: February 25, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael E. McCune, Lawrence E. Portlock, Frederick M. Schwarz
  • Patent number: 10566877
    Abstract: A wet cavity electric machine includes a stator core having stator poles formed by a post and a wire wound about the post to form a stator winding, with the stator winding having end turns, a rotor having two rotor poles and configured to rotate relative to the stator and a channel for liquid coolant to flow through the rotor to at least one nozzle, and liquid coolant sprays from the at least one nozzle at least a portion of the stator windings.
    Type: Grant
    Filed: December 21, 2018
    Date of Patent: February 18, 2020
    Assignee: GE Aviation Systems LLC
    Inventors: Lanchao Lin, Hao Huang, Xiaochuan Jia
  • Patent number: 10550700
    Abstract: A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.
    Type: Grant
    Filed: June 11, 2019
    Date of Patent: February 4, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Nicholas Howarth, Gareth M Armstrong
  • Patent number: 10550713
    Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure and front center body case structure rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.
    Type: Grant
    Filed: March 29, 2018
    Date of Patent: February 4, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 10550714
    Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure and the front center body case structure rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.
    Type: Grant
    Filed: March 29, 2018
    Date of Patent: February 4, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 10539153
    Abstract: Bleed air system includes bleed port with annular bleed slot in a compressor inner casing surrounding flowpath circumscribing a centerline in compressor inner casing. Inner and outer slot walls bound bleed flow passage through the bleed slot. Annular array of arcuate shields radially inwardly bound the bleed flow passage downstream and aft of inner slot wall. Each shield includes integrally-formed axially forward retaining portion, downstream portion, and upstream portion therebetween. Clipping means clips retaining portion to aft facing radial wall of annular lip on inner slot wall. Clipping means may be arcuate or annular clip having forward annular portion attached to annular aft flange substantially perpendicular to the centerline and forward annular portion disposed in annular slot extending into inner slot wall. Forward annular portion and annular slot may be cylindrical or conical. Clip may include aft conical portion radially offset from forward conical portion and transition portion therebetween.
    Type: Grant
    Filed: March 14, 2017
    Date of Patent: January 21, 2020
    Assignee: General Electric Company
    Inventors: Michael Anthony Thomas, Abhishek Jayant Patil, Manish Singhal
  • Patent number: 10539156
    Abstract: Disclosed is a flutter damper, including a chamber having an internal space, a movable diaphragm disposed at least partially within the chamber, the diaphragm separating the chamber into a first chamber and a second chamber, the second chamber forming an acoustic volume, wherein a size of the acoustic volume configures the chamber for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and a biasing member that moves the diaphragm responsive to a signal from an aircraft or engine electronic control (EEC) unit, wherein movement of the diaphragm increases or reduces the size of the acoustic volume of the second chamber.
    Type: Grant
    Filed: March 7, 2017
    Date of Patent: January 21, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ian T. Marchaj, Glenn Levasseur
  • Patent number: 10533458
    Abstract: A turbine ventilation structure includes: an exhaust diffuser including inner and outer tubes to form an exhaust passage for exhaust gas; a strut extending across the exhaust diffuser from a housing to support a bearing inside the inner tube; a strut cover in the exhaust passage that covers the strut; and a connecting member disposed downstream of the strut cover and including a hollow portion to connect the housing and the inner tube. The housing includes a first intake port to introduce an air from outside. The strut cover has a discharge hole at a rear edge portion thereof. The turbine ventilation structure includes a first ventilation passage extending from the first intake port through the hollow portion, then extending from an inner end portion of the strut through between the strut and the strut cover, and the discharge hole, into the exhaust passage.
    Type: Grant
    Filed: October 5, 2016
    Date of Patent: January 14, 2020
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Kazuhiko Tanimura, Hiroshi Taki, Katsuyoshi Obayashi, Kei Takashima
  • Patent number: 10513984
    Abstract: In one aspect the present subject matter is directed to a system for suppressing acoustic noise within a combustion section of a gas turbine. The system includes at least one static structure disposed forward of a combustion chamber defined within the combustion section. The static structure at least partially defines a diffuser cavity upstream of the combustion chamber. A baffle plate is coupled to the static structure. The baffle plate and the static structure at least partially define an air plenum within the combustion section forward of the combustion chamber. The baffle plate includes an aperture that provides for fluid communication between the diffuser cavity and the air plenum. The at least one static structure and the baffle plate define a Helmholtz resonator within the combustion section.
