Patents Examined by Sean V Meiller
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Patent number: 11913647Abstract: Disclosed herein is a nozzle for a combustor that burns fuel containing hydrogen, which includes a plurality of mixing tubes through which air and fuel flow, a multi-tube configured to contain and support the mixing tubes, a fuel tube formed inside the multi-tube and through which fuel flows, a tip plate coupled to a tip of the multi-tube, and a front plate spaced apart from the tip plate to define a cooling space.Type: GrantFiled: February 6, 2023Date of Patent: February 27, 2024Assignee: DOOSAN ENERBILITY CO., LTD.Inventor: Borys Shershnyov
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Patent number: 11891952Abstract: 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: GrantFiled: April 25, 2023Date of Patent: February 6, 2024Assignee: BJ Energy Solutions, LLCInventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster
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Patent number: 11885263Abstract: A secondary air system (SAS) of an aircraft engine that produces secondary airflow from a source of secondary air includes a hollow strut and one or more SAS feed pipes upstream thereof. The hollow strut extends radially through the main gas path of the engine and defines therein a strut conduit extending between a strut inlet and a strut outlet at opposite ends of the hollow strut. The strut outlet is in fluid flow communication with a buffer cavity for feeding the secondary airflow to the engine core. The SAS feed pipe includes an inlet receiving the secondary airflow from the source of secondary air, and an outlet in fluid flow communication with the strut inlet to feed the secondary airflow into the strut conduit. The SAS feed pipe has a sonic orifice therein, between the inlet and the outlet thereof.Type: GrantFiled: June 17, 2021Date of Patent: January 30, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Gabriel St-Laurent, Alain Conrad Martel
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Patent number: 11879392Abstract: A gas supply system is provided herein. The gas supply system includes a fuel oxygen reduction unit having a circuit defining a gas flowpath for a flow of a stripping gas. A reservoir is in selective fluid communication with the fuel oxygen reduction unit and is configured to store a portion of the stripping gas from the circuit. The reservoir is further configured to be in selective fluid communication with the fuel system component when installed in a vehicle to provide the stored portion of the stripping gas to the fuel system component in response to detection of a purge condition.Type: GrantFiled: December 30, 2022Date of Patent: January 23, 2024Assignee: General Electric CompanyInventor: Jeffrey Douglas Rambo
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Patent number: 11873993Abstract: A combustor includes a liner defining a combustion chamber. An air and fuel mixing body is received within the liner and upstream of the combustion chamber. The mixing body has a center axis and includes a bluff-body. A plurality of fuel injection ports on the bluff-body communicate with a central fuel supply such that fuel passes from the fuel supply passage and into a mixing chamber with a component in an axially downstream direction and a radially outward direction relative to said central axis. A plurality of inner air swirlers provide air into the mixing chamber with a component in an axially downstream direction, a radially outward direction, and with a circumferential component due to swirler structure. The fuel injection ports are downstream of an outlet of the inner air swirlers.Type: GrantFiled: February 2, 2023Date of Patent: January 16, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Alain Athanase Fossi
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Patent number: 11852345Abstract: A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts and a multiple of inlets to a respective diffusion passage, one of the multiple of inlets formed between each one of the multiple of hollow struts located between two diffusion passages.Type: GrantFiled: June 22, 2022Date of Patent: December 26, 2023Assignee: RTX CorporationInventors: Michael G. McCaffrey, Matthew Andrew Hough, Pedro E. Rivero
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Patent number: 11852030Abstract: A turbine casing for an exhaust-gas turbine is provided herein. The turbine casing has a connection flange for bearing-casing-side attachment to a bearing casing in which casing-connection holes that are mutually spaced in the circumferential direction are provided, wherein, between adjacent casing-connection holes, material recesses that are open radially inwards towards a central longitudinal axis of the turbine casing are provided in the connection flange. Further provided herein is an exhaust-gas turbine that is equipped with the turbine casing.Type: GrantFiled: June 22, 2020Date of Patent: December 26, 2023Assignee: Turbo Systems Switzerland LtdInventor: Matthias Richner
