Patents Examined by Marc J Amar
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Patent number: 11732659Abstract: A gas turbine engine comprising a variable geometry combustor having pilot fuel injectors and main fuel injectors; a fuel metering system configured to control fuel flow to the pilot fuel injectors and the main fuel injectors; a variable geometry airflow arrangement for the variable geometry combustor, which is configured to vary the airflow through the pilot fuel injectors and/or the main fuel injectors; a control system configured to control the variable geometry airflow arrangement in dependence upon airflow delivered to the combustor, the fuel flow to the pilot fuel injectors and the main fuel injectors, and a target index of soot emissions, thereby controlling airflow through the pilot fuel injectors and/or the main fuel injectors and hence the quantity of soot produced by combustion.Type: GrantFiled: August 26, 2022Date of Patent: August 22, 2023Assignee: ROLLS-ROYCE plcInventors: Peter Swann, Christopher P Madden
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Patent number: 11719168Abstract: An example compressor bleed slot apparatus includes an annular compressor casing, a blade row mounted for rotation about a centerline axis inside the compressor casing, a bleed slot passing through the forward section of the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row, an array of struts interconnecting the inboard and outboard walls, and an annular supplemental flange extending radially outward from the forward section of the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot, wherein the supplemental flange includes a necked-down portion adjacent the forward section of the compressor casing, the necked-down portion positioned axially between an inlet of the bleed slot and an outlet of the bleed slot.Type: GrantFiled: March 1, 2021Date of Patent: August 8, 2023Assignee: General Electric CompanyInventors: Steven Mitchell Taylor, Vishnu Das K, Manish Singhal, Atanu Saha, Michael Anthony Thomas
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Patent number: 11713730Abstract: In a convergent-divergent flap pair for a turbojet engine nozzle of the variable-geometry convergent-divergent type, the convergent flap and the divergent flap include respective cooling-air ducts connected to one another through air passage openings formed in respective contact surfaces of the convergent flap and of the divergent flap arranged facing one another.Type: GrantFiled: August 27, 2020Date of Patent: August 1, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thierry Kohn, Frédéric Paul Eichstädt, Florent Luc Lacombe, François Leglaye, Brice Marie Yves Emile Le Pannerer
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Patent number: 11708792Abstract: A twin-engine system includes a gas turbine engine comprising a core and a first output shaft drivable by the core. An electric engine has an electric motor configured to drive a second output shaft. A reduction gear box (RGB) has an RGB input drivingly engaged to both the first output shaft and the second output shaft. The RGB has an RGB output to provide rotational output to a rotatable load.Type: GrantFiled: May 31, 2022Date of Patent: July 25, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Guy Lefebvre
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Patent number: 11698004Abstract: An aircraft propulsion assembly includes a turbine engine surrounded by a nacelle with an annular air-intake lip extending around the turbine engine by two annular walls, inner and outer, respectively, intended for being swept across by air flows at least when the aircraft is in flight. The inner and outer walls each includes or supports at least one network of pipes forming heat exchangers. The inner wall pipe network having liquid outlet connected with a liquid intake of the outer wall pipe network. The propulsion assembly further includes means for circulating the liquid, connected to at least one liquid intake of the network of pipes of the inner wall.Type: GrantFiled: April 12, 2018Date of Patent: July 11, 2023Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN NACELLESInventors: Sébastien Oriol, Mohammed-Lamine Boutaleb, Vincent Jean-François Peyron
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Patent number: 11692448Abstract: A nozzle assembly for a gas turbine engine includes a nozzle having a first material defining a first coefficient of thermal expansion, the nozzle having an airfoil defining a fluid passage therein, an inlet wall defining a fluid inlet that is fluidly connected to the fluid passage, and a passive valve assembly comprising an annular band, the annular band comprising a second material having a second coefficient of thermal expansion less than the first coefficient of thermal expansion such that the passive valve assembly is at least partially moveable relative to the fluid inlet.Type: GrantFiled: March 4, 2022Date of Patent: July 4, 2023Assignee: General Electric CompanyInventors: Paul Hadley Vitt, Steven Douglas Johnson
