Patents Examined by Steven M Sutherland
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Patent number: 11920510Abstract: An electrical power generation system including a micro-turbine alternator including a combustion chamber, at least one turbine driven by combustion gases from the combustion chamber, a first stage compressor, and a second stage compressor located aft of the first stage compressor. The first stage compressor and the second stage compressor being operably connected to the combustion chamber to provide a compressed airflow thereto. The micro-turbine alternator including one or more shafts connecting the at least one turbine to the first stage compressor and the second stage compressor such that rotation of the at least one turbine drives rotation of the first and second stage compressor. An electric generator is disposed along the one or more shafts such that electrical power is generated via rotation of the one or more shafts. The electric generator is disposed along the one or more shafts between the first and second stage compressors.Type: GrantFiled: September 10, 2021Date of Patent: March 5, 2024Assignee: HAMILTON SUNDSTRAND CORPORATIONInventor: Richard A. Himmelmann
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Patent number: 11913349Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, first and second bearings, and a fan drive shaft interconnecting the gear system and the fan. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.Type: GrantFiled: February 1, 2023Date of Patent: February 27, 2024Assignee: RTX CORPORATIONInventors: Frederick M. Schwarz, Gabriel L. Suciu, William K. Ackermann, Daniel Bernard Kupratis, Michael E. McCune
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Patent number: 11905881Abstract: A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.Type: GrantFiled: August 24, 2021Date of Patent: February 20, 2024Assignee: General Electric CompanyInventors: Daniel Endecott Osgood, Jonathan Russell Ratzlaff, Kirk D. Gallier
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Patent number: 11898468Abstract: A sub-assembly for a low-pressure compressor of an aircraft turbine engine includes a straightener provided with cantilevered vanes and a rotor hub having a cavity covered by an inner shroud opposite the vanes. Orifices are made in the inner shroud to allow an air flow to circulate in the downstream to upstream direction of the low-pressure compressor.Type: GrantFiled: May 11, 2021Date of Patent: February 13, 2024Assignee: SAFRAN AERO BOOSTERSInventor: Stéphane Hiernaux
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Patent number: 11891951Abstract: A scramjet engine with a novel isolator is disclosed herein. The scramjet includes an air inlet configured to receive and direct air into the engine and a combustor operable to receive air from the air inlet and combust fuel therein as is conventional. An isolator is positioned between the air inlet and the combustor. The isolator includes a primary flow path separated into a plurality of separate secondary flow channels formed therethrough. The smaller secondary flow channels prevent shockwaves from propagating upstream from the combustor to the inlet that can occur during some operating conditions of a supersonic combustion flow process.Type: GrantFiled: February 1, 2023Date of Patent: February 6, 2024Assignee: United States of America as represented by the Secretary of the Air ForceInventors: Robert Mercier, Mark Gruber, Ryan Milligan
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Patent number: 11879541Abstract: A gearbox including a gear and a gutter. The gear is rotatable about a rotational axis in a rotational direction. The gear has a radial direction and an axial direction, and the gear expels oil radially outward when the gear rotates. The gutter is positioned radially outward of the gear in the radial direction of the gear to collect oil expelled by the gear when the gear rotates. The gutter includes an axial surface, a plurality of radial surfaces including a first radial surface and a second radial surface, and at least one opening to allow the oil collected in the gutter to flow therethrough. Each of the first radial surface and the second radial surface is oriented in a direction intersecting the axial surface, and the at least one opening is formed on both the axial surface and one of the first radial surface and the second radial surface.Type: GrantFiled: April 1, 2022Date of Patent: January 23, 2024Assignees: GENERAL ELECTRIC COMPANY, GE AVIO S.R.L.Inventors: Xiaohua Zhang, Bugra H. Ertas, Flavia Turi, Walter J. Smith
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Patent number: 11879363Abstract: The invention discloses a new type of integrated cycle to compete with the standard gas-steam combined cycle in terms of full load/part load efficiency besides ramp rate, startup time and other off design performance. The topping cycle is intercooled recuperative gas turbine (ICR GT) with multiple intercoolers. The bottoming compound cycles consists of supercritical refrigerant Rankine cycle (RRC) and vapor compression refrigeration cycle (VCRC). The refrigerant can be chosen from various organic and inorganic working fluids. The topping and bottoming cycles are highly coupled and form a new integrated cycle rising to the challenge of incoming renewable energy era when thermal power plants undergo frequent load change and long-term part load operation. This invention also markedly outperforms single intercooler ICR GT bottomed by single pressure subcritical RRC system in terms of efficiency, ramp rate etc., and could be an incredibly competitive solution for stationary power generation and marine propulsion.Type: GrantFiled: March 12, 2021Date of Patent: January 23, 2024Inventor: Xuanhua Guo
