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公开(公告)号：US20240174375A1
公开(公告)日：2024-05-30
申请号：US18316450
申请日：2023-05-12
Applicant: General Electric Company
Inventor： Michael Joseph Murray , Victor Moreno Patan , Brandon W. Miller
Abstract: An aircraft fuel system includes a first fuel storage tank arranged to store a first fuel, a second fuel storage tank arranged to store a reduced oxygen fuel, and a fuel tank inerting system arranged to provide a reduced oxygen gas through a fuel contained within the second fuel storage tank to generate the reduced oxygen fuel within the second fuel storage tank. The fuel tank inerting system may include a fuel tank sparging system to inject the reduced oxygen gas directly into the fuel contained within the second fuel storage tank to generate the reduced oxygen fuel.
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公开(公告)号：US20230059995A1
公开(公告)日：2023-02-23
申请号：US17406930
申请日：2021-08-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Egbert Geertsema , Nicholas J. Kray , Brandon W. Miller
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：US20250109695A1
公开(公告)日：2025-04-03
申请号：US18883919
申请日：2024-09-12
Applicant: General Electric Company
Inventor： Brandon W. Miller , Arthur W. Sibbach , Andrew Hudecki , Patrick S. Sage , Eric Barre , Stefan Joseph Cafaro , Gerardo Perez Perez , Kevin Graziano
Abstract: An engine includes a gearbox coupled to a first element and a second element. The engine may include a first speed sensor positioned on an input side of the gearbox, the first speed sensor operable to detect a first speed of the first element. The engine may further include a second speed sensor positioned on an output side of the gearbox, the second speed sensor operable to detect a second speed of the second element. The engine includes a controller comprising a processor and a memory coupled to the processor. The processor may be configured to receive data from the first speed sensor and the second speed sensor. The processor is also configured to detect a trigger event based on the data from the first speed sensor and the data from the second speed sensor. Upon detecting the trigger event, the processor communicates a command to an engine operational system.
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公开(公告)号：US20250101881A1
公开(公告)日：2025-03-27
申请号：US18947789
申请日：2024-11-14
Applicant: General Electric Company
Inventor： Ryan T. Roehm , Brandon W. Miller , Robert Eugene Dyson , Arthur W. Sibbach , Donald S. Yeager , John C. Schilling
IPC: F01D25/04
Abstract: Variable diameter thrust link apparatus are disclosed. A thrust link for an aircraft engine includes a forward end coupled to the aircraft engine, the forward end having a first diameter, and an aft end coupled to the aircraft engine or a pylon, the aft end having the first diameter, wherein the thrust link defines a thrust link span that extends from the forward end to the aft end, wherein a second diameter greater than the first diameter is defined between the forward end and the aft end, wherein the second diameter spans a center diameter span that is equivalent to or between 60% and 90% of the thrust link span.
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公开(公告)号：US20250100700A1
公开(公告)日：2025-03-27
申请号：US18947832
申请日：2024-11-14
Applicant: General Electric Company
Inventor： Ryan T. Roehm , Brandon W. Miller , Robert Eugene Dyson , Arthur W. Sibbach , Donald S. Yeager , John C. Schilling
Abstract: Fluid-filled thrust link apparatus and associated method are disclosed. A thrust link for an aircraft engine includes a first wall having a forward portion and an aft portion at opposite ends of the thrust link, the forward portion coupled to the aircraft engine, the aft portion coupled to the aircraft engine, a pylon, or an aircraft associated with the aircraft engine, and a second wall within an interior area surrounded by the first wall, the second wall spaced apart from the first wall, a space between the first wall and the second wall defining a channel within the interior area, the channel including a fluid, the fluid pressurized based on a damping ratio to withstand a resonant vibration frequency generated by the aircraft engine.
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Patent Agency Ranking
公开(公告)号：US20250084797A1
公开(公告)日：2025-03-13
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：US20250084788A1
公开(公告)日：2025-03-13
申请号：US18463793
申请日：2023-09-08
Applicant: General Electric Company
Inventor： Brandon W. Miller , Andrew J. Hank , Scott D. Hunter , Geoffrey Whitener , Paul Pezzi , Jeffrey D. Clements
Abstract: A turbine engine includes a high-pressure (HP) compressor and a bleed system. The HP compressor includes an HP compressor flowpath and a plurality of stages of HP compressor rotor blades and HP compressor stator vanes. The bleed system includes a plurality of bleed flowpaths including at least three bleed flowpaths in fluid communication with the HP compressor flowpath. The plurality of bleed flowpaths direct compressed air from the HP compressor flowpath. At least two of the bleed flowpaths are at successive stages of the plurality of stages.
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公开(公告)号：US12228042B1
公开(公告)日：2025-02-18
申请号：US18537490
申请日：2023-12-12
Applicant: General Electric Company
Inventor： Brandon W. Miller , Arthur W. Sibbach , Andrew Hudecki
Abstract: A lubrication system for a turbine engine having a longitudinal centerline axis and one or more rotating components. The lubrication system includes a primary lubrication system that supplies lubricant to the one or more rotating components during normal operation of the turbine engine. The lubrication system also includes an auxiliary lubrication system. The auxiliary lubrication system includes an auxiliary reservoir and a lubricant dispersion device. The auxiliary reservoir stores the lubricant therein. The lubricant dispersion device rotates about the longitudinal centerline axis. The lubricant dispersion device collects the lubricant in the auxiliary reservoir and disperses the lubricant to the one or more rotating components as the lubricant dispersion device rotates.
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公开(公告)号：US20250035206A1
公开(公告)日：2025-01-30
申请号：US18910919
申请日：2024-10-09
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Ravindra Shankar Ganiger , Andrea Piazza , Brandon W. Miller
IPC: F16H57/025 , F16H57/02 , F16H57/023
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 gear includes a first gear that is a split sun gear including a forward sun gear and an aft sun gear separate from the forward sun gear. The forward sun gear and the aft sun gear are each rotationally coupled to a rotating shaft of the gas turbine engine.
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公开(公告)号：US20250035041A1
公开(公告)日：2025-01-30
申请号：US18913857
申请日：2024-10-11
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
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 is provided that adjusts parameters of the fuel based on data received from the sensors.
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