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Patent number: 11685541Abstract: An air-breathing turbojet engine for a hypersonic vehicle is shown. The engine comprises a pump for pumping a cryogenic fuel, an inlet configured to compress inlet air by one or more shocks, a cooler to cool the compressed inlet air using the cryogenic fuel, and a turbo-compressor to compress the air further. A precooler cools the compressed inlet air using compressed cooled air from the turbo-compressor. A combustor receives compressed cooled air from the turbo-compressor and a first portion of the cryogenic fuel for combustion. A first turbine expands and is driven by combustion products, and a second turbine expands and is driven by a second portion of the cryogenic fuel. The first turbine and the second turbine drive the turbo-compressor via a shaft. An afterburner receives combustion products from the first turbine and the second portion of the cryogenic fuel from the second turbine for combustion therein.Type: GrantFiled: June 10, 2022Date of Patent: June 27, 2023Assignee: ROLLS-ROYCE plcInventor: Ahmed My Razak
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Patent number: 11679886Abstract: A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader having a central part connected to the support and a first and a second end that are connected to thrust rods, at least one limiting system for limiting the travel of the spreader having an upper and a lower stop between which is positioned the first or second end of the spreader, the upper and the lower stop being connected to one another so as to form a single part connected to a fitting secured to the support.Type: GrantFiled: April 21, 2022Date of Patent: June 20, 2023Assignee: Airbus Operations SASInventors: Michael Berjot, Rémi Lansiaux, William Bras, Germain Gueneau, Sébastien Van Arendonk, Jacques Demange, Sébastien Commenge
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Patent number: 11661867Abstract: A gas turbine exhaust heat recovery plant includes a plurality of gas turbine exhaust heat recovery devices that have a gas turbine and an exhaust heat recovery boiler for generating steam by recovering exhaust heat of the gas turbine, a steam-utilizing facility that utilizes the steam generated by the exhaust heat recovery boiler, and an inter-device heat medium supply unit capable of supplying a portion of water heated or a portion of the steam generated by at least one of the gas turbine exhaust heat recovery devices out of the plurality of gas turbine exhaust heat recovery devices, to the other gas turbine exhaust heat recovery device.Type: GrantFiled: January 29, 2020Date of Patent: May 30, 2023Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Hideyuki Uechi, Eisaku Ito
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Patent number: 11662095Abstract: A fuel nozzle includes a shroud; an injection cylinder surrounded by the shroud and configured to supply fuel to a combustion chamber; a swirler disposed between the injection cylinder and the shroud; and a porous disk disposed downstream of the swirler to surround an outer peripheral surface of the injection cylinder in order to prevent a flashback phenomenon occurring due to a reduction in pressure around the swirler. The porous disk includes a disk body to block a flame produced in the combustion chamber, and a plurality of flow holes are formed in the disk body through which the fuel flows. It is possible to prevent flashback by installing the porous disk downstream of the swirler, and to impart linearity and a swirling effect to the fuel passing through the fuel nozzle by forming variously configured flow holes in the porous disk.Type: GrantFiled: October 15, 2021Date of Patent: May 30, 2023Assignee: DOOSAN ENERBILITY CO., LTD.Inventors: Moonsoo Cho, Inchan Choi
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Patent number: 11649965Abstract: The fuel nozzle for the gas turbine includes a radial swirler and an axial swirler. The radial swirler is arranged to swirl a first flow of a first oxidant-fuel mixture and the axial swirler is arranged to swirl a second flow of a second oxidant-fuel mixture. The first flow may be fed by a central conduit and the second flow may be fed by an annular conduit surrounding the central conduit.Type: GrantFiled: May 30, 2017Date of Patent: May 16, 2023Assignee: NUOVO PIGNONE TECNOLOGIE SRLInventor: Matteo Cerutti
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Patent number: 11643968Abstract: An air intake system for an aircraft, which is switchable between a performance mode and a filtered mode, includes a duct forming filtered air inlet slits. The air intake system also includes interconnected gills adjacent to the filtered air inlet slits. The gills are movable between various gill positions including a closed position substantially covering the filtered air inlet slits and an open position substantially exposing the filtered air inlet slits. The air intake system also includes an actuator configured to move the gills into the closed position in the performance mode and the open position in the filtered mode.Type: GrantFiled: May 6, 2021Date of Patent: May 9, 2023Assignee: Textron Innovations Inc.Inventors: Bruce Bennett Bacon, Kristine Joyce Lazo, Shawn Patrick Leonard, Jr.