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Patent number: 11879390Abstract: The invention relates to a de-icing device for an air intake of an aircraft turbojet engine nacelle extending along an X-axis in which an air stream flows from upstream to downstream, the air intake having an inner cavity, extending annularly about the X-axis, which comprises an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the walls being connected by a leading edge, the de-icing device comprising at least one injector for injecting a stream of hot air into the inner cavity, the injector comprising a nozzle extending along a nozzle axis, the nozzle being configured to inject a stream of hot air having a dissymmetry along the nozzle axis.Type: GrantFiled: February 25, 2020Date of Patent: January 23, 2024Assignee: SAFRAN NACELLESInventor: Thierry Jacques Albert Le Docte
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Patent number: 11873759Abstract: A method for pressurizing exhaust gases from a turbine power plant includes the steps of: applying a pressure to at least a proportion, in particular a proportion rich in carbon dioxide, of the exhaust gases from the power plant by way of a fluid operating machine of a pressurization device, and applying a torque to the fluid operating machine and/or driving the fluid operating machine by way of such a torque, which is present at an output shaft of a main turbine of the power plant.Type: GrantFiled: December 13, 2021Date of Patent: January 16, 2024Assignee: Voith Patent GmbHInventors: Josef Braun, Hans Schirle
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Patent number: 11867103Abstract: An annular resonator with a multiplicity of perforations for installation into a combustor arrangement of a static gas turbine installation, wherein the resonator is produced from refractory ceramic. A combustor arrangement for a gas turbine installation with a combustor unit, has a combustor, with a transfer line, which is arranged downstream of the combustor unit and which is designed to conduct hot gas generated by the combustor to a turbine, and with at least one resonator.Type: GrantFiled: March 16, 2020Date of Patent: January 9, 2024Assignee: Siemens Energy Global GmbH &Co. KGInventor: Claus Krusch
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Patent number: 11859537Abstract: A gas turbine engine comprises at least a power output turbine unit (POT), which is rotatably arranged inside an outer housing unit, and a compressor-turbine unit (CTU), which is rotatably arranged inside the POT, and the CTU, POT and outer housing unit are arranged about a common axis of rotation (CL). The POT and the CTU are arranged in such close proximity (d) that a dynamic friction coupling is generated between the POT and the CTU.Type: GrantFiled: November 10, 2020Date of Patent: January 2, 2024Assignee: TNS TEKNOLOGIInventor: Torleik Stangeland
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Patent number: 11859545Abstract: An assembly for an aircraft includes a variable area inlet for an aircraft propulsion system. The variable area inlet extends along a longitudinal centerline. The variable area inlet includes an inlet structure, an inlet door, an inner inlet passage, and an outer inlet passage. The inlet door is configured to axially translate from a closed position to an open position along the longitudinal centerline. The inlet door is configured to close the outer inlet passage when the inlet door is in the closed position. The inlet door is configured to open the outer inlet passage when the inlet door is in the open position. The inner inlet passage extends into the variable area inlet from a leading edge of the inlet structure. The outer inlet passage extends through the inlet structure to the inner inlet passage.Type: GrantFiled: January 27, 2023Date of Patent: January 2, 2024Assignee: Rohr, Inc.Inventors: Imad D. Ghandour, Jihad I. Ramlaoui, Timothy Gormley
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Patent number: 11859556Abstract: An air starter for starting a turbine engine that includes a housing, a turbine member, a drive shaft, and at least one bearing assembly. The housing can define an interior where the turbine member rotatably couples to the drive shaft, where the drive shaft or turbine member are rotatably supported by the least one bearing assembly. A scoop wheel located in the interior of the housing provides lubrication to the at least one bearing assembly.Type: GrantFiled: February 10, 2023Date of Patent: January 2, 2024Assignee: Unison Industries, LLCInventors: Nilesh Vilas Varote, David Raju Yamarthi, David Allan Dranschak, Eliel Fresco Rodriguez, Amit Arvind Kurvinkop
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Patent number: 11859517Abstract: The present disclosure relates to cogeneration of power and one or more chemical entities through operation of a power production cycle and treatment of a stream comprising carbon monoxide and hydrogen. A cogeneration process can include carrying out a power production cycle, providing a heated stream comprising carbon monoxide and hydrogen, cooling the heated stream comprising carbon monoxide and hydrogen against at least one stream in the power production cycle so as to provide heating to the power production cycle, and carrying out at least one purification step so as to provide a purified stream comprising predominately hydrogen.Type: GrantFiled: June 12, 2020Date of Patent: January 2, 2024Assignee: 8 Rivers Capital, LLCInventors: Xijia Lu, Brock Alan Forrest, Navid Rafati
