Patents Examined by Todd E. Manahan
  • Patent number: 11326525
    Abstract: A method of monitoring bleed air provided from a first engine to a second engine of a multi-engine aircraft includes operating the first engine in a powered mode to provide motive power to the multi-engine aircraft; and when the first engine is in the powered mode: actuating an air valve to open an air flow path from a compressor section of the first engine to a plurality of parts of the second engine, after the step of actuating the air valve, determining a change in a temperature in a main gas path of the first engine at a location in the main gas path at or downstream of a combustor of the first engine, and in response to determining that the change is below a threshold, executing an action with respect to the first engine, the air valve, and/or the second engine.
    Type: Grant
    Filed: October 11, 2019
    Date of Patent: May 10, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Patrick Manoukian, Philippe Beauchesne-Martel
  • Patent number: 11326518
    Abstract: A combustor panel arrangement for a gas turbine engine. The combustor panel arrangement includes a first combustor panel that has a first edge. A second combustor panel has a second edge facing the first edge. A first plurality of effusion holes extend through the first edge towards the second edge along a corresponding one of a first plurality of flow paths. A second plurality of effusion holes extend through the second edge along a corresponding one of a second plurality flow paths towards the first edge. The first plurality of flow paths and the second plurality of flow paths are non-intersecting.
    Type: Grant
    Filed: January 24, 2020
    Date of Patent: May 10, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Maleek E. Wedderburn, Nurhak Erbas-Sen, John W. Mubeezi, Fumitaka Ichihashi, Roger O. Coffey
  • Patent number: 11319895
    Abstract: A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool; a structural support housing at least partially enclosing the electric generator, the structural support housing being located within the tail cone; and a mounting system located within the tail cone between the structural support housing and the tail cone, wherein the mounting system attaches the tail cone to the structural support housing.
    Type: Grant
    Filed: March 15, 2019
    Date of Patent: May 3, 2022
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Todd A. Spierling
  • Patent number: 11319884
    Abstract: A distributor valve comprising a second element configured to be displaced relative to a first element, so as to form an overall passage opening of variable fuel passage section corresponding to the intersection of a first passage opening and a second passage opening. The head portion of the second passage opening comprises a first inclination having a first average slope, the intermediate portion of the second passage opening comprises a second inclination having a second average slope strictly greater than said first average slope, and the foot portion of the second passage opening comprises a third inclination having a third average slope, strictly less than said second average slope.
    Type: Grant
    Filed: March 18, 2020
    Date of Patent: May 3, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Regis Michel Paul Deldalle, Pierre Charles Mouton
  • Patent number: 11319899
    Abstract: The invention relates to a module of an aircraft bypass engine including an annular flow path of a secondary flow of gas wherein is mounted an annular row of stator blades configured to straighten the gas flow, an arm extending in the flow path downstream from said annular row of blades and being connected physically to one of the stator blades so as to form a unitary aerodynamic assembly, wherein at least one of the two blades adjacent to the blade of the unitary aerodynamic assembly is of a variable pitch type and capable of being rotationally moved about a substantially radial axis with respect to a longitudinal axis of the engine.
    Type: Grant
    Filed: June 27, 2019
    Date of Patent: May 3, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Paul Antoine Foresto
  • Patent number: 11319897
    Abstract: Provided are an exhaust duct, an exhaust duct assembly, and an aircraft using the exhaust duct. The exhaust duct has a structure that enables combustion gas to be diverged and discharged from an inlet end to a first outlet end and a second outlet end at respective sides of the exhaust duct. The exhaust duct includes a first housing including a first body forming an outer wall of the inlet end, and further includes second bodies respectively extending on respective sides from the first body and respectively forming the first outlet end and the second outlet end; a second housing spaced apart from the first body, forming an inner wall of the inlet end, and extending curvedly toward the second bodies; and a connection housing connecting the first housing to the second housing and including at least one recess portion recessed toward the inlet end.
    Type: Grant
    Filed: March 30, 2020
    Date of Patent: May 3, 2022
    Assignee: HANWHA AEROSPACE CO., LTD.
    Inventors: Young Jung Joo, Hee Yoon Chung, Eray Akcayoz
  • Patent number: 11320144
    Abstract: A combustion chamber assembly group, and a mounting method therefor, includes a combustion chamber for an engine that includes a curved combustion chamber wall extending along two spatial directions, and a combustion chamber shingle affixed at an inner side of the combustion chamber wall and having a shingle edge defining the outer contour of the shingle. For an at least sectional abutment of the shingle edge at the combustion chamber wall with a minimum clamping force in an operational state of the engine, the shingle is mounted to the combustion chamber wall in a mounting state in which the shingle at least at one section of the shingle edge has a curvature with respect to at least one of the spatial directions that differs from the curvature of the combustion chamber wall with respect to this spatial direction.