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Patent number: 11802495Abstract: An Ericsson cycle turbine engine. The Ericsson cycle turbine may comprise: a centrifugal gas compressor, shaft, at least one heat exchanger, and a reaction turbine. The centrifugal gas compressor may function as a spinning wheel trompe and may be fed with a gas-liquid mixture. The centrifugal gas compressor may separate a gas from the gas-liquid mixture after compression of that gas via centrifugal acceleration. The shaft may couple to the downstream end of the centrifugal gas compressor and may have an annular space to permit the compressed gas to travel therein. The heat exchanger may introduce heat to the compressed gas, such that isobaric expansion is approached. The reaction turbine may couple to the downstream end of the shaft and may rotate the shaft when releasing the compressed gas. The liquid may be mercury, oil, or a water-glycol mixture. The gas may be helium, air, argon, or ammonia.Type: GrantFiled: September 29, 2022Date of Patent: October 31, 2023Assignee: The United States of America, as represented by the Secretary of the NavyInventor: Geoffrey Robert Kemmerer
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Patent number: 11773780Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a turbine section, with both the main compressor section and the turbine section housing rotatable components. A first tap taps air compressed by the main compressor section at an upstream location upstream of the downstream most location. The first tap passes through a heat exchanger, and to a cooling compressor. Air downstream of the cooling compressor is selectively connected to reach at least one of the rotatable components. The cooling compressor is connected to rotate at a speed proportional to a rotational speed in one of the main compressor section and the turbine section. A valve system includes a check valve for selectively blocking flow downstream of the cooling compressor from reaching the at least one rotatable component. A dump valve selectively dumps air downstream of the cooling compressor. A method is also disclosed.Type: GrantFiled: January 28, 2022Date of Patent: October 3, 2023Assignee: RTX CORPORATIONInventor: Joseph Turney
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Patent number: 11774102Abstract: An assembly for a turbomachine can include a fuel nozzle and a combustion liner. The fuel nozzle and the combustion liner can be attached to each using a plurality of clip joints such that the combustion liner is longitudinally fixed relative to the fuel nozzle but such that the combustion liner can radially move relative to the fuel nozzle.Type: GrantFiled: June 2, 2021Date of Patent: October 3, 2023Assignee: Collins Engine Nozzles, Inc.Inventors: Jacob Greenfield, Thomas J. Ocken, Jason A. Ryon
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Patent number: 11753992Abstract: A de-icing device for an air intake of an aircraft jet engine nacelle extending along an axis in which a flow of air flows from upstream to downstream, the intake comprising an inner wall and an outer wall connected by a leading edge, the inner wall comprising a plurality of blowing lines, each blowing line comprising a plurality of through-openings configured to blow elementary streams from the hot air source in order to de-ice said inner wall, the blowing lines being parallel to one another in a cylindrical projection plane, each blowing line having a depth defined along the axis X and a length defined along the axis Y in the cylindrical projection plane, two adjacent blowing lines being spaced apart by a distance, the ratio of the distances L3/D3 being between 1 and 2.Type: GrantFiled: December 3, 2019Date of Patent: September 12, 2023Assignee: SAFRAN NACELLESInventor: Hervé Léopold Hurlin
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Patent number: 11746698Abstract: 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: GrantFiled: December 14, 2022Date of Patent: September 5, 2023Assignee: BJ Energy Solutions, LLCInventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster
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Patent number: 11732643Abstract: A multi-engine aircraft includes a first engine drivingly engaged to a common rotatable load and a second engine drivingly engaged to the common rotatable load, the second engine having a bleed air system and a control system in communication with a compressed air switching system. The control system controls operation of the second engine and/or the compressed air switching system. The compressed air switching system includes a switching valve that is displaceable between at least a first position and a second position, the first position interconnecting a lower pressure inlet and a switch outlet, and the second position interconnecting a high pressure inlet and the switch outlet. The switch outlet is in communication with the bleed air system of the second engine. The control system actuates the switching valve to switch between the first and second positions.Type: GrantFiled: February 3, 2022Date of Patent: August 22, 2023Assignee: PRATT & WHITNEY CANADA CORPInventors: Kevin Ng, Johnny Vinski, Adam Logan
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Patent number: 11719441Abstract: Systems and methods including a reformer stack extended around a combustion chamber. The reformer stack is configured to provide output products to the combustion chamber.Type: GrantFiled: January 4, 2022Date of Patent: August 8, 2023Assignee: General Electric CompanyInventors: Honggang Wang, Michael Anthony Benjamin
