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公开(公告)号：US12152537B2
公开(公告)日：2024-11-26
申请号：US18430317
申请日：2024-02-01
Applicant: General Electric Company
Inventor： Pranav R. Kamat , Bhaskar Nanda Mondal , Jeffrey D. Clements
Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
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公开(公告)号：US11555453B2
公开(公告)日：2023-01-17
申请号：US17368317
申请日：2021-07-06
Applicant: Pratt & Whitney Canada Corp.
Inventor： Keith Morgan , Robert Peluso , Ghislain Plante , Eugene Gekht , Eric Durocher , Jean Dubreuil
IPC: F02C7/32 , F02C3/14 , F02C6/20 , F02C3/04 , F02C3/067 , F02C3/113 , F02C7/36 , F01D1/26 , F04D25/02
Abstract: A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.
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公开(公告)号：US20220186633A1
公开(公告)日：2022-06-16
申请号：US17440073
申请日：2020-03-16
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: A counter-rotating turbine of an aircraft turbomachine, includes a casing including an endoscopy port configured for an endoscopy plug of a non-destructive testing device to pass into the casing. The endoscopy plug includes a mechanism for acquiring and transmitting images. The non-destructive testing device includes a mechanism for receiving and displaying images connected to the mechanism for acquiring and transmitting images by a wireless connection. First and second rotors are configured to rotate in opposite rotation directions, the second rotor having an endoscopy port in which the endoscopy plug is removably attached.
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公开(公告)号：US11280198B2
公开(公告)日：2022-03-22
申请号：US16675918
申请日：2019-11-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Bhaskar Nanda Mondal , Alan Roy Stuart , Robert Proctor , Christopher Charles Glynn
IPC: F01D5/24 , F01D5/08 , F01D1/24 , F02K3/072 , F01D11/00 , F02C7/18 , F01D25/14 , F02C7/12 , F01D1/26
Abstract: An apparatus for a turbine engine comprising an outer casing, an engine core provided within outer casing and having a at least one set of blades, and through which gasses flow in a forward to aft direction, an outer drum located within the outer casing to define an annular cavity. A set of seals extending between the first surface and the second surface to define at least one cooled cavity within the annular cavity.
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公开(公告)号：US11105200B2
公开(公告)日：2021-08-31
申请号：US15648867
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Jeffrey Donald Clements , Darek Tomasz Zatorski , Brandon Wayne Miller , Joseph Robert Dickman
Abstract: The present disclosure is directed to a turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction. The turbine engine includes a power turbine including a first turbine rotor assembly interdigitated with a second turbine rotor assembly along the longitudinal direction; a gear assembly coupled to the first turbine rotor assembly and the second turbine rotor assembly, wherein the gear assembly includes a first input interface coupled to the first turbine rotor assembly, a second input interface coupled to the second turbine rotor assembly, and one or more third gears coupled to the first input interface and the second input interface therebetween; and a first output shaft and a second output shaft, wherein each of the first output shaft and the second output shaft are configured to couple to an electrical load device.
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Patent Agency Ranking
公开(公告)号：US10801442B2
公开(公告)日：2020-10-13
申请号：US15427340
申请日：2017-02-08
Applicant: General Electric Company
Inventor： Jeffrey Donald Clements , Darek Tomasz Zatorski , Alan Roy Stuart
Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section and a gear assembly within or downstream of the turbine section. The turbine section includes a first rotating component and a second rotating component along the longitudinal direction. The first rotating component includes one or more connecting airfoils coupled to a radially extended rotor, and the second rotating component includes an inner shroud defining a plurality of inner shroud airfoils extended outward of the inner shroud along the radial direction. The second rotating component is coupled to a second shaft connected to an input accessory of the gear assembly, and the first rotating component is coupled to an output accessory of the gear assembly. The output accessory rotates the first rotating component about the axial centerline at a first speed and wherein the second rotating component rotates about the axial centerline at a second speed.
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公开(公告)号：US10190497B2
公开(公告)日：2019-01-29
申请号：US14887433
申请日：2015-10-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry
Abstract: A gas turbine engine comprises a compressor section, a combustor section downstream of the compressor section, and a turbine section downstream of the combustor section. A mid-turbine frame includes an outer case portion and is configured to support the turbine section. At least one shaft defines an axis of rotation, and the turbine section comprises an inner rotor directly driving the shaft. The inner rotor includes an inner set of blades. An outer rotor is positioned immediately adjacent to the outer case portion and has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system is positioned downstream of the combustor section, is mounted to the mid-turbine frame, and is coupled to the outer rotor to drive the at least one shaft.
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公开(公告)号：US20180274365A1
公开(公告)日：2018-09-27
申请号：US15412157
申请日：2017-01-23
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section that includes a first rotating component and a second rotating component. The first rotating component includes an inner shroud and an outer shroud outward of the inner shroud in the radial direction. The outer shroud defines a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction. The first rotating component further includes at least one connecting airfoil coupling the inner shroud and the outer shroud. The second rotating component is upstream of the one or more connecting airfoils of the first rotating component along the longitudinal direction. The second rotating component includes a plurality of second airfoils extended outward in the radial direction. The first rotating component defines at least one stage of the plurality of outer shroud airfoils upstream of the second rotating component.
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公开(公告)号：US09611809B2
公开(公告)日：2017-04-04
申请号：US13520600
申请日：2011-01-07
Applicant: Wouter Balk
Inventor： Wouter Balk
CPC classification number: F02K3/072 , B64C11/48 , B64D2027/026 , F02C3/067 , F02C3/10 , F02C7/36 , F05D2260/40311 , F05D2260/96 , Y02T50/66 , Y02T50/671
Abstract: A contra-rotating propeller system for an aircraft turbine engine, including a free power turbine including a first rotor and a second rotor contra-rotating relative to the first rotor, a first contra-rotating propeller and a second contra-rotating propeller to be rotated about a longitudinal axis of the propeller system relative to a stator of the system, and a mechanical transmission device. The mechanical transmission system is provided between the first propeller and the second propeller.
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公开(公告)号：US09376202B2
公开(公告)日：2016-06-28
申请号：US13588180
申请日：2012-08-17
Applicant: Aleksander Krzysztof Szymandera
Inventor： Aleksander Krzysztof Szymandera
CPC classification number: B64C11/306 , B64C11/308 , B64D27/16 , B64D2027/005 , F01D1/26 , F02C9/58 , F02K3/025 , F02K3/072 , F05D2220/323 , F05D2240/30 , F05D2260/40311 , Y02T50/66
Abstract: A pitch control mechanism for an open rotor gas turbine engine is provided, the engine having a first rotor assembly and a second rotor assembly, with a plurality of airfoil blades circumferentially mounted on each rotor assembly, and arranged in contra-rotational relationship to each other. The pitch control mechanism includes an actuator assembly configured to be secured to a non-rotating frame of the engine, the actuator assembly having a first actuator and a second actuator, with the actuator assembly being rotationally isolatable from and couplable to the first and second rotor assemblies such that, in use, an actuation signal from the first or second actuator induces a corresponding desired change in pitch of the airfoil blades of the respective first or second rotor assembly independently of the pitch of the airfoil blades of the second or first rotor assembly.
Abstract translation: 提供了一种用于开式转子燃气涡轮发动机的变桨控制机构，该发动机具有第一转子组件和第二转子组件，多个翼型叶片周向地安装在每个转子组件上，并且以彼此相互旋转的关系布置 。 桨距控制机构包括构造成固定到发动机的非旋转框架的致动器组件，致动器组件具有第一致动器和第二致动器，致动器组件可旋转地隔离并可联接到第一和第二转子 组件，使得在使用中来自第一或第二致动器的致动信号独立于第二或第一转子组件的翼型叶片的桨距而引起相应的第一或第二转子组件的翼型叶片的螺距的相应的期望变化 。
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