    Type: Grant
    Filed: March 19, 2019
    Date of Patent: May 3, 2022
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Kay Heinze, Michael Ebel, Igor Sikorski, Manfred Baumgartner, Ivo Szarvasy
  • Patent number: 11319813
    Abstract: A tapering exponential spiral for a gas expander for work extraction or air cooling. A gas compressor to increase the pressure and temperature of air. The compressor-expander forms a single and simple structure. A generator with a disk format using a circle of alternating polarity magnets to induce current in polygon solenoids. A heat turbine, Firefly Electric, is small, simple, and efficient heat engine. A heat pump, Firefly Air, for cooling, refrigeration, water capture, and heating. Solar power can be generated and stored as compress air. A water purifier, Firefly Aqua, to desalinate water by solar power. Sunlight is concentrated by a sun tracking conic reflective surface onto a column of salty water. Solar photovoltaic power can be used to power a spiral compressor to condense low pressure steam. Also, we reuse solar heat by extracting the heat of compressing and condensing steam for evaporating more salty water under reduced pressure.
    Type: Grant
    Filed: August 2, 2017
    Date of Patent: May 3, 2022
    Assignee: MONARCH POWER TECHNOLOGY (HONG KONG) LIMITED
    Inventor: Joseph Y. Hui
  • Patent number: 11319873
    Abstract: A turbo cluster gas turbine system includes: at least one combustor configured to combust a fuel to generate a combustion gas; an output turbine configured to be driven with the combustion gas from the at least one combustor; and a plurality of supercharging systems configured to supply compressed air to be supplied to the at least one combustor, wherein each of the supercharging systems includes: a first turbocharger having a rotation shaft formed separately from a rotation shaft of the output turbine and configured to be driven with the combustion gas from the combustor; a first air line for supplying compressed air compressed by a compressor of the first turbocharger to the combustor; and a first combustion gas line for supplying the combustion gas from the combustor to a turbine of the first turbocharger.
    Type: Grant
    Filed: February 3, 2020
    Date of Patent: May 3, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Ryo Takata, Takao Yokoyama, Kenji Nakamichi, Shinsuke Sato
  • Patent number: 11313560
    Abstract: A combustor assembly for a heat engine is generally provided. The combustor assembly defines a fuel nozzle centerline and a radial direction extended from the nozzle centerline. The combustor assembly includes a fuel nozzle disposed at least partially concentric to the nozzle centerline. The fuel nozzle defines a fuel injection opening. A deflector assembly is defined around the nozzle centerline extended therethrough. The deflector assembly includes a deflector wall extended at least partially along the radial direction. The deflector assembly includes a conical portion defined around the nozzle centerline. The conical portion defines a fuel nozzle opening. A plurality of openings is defined through the conical portion radially adjacent to the fuel injection opening at the fuel nozzle.
    Type: Grant
    Filed: July 18, 2018
    Date of Patent: April 26, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Anne Dord, Nayan Vinodbhai Patel
  • Patent number: 11313440
    Abstract: A star-configuration epicyclic gearbox is shown. It comprises a sun gear (112) for connection with a first shaft (112), a plurality of planet gears (113) intermeshed with the sun gear and located in a static carrier (114), and a ring gear (115) for connection with a second shaft (116) and which is intermeshed with the plurality of planet gears. It further comprises one or more electric machines (117) drivingly connected with a respective one of the plurality of planet gears.
    Type: Grant
    Filed: October 17, 2019
    Date of Patent: April 26, 2022
    Assignee: ROLLS-ROYCE PLC
    Inventor: Giles E Harvey
  • Patent number: 11312664
    Abstract: A ceramic heat shield for a gas turbine. The ceramic heat shield has a ceramic body containing aluminium oxide and has a surface layer of the ceramic body which contains yttrium aluminium garnet as reaction coating material. A gas turbine includes such a ceramic heat shield and a method produces such a ceramic heat shield.
    Type: Grant
    Filed: July 10, 2017
    Date of Patent: April 26, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Friederike Lange, Ivo Krausz, Christian Nikasch
  • Patent number: 11313418
    Abstract: A method of manufacturing a motoring system for a gas turbine engine including the steps of: forming a mechanical shaft fuse, the mechanical shaft fuse including a plurality of through holes; forming an outer housing; installing a reduction gear train into the outer housing, the reduction gear train having an input and an output; operably connecting an electric motor to the input; operably connecting a clutch to the output using the mechanical shaft fuse, the clutch in operation engages and disengages the reduction gear train; operably connecting a starter to the clutch, the starter having an output shaft; and operably connecting an accessory gearbox to the output shaft of the starter. The mechanical shaft fuse in operation shears when torque on the mechanical is greater than or equal to a selected value.
    Type: Grant
    Filed: November 1, 2019
    Date of Patent: April 26, 2022
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Matthew Allen Slayter, Richard Alan Davis, Benjamin T. Harder, James Vandung Nguyen, Paul F. Fox, Jeffrey Todd Roberts, Jeff A. Brown, Brian McMasters, Dwayne Leon Wilson, Daniel Richard Walker
  • Patent number: 11306658
    Abstract: A gas turbine engine includes a compressor section having a high pressure compressor and a core casing surrounding the compressor section and defining an inlet. The gas turbine engine also includes a cooling system for cooling air in or to the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and a fluid line assembly in fluid communication with the fluid tank. The fluid line assembly includes an outlet positioned upstream of the high pressure compressor and downstream of the inlet defined by the core casing for injecting cooling fluid into an airflow upstream of the high pressure compressor.