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Patent number: 11852072Abstract: A starter generator located within a sump region of a turbofan engine and coupled to an adapter shaft. The adapter shaft rotationally coupled to the high pressure shaft, forward of a high pressure shaft bearing, and secured by a spanner nut. The engine makes use of two pluralities of electrical conductors, the first extends through an electrical conduit defined by a forward strut extending from the sump region to the outward casing, the second extends axially away from the electric starter. Each of the first plurality of electrical conductors makes reversible contact with a respective one of the second plurality of electrical conductors via an elbow/pin connector, producing a tight turn in area of limited space.Type: GrantFiled: October 28, 2021Date of Patent: December 26, 2023Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce CorporationInventors: Melissa Hughes, Brian R. Bennett, Stanford Clemens, Randal Renback
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Patent number: 11845034Abstract: A vehicle provided with an engine, at least one air intake through which the engine takes in the external air needed to operate, and an air filter arranged downstream of the air intake. The air filter presents: at least one filtering material panel having a corrugated shape having a plurality of crests disposed towards an outer environment and a plurality of valleys arranged towards an internal environment; an outer reinforcement mesh; an inner reinforcement mesh; and a heating device which is designed to heat the filtering material panel. The heating device presents: a plurality of electrical conductors, which are completely independent and separated from the outer reinforcement mesh, rest on the outer surface of the filtering material panel, and are arranged only and exclusively at the crests; and a supply device designed to cause an electric current to flow through the electric conductors so as to generate heat, due to the Joule effect.Type: GrantFiled: October 23, 2019Date of Patent: December 19, 2023Assignee: BMC S.R.L.Inventor: Gaetano Bergami
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Patent number: 11846231Abstract: A system and method for preventing icing in the combustion inlet air path of a gas turbine system. An air intake system of the gas turbine system supplies intake air to a gas turbine engine. The air intake system includes an air filter inlet house to filter the intake air. The air filter inlet house includes at least one filter stage having an array of pulse filters, with each of the pulse filters being hydrophobic. A combustion inlet air path is in fluid communication with the air intake system and the gas turbine engine. The combustion inlet air path receives the filtered air from the air filter inlet house and supplies the filtered air as combustion inlet air to an inlet of the gas turbine engine. A surface of at least one component in the combustion inlet air path includes an anti-icing coating to prevent ice from forming thereon.Type: GrantFiled: December 23, 2021Date of Patent: December 19, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: William Stanley Adams, Victor Alfonso Gonzalez Tellez, Jametra Stitt, Nileshpuri Goswami
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Patent number: 11840935Abstract: A method and system for controlling a vibration of a rotor in a turboshaft engine are provided. The method includes: establishing, based on a kinetic model for a rotor-casing system, a mapping matrix indicating a correspondence among an unbalance, an oil film clearance, and a vibration response; performing determination on a real-time vibration response, and skipping adjustment if the real-time vibration response is smaller than a response threshold; otherwise, approximately matching a real-time oil film clearance and the real-time vibration response with the mapping matrix to obtain a real-time unbalance; obtaining, based on the real-time unbalance and the mapping matrix, a preferred vibration response, and further obtaining a preferred oil film clearance; based on the preferred oil film clearance and the real-time oil film clearance, obtaining a clearance adjustment amount; generating a control signal based on the clearance adjustment amount, and performing adjustment based on the control signal.Type: GrantFiled: August 3, 2022Date of Patent: December 12, 2023Assignee: Hunan University of Science and TechnologyInventors: Guangfu Bin, Chao Li, Qingxiong Lu, Yangyan Zhang, Jian Li, Huiyu Xu, Weimin Wang, Pingping Yang
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Patent number: 11840346Abstract: An aircraft engine includes an air inlet duct and at least one strut having a leading edge and a trailing edge. The at least one strut extends across at least part of the air inlet duct and has a strut passage. The trailing edge has one or more edge contours, each defining a contour edge wall recessed from a baseline surface of the trailing edge. The one or more edge contours have a recessed tap in fluid communication with the strut passage.Type: GrantFiled: March 28, 2022Date of Patent: December 12, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Mateusz Ożóg
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Patent number: 11841141Abstract: An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.Type: GrantFiled: October 16, 2020Date of Patent: December 12, 2023Assignees: GENERAL ELECTRIC COMPANY, GE AVIO S.R.L.Inventors: Massimo Giovanni Giambra, Joseph Douglas Monty, Stephen John Howell