    Type: Grant
    Filed: August 25, 2015
    Date of Patent: December 24, 2019
    Assignee: General Electric Company
    Inventors: Kwanwoo Kim, Fei Han, Owen Graham
  • Patent number: 10502095
    Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid-turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid-turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.
    Type: Grant
    Filed: November 1, 2016
    Date of Patent: December 10, 2019
    Assignee: United Technologies Corporation
    Inventors: Paul K. Sanchez, Kalpendu J. Parekh, William A. Daniels, John S. Tu
  • Patent number: 10502143
    Abstract: The present application relates to an axial turbine engine with a turbine, a low-pressure compressor, and a fan. The turbine drives the compressor and the fan via a plurality of epicyclic reducing gears. The rotor of the compressor includes upstream a disc with a row of vanes and downstream a drum with a plurality of rows of vanes. The disc and the drum are connected to different parts of the epicyclic reducing gears, so as to be counter-rotating. The turbine engine includes a row of stator vanes arranged between two rows of rotor blades of the drum of the compressor, so as to straighten the flow and improve the efficiency. The turbine engine includes at least two epicyclic reducing gears, so that the vane rows of the drum turn faster than that downstream, which itself turns faster than the fan.
    Type: Grant
    Filed: September 25, 2015
    Date of Patent: December 10, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Stéphane Hiernaux
  • Patent number: 10502144
    Abstract: A gas turbine engine, in particular an aircraft engine is provided. The gas turbine engine including a geared turbofan arrangement, a propulsive fan and a planetary gearbox being driveably connected with a first shaft on the output side of the planetary gearbox and a second shaft on the input side of the planetary gearbox. The propulsive fan is supported through a front load path and a rear load path, the front load path including a first bearing between the first shaft and a sun gear, the rear load path including a second bearing between the second shaft and a fixed structure of the gas turbine engine. The first shaft including a first portion of the shaft as torque carrying part, wherein the torque carrying part including a torque carrying coupling being connected to the first shaft and to a carrier of the planetary gearbox.
    Type: Grant
    Filed: September 19, 2017
    Date of Patent: December 10, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Dominic Boniface
  • Patent number: 10473035
    Abstract: The present invention relates to an engine (1) with a modular structure comprising a plurality of coaxial modules (A, B, C) with, at one end, a first module (A) comprising a power transmission shaft (3) and a speed reduction gear (7), said power transmission shaft being driven via the speed reduction gear (7) by a turbine shaft (2) secured to one (C) of said coaxial modules that is separate from the first module, the speed reduction gear comprising a drive means (8 and 9) fixed to the turbine shaft (2) and to a journal (13) of a shaft of a low-pressure compressor rotor (1 a), characterized in that it comprises a first nut (16) for fastening the drive means to the journal and a second nut (14) for fastening the drive means to the turbine shaft.
    Type: Grant
    Filed: November 6, 2014
    Date of Patent: November 12, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Roland Gilbert Michel Brault, Nathalie Nowakowski
  • Patent number: 10465561
    Abstract: When cold and in the non-coated state, an aerodynamic profile defining an arm of a structural casing of a turbine having a central hub and a shroud is substantially identical to a nominal profile determined by Cartesian coordinates X,Y,Zadim given in Table 1, in which the coordinate Zadim is a quotient D/H where D is a distance of a point under consideration from a first reference plane P0 situated at a base of the nominal profile, and H is a height of said nominal profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to an axial direction of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: February 22, 2017
    Date of Patent: November 5, 2019
    Assignee: Safran Aircraft Engines
    Inventors: Thomas Michel Mervant, Renaud Gabriel Royan, Pierre Hervé Marche, Vincent Nicolas Leonardon