    Type: Grant
    Filed: May 6, 2020
    Date of Patent: April 19, 2022
    Assignee: General Electric Company
    Inventors: Thomas Ory Moniz, Ann Marie Yanosik, Patrick Sean Sage
  • Patent number: 11300086
    Abstract: A fuel and oil system includes a fuel pump, an oil pump, and a fixed electrical drive. A first electric motor controller of the fuel and oil system supplies a variable electrical drive, and a second electric motor controller supplies a variable electrical drive. The fuel pump is selectively connected to and driven by the first electric motor controller or the second electric motor controller. The oil pump is selectively connected to and driven by the second electric motor controller or the fixed electrical drive.
    Type: Grant
    Filed: March 1, 2017
    Date of Patent: April 12, 2022
    Assignee: ROLLS-ROYCE plc
    Inventors: Gian Incerpi, Edward W Adams
  • Patent number: 11300296
    Abstract: An annular combustion chamber of a turbomachine is described. The combustion chamber has an axis of revolution and is delimited by coaxial internal and external annular walls joined upstream by a bottom of chamber substantially transverse to the walls. In some embodiments, the chamber includes at least one annular deflector placed in the chamber and substantially parallel to the bottom of chamber. The bottom of chamber may have openings adapted to be traversed by air for cooling the deflector. In some embodiments, the bottom of chamber and the deflector include mounting openings for mounting an annular row of injection devices for injecting a mixture of air and fuel into the chamber. At least a portion of the air for cooling the deflector is conveyed into the chamber through holes in the injection devices.
    Type: Grant
    Filed: May 31, 2019
    Date of Patent: April 12, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrice André Commaret, Haris Musaefendic, Romain Nicolas Lunel
  • Patent number: 11300056
    Abstract: A method of starting a turbine engine utilizing multiple components. The turbine engine may comprise a gearbox coupled to a spool of the turbine engine via an output shaft. A first starter may be coupled to the gearbox via an input shaft. A first accessory may be coupled to the gearbox via another input shaft. The rotation of the output shaft of the gearbox may be coupled to the rotation of the spool. The rotation of each of the first starter and first accessory may be coupled to the rotation of the respective input shaft of the gearbox. The method may comprise applying a first application of power to one of the first starter and the first accessory and applying a second application of power to the other of the first accessory and the first starter.
    Type: Grant
    Filed: August 29, 2019
    Date of Patent: April 12, 2022
    Assignee: ROLLS-ROYCE CORPORATION
    Inventors: Adam Kempers, Jeremy Gallagher
  • Patent number: 11300294
    Abstract: The invention provides a gas turbine combustor having structural reliability against vibration of fuel nozzles caused by fluid force and high environmental performance by uniform combustion in a combustion chamber. The gas turbine combustor comprises a fuel nozzle configured to inject fuel, and a fuel nozzle plate including a hole section into which an insertion section located in a root part of the fuel nozzle is inserted. The fuel nozzle includes a male screw section at least on an outer circumferential surface of a downstream portion viewed from a flowing direction of the fuel in the insertion section. The fuel nozzle plate includes a female screw section in the hole section. The female screw section screws with the male screw section. The fuel nozzle includes the insertion section. An upstream end portion of the insertion section is metallurgically joined to an upstream end portion of the fuel nozzle plate.
    Type: Grant
    Filed: November 20, 2017
    Date of Patent: April 12, 2022
    Assignee: Mitsubishi Power, Ltd.
    Inventors: Satoshi Kumagai, Yoshihide Wadayama, Keisuke Miura
  • Patent number: 11300010
    Abstract: This cooling equipment comprises: a refrigerant supply line (81) supplying, to a condenser (6), a condenser refrigerant which cools steam (Sb) that has driven a steam turbine (5), to return the steam (Sb) to water (W); and a cooling part (80) which is disposed on the refrigerant supply line (81), and performs heat exchange between liquefied gas used as fuel for a gas turbine (2) and the condenser refrigerant to heat and vaporize the liquefied gas and to cool the condenser refrigerant at the same time.
    Type: Grant
    Filed: September 8, 2015
    Date of Patent: April 12, 2022
    Assignee: MITSUBISHI POWER, LTD.
    Inventor: Kazunori Fujita
  • Patent number: 11300050
    Abstract: Systems and methods to increase intake air flow to a gas turbine engine of a hydraulic fracturing unit when positioned in an enclosure may include providing an intake expansion assembly to enhance intake air flow to the gas turbine engine. The intake expansion assembly may include an intake expansion wall defining a plurality of intake ports positioned to supply intake air to the gas turbine engine. The intake expansion assembly also may include one or more actuators connected to a main housing of the enclosure and the intake expansion assembly. The one or more actuators may be positioned to cause the intake expansion wall to move relative to the main housing between a first position preventing air flow through the plurality of intake ports and a second position providing air flow through the plurality of intake ports to an interior of the enclosure.
    Type: Grant
    Filed: November 17, 2021
    Date of Patent: April 12, 2022
    Assignee: BJ Energy Solutions, LLC
    Inventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster