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公开(公告)号：US20250163829A1
公开(公告)日：2025-05-22
申请号：US18435651
申请日：2024-02-07
Applicant: General Electric Company
Inventor： Brandon W. Miller , Andrew Hudecki , Ryan T. Roehm , Ravindra Shankar Ganiger
Abstract: A lubrication system for a turbine engine having one or more rotating components. The lubrication system includes a primary reservoir that stores a lubricant therein. A primary lubrication system supplies the lubricant from the primary reservoir to the one or more rotating components during normal operation of the turbine engine. An auxiliary lubrication system includes an auxiliary reservoir in fluid communication with the primary reservoir and the one or more rotating components. The auxiliary reservoir receives the lubricant from the primary reservoir and is positioned at substantially a six o'clock position of the turbine engine. The auxiliary lubrication system supplies the lubricant from the auxiliary reservoir to the one or more rotating components based on at least one of a pressure of the lubricant in the primary lubrication system, a pressure of fuel in the turbine engine, or a pressure of hydraulics of the turbine engine.
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公开(公告)号：US12276229B2
公开(公告)日：2025-04-15
申请号：US18463800
申请日：2023-09-08
Applicant: General Electric Company
Inventor： Brandon W. Miller , Geoffrey Whitener , Jeffrey D. Clements , Patrick Marrinan , Andrew J. Hank
IPC: F02C9/18
Abstract: A method of operating a turbine engine. The turbine engine includes a high-pressure compressor including a high-pressure compressor flowpath and a plurality of stages, and a bleed system. The bleed system includes a plurality of bleed flowpaths including a first bleed flowpath from one stage of the plurality of stages and a second bleed flowpath from another stage of the plurality of stages. The method includes directing compressed air through the high-pressure compressor flowpath, directing a first portion of the compressed air through the first bleed flowpath, the first portion of the compressed air having a first mass flow, directing a second portion of the compressed air through the second bleed flowpath, determining an altitude of the turbine engine, and changing the first mass flow of the first portion of the compressed air through the first bleed flowpath based on the altitude of the turbine engine.
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公开(公告)号：US20250101916A1
公开(公告)日：2025-03-27
申请号：US18972172
申请日：2024-12-06
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Xiaohua Zhang , Miriam Manzoni , Flavia Turi , Andrea Piazza , Arthur W. Sibbach , Brandon W. Miller
Abstract: A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: V G V G B · V G is a gutter volume of the gutter and VGB is a gearbox volume. The gas turbine engine includes a lubricant flow control system that includes a variable flow lubricant pump that generates a pump variable flow of lubricant to the gearbox assembly. The gearbox assembly has a variable consumption demand for delivery of lubricant. A lubricant flow controller is configured to generate a pump control command for the variable flow lubricant pump to produce the pump variable flow of lubricant based on the variable consumption demand.
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公开(公告)号：US20250074620A1
公开(公告)日：2025-03-06
申请号：US18461651
申请日：2023-09-06
Applicant: General Electric Company
Inventor： Brandon W. Miller , Daniel A. Niergarth , Arthur W. Sibbach
Abstract: An aircraft gas turbine includes a combustor that combusts compressed air and at least one fuel flow from at least one fuel source to generate combustion gases. A fuel supply system is arranged to provide at least one of a first flow of fuel to the combustor via a first fuel supply line and a second flow of a heated fuel to the combustor via a second fuel supply line. A fuel heat exchanger is arranged within the fuel supply system to generate the heated fuel that is heated above an autoignition temperature of the fuel, and a heat source communicates with the fuel heat exchanger for generating the heated fuel.
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公开(公告)号：US20250035052A1
公开(公告)日：2025-01-30
申请号：US18913330
申请日：2024-10-11
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Ravindra Shankar Ganiger , Andrea Piazza , Brandon W. Miller
IPC: F02C7/36
Abstract: A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine also includes a heat exchanger including an inner peripheral wall and an outer peripheral wall extending between an inlet and an outlet. The inner peripheral wall and the outer peripheral wall define a flow channel therebetween. The heat exchanger includes a plurality of fins disposed in the flow channel and dividing the flow channel into a plurality of flow passages.
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Patent Agency Ranking
公开(公告)号：US11994071B2
公开(公告)日：2024-05-28
申请号：US17652790
申请日：2022-02-28
Applicant: General Electric Company
Inventor： Hejie Li , Mathew Paul Thariyan , Diana Julieta Méndez Maya , Jorge Omar Mañón Cantú , Brandon W. Miller , Michael A. Benjamin , Brian Devendorf
Abstract: A fuel system including a fuel metering unit, a heat exchanger, a plurality of fuel nozzles, and a coke filtration system. The fuel metering unit is configured to meter a flow of a hydrocarbon fuel. The heat exchanger is fluidly connected to the fuel metering unit. The heat exchanger is configured to heat the hydrocarbon fuel to improve engine performance or efficiency. The plurality of fuel nozzles is fluidly connected to the heat exchanger downstream of the heat exchanger to receive the hydrocarbon fuel heated by the heat exchanger. The coke filtration system includes at least one filter to remove coke particles in the heated fuel. The coke filtration system is located upstream of the plurality of fuel nozzles and directly downstream of the heat exchanger.
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公开(公告)号：US11970957B2
公开(公告)日：2024-04-30
申请号：US17406930
申请日：2021-08-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Egbert Geertsema , Nicholas J. Kray , Brandon W. Miller
CPC classification number: F01D9/02 , F01D25/04 , F05D2220/323 , F05D2230/13 , F05D2230/30 , F05D2240/12
Abstract: Acoustic turbofan airfoil apparatus are disclosed. An example apparatus includes a platform of a turbofan engine, the platform including perforations to receive acoustic waves, acoustic chambers protruding from a first side of the platform, the acoustic chambers aligned with the perforations in a radial direction defined by the turbofan engine, the acoustic chambers to attenuate the acoustic waves, and an airfoil protruding from a second side of the platform opposite the first side of the platform.
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公开(公告)号：US20240044290A1
公开(公告)日：2024-02-08
申请号：US18489736
申请日：2023-10-18
Applicant: General Electric Company
Inventor： Brandon W. Miller , Robert Jon McQuiston , Stefan Joseph Cafaro , Eric Richard Westervelt , Michael A. Benjamin , Joel M. Haynes , Hejie Li
CPC classification number: F02C7/22 , F23R3/28 , F02C9/28 , F02C7/224 , F23R2900/00 , F05D2240/35 , F05D2220/32
Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system can be controlled to adjust one or more parameters of the fuel based on data received from the sensors.
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公开(公告)号：US20230305584A1
公开(公告)日：2023-09-28
申请号：US17702563
申请日：2022-03-23
Applicant: General Electric Company
Inventor： Biao Fang , David Justin Brady , John C. Glessner , Brandon W. Miller , Stephanie Glynn Cotten , William Dwight Gerstler , Daniel A. Niergarth , Michael Joseph Murray
CPC classification number: G05D7/0635 , F16K11/0712 , F16K31/406
Abstract: Example split valves for regulating a first flowrate and a second flowrate of a fluid within a closed loop systems are disclosed herein. An example split valve includes an electrohydraulic servo valve coupled to a first piston via a first hydraulic flowline and a second hydraulic flowline, the first piston to include a piston shaft, a first head, and a second head; one or more bellows fixed to at least one of the first head or the second head, the one or more bellows to hermetically seal the fluid from a hydraulic fluid; and a control system connected to the electrohydraulic servo valve, the control system to adjust the first flowrate and the second flowrate of the fluid through a first fluid chamber, the first piston to be located in the first fluid chamber.
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公开(公告)号：US20230265796A1
公开(公告)日：2023-08-24
申请号：US18310386
申请日：2023-05-01
Applicant: General Electric Company
Inventor： Brandon W. Miller , Robert Jon McQuiston , Stefan Joseph Cafaro , Eric Richard Westervelt , Michael A. Benjamin , Joel M. Haynes , Hejie Li
CPC classification number: F02C7/22 , F02C7/224 , F02C9/28 , F05D2260/20 , F05D2240/35 , F05D2220/32
Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.
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