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Patent number: 11639700Abstract: Airframe integrated scramjet engines are disclosed. Scramjet engines within the scope of this disclosure may be configured to integrate smoothly with an airframe of a hypersonic flight aircraft or vehicle. The scramjet engine may include capture shape of an inlet configured to capture airflow, a combustor configured for combustion of fuel and air, and an exit shape of a nozzle configured for expansion of the combusted fuel and air to provide hypersonic thrust. In some embodiments, the scramjet engine has a fixed geometry and a transitioning cross-sectional shape over its full length. The scramjet engine is configured to be a component of launch vehicle system.Type: GrantFiled: September 8, 2020Date of Patent: May 2, 2023Assignee: Hypersonix IP Holdings, Inc.Inventor: Michael Kevin Smart
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Patent number: 11578663Abstract: A method of providing an engine family includes providing a first engine having a low pressure turbine driving a low pressure compressor at a first speed ratio, and a high pressure turbine driving a high pressure compressor. The method includes providing a second engine by changing the first speed ratio of the first engine to a second speed ratio.Type: GrantFiled: September 10, 2019Date of Patent: February 14, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ghislain Plante, Keith Morgan, Stephen Mah, Patrick Valois, Robert Peluso
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Patent number: 11578652Abstract: A combined heat and power system and method of operation is provided. The system includes a combustion chamber configured to directly combust solid organic material. A compressor turbine is fluidly coupled to the combustion chamber. An expansion turbine is fluidly coupled to the combustion chamber. In an embodiment, the system has a low turbine pressure ratio.Type: GrantFiled: August 12, 2019Date of Patent: February 14, 2023Assignee: ENEXOR ENERGY, LLCInventor: Ricardo Conde
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Patent number: 11572840Abstract: A computer-implemented method for multi-mode operation of a combustion system, a combustion system, and a heat engine are provided. The method includes initializing combustion of a fuel/oxidizer mixture, determining whether conditions at the combustion system meet or exceed a first threshold operating parameter, transitioning to detonation combustion of the fuel/oxidizer mixture if conditions at the combustion system meet or exceed the first threshold operating parameter, and maintaining or increasing fuel flow through a deflagrative fuel circuit if conditions at the combustion system do not meet or exceed the first threshold operating parameter.Type: GrantFiled: December 3, 2019Date of Patent: February 7, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Joel Meier Haynes, Sarah Marie Monahan, Thomas Michael Lavertu, Venkat Eswarlu Tangirala, Kapil Kumar Singh
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Patent number: 11572833Abstract: An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.Type: GrantFiled: April 2, 2019Date of Patent: February 7, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie Hellegouarch, Frédéric Paul Eichstadt, Quentin Matthias Emmanuel Garnaud
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Patent number: 11572838Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.Type: GrantFiled: September 29, 2020Date of Patent: February 7, 2023Assignee: General Electric CompanyInventors: Brandon Wayne Miller, John Carl Glessner, Lawrence William Nurre, Ian Francis Prentice, Ethan Patrick O'Connor, Arthur William Sibbach
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Patent number: 11555457Abstract: A fuel control device includes a stem fuel valve opening degree determination unit, a branch line flow rate determination unit, and a correction value determination unit. The stem fuel valve opening degree determination unit is configured to determine an opening degree of a flow rate adjustment valve of a stem fuel supply line. The branch line flow rate determination unit is configured to determine an opening degree of a flow rate adjustment valve of at least one branch line. The correction value determination unit is configured to determine a correction value of the opening degree of the flow rate adjustment valve of the at least one branch line based on a value of a pressure difference between a fuel pressure upstream of a nozzle connected to the at least one branch line and a corrected fuel pressure for a fuel pressure at an outlet.Type: GrantFiled: March 8, 2017Date of Patent: January 17, 2023Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Kenji Miyamoto, Kotaro Miyauchi, Hisashi Nakahara, Kiyoshi Fujimoto
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Patent number: 11549464Abstract: A system includes a gas turbine engine having a low speed spool, a high speed spool, and a combustor. The system also includes a low spool motor configured to augment rotational power of the low speed spool. The system further includes a controller configured to cause fuel flow. The controller is operable to control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor.Type: GrantFiled: July 23, 2020Date of Patent: January 10, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Neil Terwilliger, Gary Collopy