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Patent number: 11713731Abstract: A variable area nozzle assembly includes a fixed structure surrounding an exhaust duct extending along a nozzle axis. The fixed structure defines an exhaust duct outlet of the exhaust duct. The fixed structure includes a first side beam and a second side beam. Each of the first side beam and the second side beam extend in a direction axially aft from the exhaust duct outlet. Each of an upper thrust reverser door and a lower thrust reverser door are pivotably mounted to the first side beam and the second side beam at a first axial position. An upper panel and a lower panel are pivotably mounted to the upper thrust reverser door and the lower thrust reverser door, respectively, at a second axial position located axially forward of the first axial position. The upper panel and the lower panel define a nozzle outlet cross-sectional area therebetween.Type: GrantFiled: December 30, 2021Date of Patent: August 1, 2023Assignee: Rohr, Inc.Inventor: Timothy Gormley
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Patent number: 11702994Abstract: A pressure relief latch includes a housing configured to be mounted to a pressure relief door. A bolt is coupled to the housing about a first axis and is rotatable about the first axis between a first bolt position and a second bolt position. The bolt includes a bearing centered about a second axis. The bearing is configured to rotate about the second axis. A spring assembly includes a first assembly end mounted to the bearing and a second assembly end in rotational communication with the housing about a third axis. The spring assembly is rotatable about the second and third axes and further includes a spring extending between the first and second assembly ends. The bolt is configured to permit movement of the pressure relief door from the closed position to the open position as the bolt rotates from the first bolt position to the second bolt position.Type: GrantFiled: May 6, 2019Date of Patent: July 18, 2023Assignee: Rohr, Inc.Inventors: Paul F. McMahan, David L. Lipson
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Patent number: 11692487Abstract: A fuel injector system includes an outer support and an inner support, with a feed arm extending radially between the inner support and the outer support. A plurality of outlet openings extend in an axial direction from the feed arm for feeding respective injection nozzles. The outer support and feed arm define a plurality of fuel passages therethrough to convey fluid from an external source through the outer support and feed arm to the outlet openings. A heat shield extends around the feed arm from the outer support to the inner support. The heat shield is spaced apart from the feed arm with an insulative gap therebetween.Type: GrantFiled: January 19, 2022Date of Patent: July 4, 2023Assignee: Collins Engine Nozzles, Inc.Inventors: Jason A. Ryon, Lev A. Prociw, Gregory A. Zink
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Patent number: 11692480Abstract: An air intake scoop intended to be fastened on a panel of an aircraft includes an air inlet mouth having a wall, a peripheral collar intended to be fastened to the panel, and a bearing element intended to support the air circulation duct. The air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar so as to achieve a pressure barrier in case of breakage of the wall of the air inlet mouth.Type: GrantFiled: August 27, 2019Date of Patent: July 4, 2023Assignee: Safran NacellesInventors: François Bellet, Laurent Georges Valleroy, Mathieu David
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Patent number: 11662096Abstract: A combustor for a gas turbine includes a cowl structure, a pseudo-dome structure, a ceramic matrix composite (CMC) dome, and a swirler assembly. The swirler assembly is connected to the pseudo-dome structure, which is connected to the cowl structure, and the CMC dome is separately connected to the cowl structure apart from the swirler assembly. The swirler assembly includes a swirler dome interface wall that interfaces with the CMC dome on an upstream side of the CMC dome, and a swirler outlet extends through a CMC dome swirler opening through the CMC dome.Type: GrantFiled: October 7, 2021Date of Patent: May 30, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Gerardo Antonio Salazar Lois, Daniel D. Brown, Daniel J. Kirtley
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Patent number: 11655762Abstract: A gas turbine engine includes a fan assembly, a compressor assembly, a combustion chamber, a turbine assembly, a bypass duct conveying rearward a bypass airstream driven by the fan assembly when the gas turbine engine is in use, a fairing extending across at least a portion of the bypass duct downstream of the fan assembly, and a heat exchanger having an inlet fluidly connected to the compressor assembly and an outlet fluidly connected to a pneumatic actuator of the gas turbine engine. The fairing has a leading edge and a trailing edge. The heat exchanger is disposed adjacent the trailing edge of the fairing.Type: GrantFiled: April 8, 2019Date of Patent: May 23, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jason Fish, Charlie Molina, Daniel Alecu