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公开(公告)号：US12292029B2
公开(公告)日：2025-05-06
申请号：US18015595
申请日：2021-07-13
Applicant: General Electric Company
Inventor： Pascal Meyer , Biao Fang , Norman Arnold Turnquist , Xiaopeng Li , Gregory Edward Cooper , Christopher James Kenny
Abstract: A tower structure particularly suited for a wind turbine includes a lower tower section formed of concrete and an upper tower section formed of steel. A transition system connects the upper tower section to the lower tower section, the transition system including a concrete component having a tubular wall with a base portion fixed on the lower tower section and a head portion connected to the upper tower section. The head portion extends radially outward beyond the upper tower section. A plurality of first tensioning tendons extend longitudinally at least partially through the tubular wall and are anchored to the concrete component at a top face of the head portion at locations radially outward of the upper tower section.
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公开(公告)号：US12292003B2
公开(公告)日：2025-05-06
申请号：US17571609
申请日：2022-01-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Craig Alan Gonyou , Nathan Joel Mullenix , Fei Huang
Abstract: A leakage management assembly for an orifice configured to limit a flow of at least one of a leakage fluid and a cooling fluid past an instrument positioned within the orifice are provided. The leakage management assembly includes a labyrinth ferrule including an annular ferrule body having a central bore extending therethrough. The labyrinth ferrule further includes an annular assembly cone formed at a first end of the labyrinth ferrule. The annular assembly cone includes an annular convergent lip and is configured to facilitate directing the instrument into the central bore. The labyrinth ferrule also includes a plurality of labyrinthine annular restrictions extending from a radially inner surface of the annular body toward the central bore. A combustor and a gas turbine engine including such a seal assembly are also provided.
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公开(公告)号：US12290409B2
公开(公告)日：2025-05-06
申请号：US16237154
申请日：2018-12-31
Applicant: General Electric Company
Inventor： Thomas Huepf , Christian Fritz Perrey , Thomas Andrew Kraus
IPC: A61B8/00
Abstract: Various methods and systems are provided for ultrasound imaging. In one embodiment, a method comprises, during an ultrasound scan, acquiring a series of ultrasound frames with a first transmit power, receiving a command to pause the ultrasound scan, and acquiring at least one ultrasound frame with a second transmit power higher than the first transmit power responsive to receiving the command. In this way, the image quality of an image displayed while a scan is paused may be increased.
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公开(公告)号：US20250137406A1
公开(公告)日：2025-05-01
申请号：US19006941
申请日：2024-12-31
Applicant: General Electric Company
Inventor： Pradeep Hemant Sangli , Santosh Kumar Potnuru , Keith A. Miedema , Matthew D. Brothers , Ravindra Shankar Ganiger
Abstract: Separators for use with gas turbine engines are disclosed herein. An example cabin bleed system disclosed herein includes a bleed line coupled to a gas turbine engine, a separator defining a cavity fluidly coupled to the bleed line, the separator including a first ring including a first opening fluidly coupled to the cavity. a second ring surrounding the first ring, the second ring including a second opening fluidly coupled to a cabin of an aircraft, and a filter disposed in a fluid pathway extending between the first opening and the second opening.
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公开(公告)号：US12287094B2
公开(公告)日：2025-04-29
申请号：US18355449
申请日：2023-07-20
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Varun S. Lakshmanan , Michael T. Bucaro , Pradeep Naik , Steven C. Vise , Michael A. Benjamin
Abstract: A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.
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Patent Agency Ranking
公开(公告)号：US12286932B1
公开(公告)日：2025-04-29
申请号：US18441736
申请日：2024-02-14
Applicant: General Electric Company
Inventor： Hejie Li , Hiranya Nath , Habeeb Kunnummal Manat , Shai Birmaher , Craig Alan Gonyou , Anquan Wang , Michael A. Benjamin
Abstract: A combustor of a turbine engine has a combustion chamber for combusting fuel and air, generating heat. A fuel nozzle-mixer assembly mixes and injects fuel and air into the combustion chamber for combustion. The assembly has a heat shield at an aft end for shielding the assembly from the heat. A centerbody outer shell defines a cooling air flow cavity. A cooling air flow gap is defined between the centerbody outer shell and the heat shield. The centerbody outer shell has cooling air exit holes between the cooling air flow cavity and the cooling air flow gap, the air passing through the cooling air exit holes and into the cooling air flow gap. The cooling air exits the cooling air flow gap at a cooling air exit angle, the cooling air exit angle having a non-zero axially aft component, displacing the combustion downstream, to protect the assembly.
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公开(公告)号：US12286901B2
公开(公告)日：2025-04-29
申请号：US17468834
申请日：2021-09-08
Applicant: General Electric Company
Inventor： Kirk D. Gallier
Abstract: An apparatus and method for a turbine engine for can include an engine component. The engine component can include an interior cooling passage at least partially defining a cooling circuit for passing a flow of cooling fluid through the component. Film holes provide for exhausting a portion of the cooling fluid to an exterior of the component, to form a cooling film along an exterior hot surface of the engine component. A deflector can be position within the cooling passage upstream form the film hole.
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公开(公告)号：US12286889B2
公开(公告)日：2025-04-29
申请号：US18350496
申请日：2023-07-11
Applicant: General Electric Company
Inventor： Avinash Natarajan , Vishnu Vardhan Venkata Tatiparthi , Ravindra Shankar Ganiger , Nagashiresha G , Prateek Mathur , Michał Tomasz Kuropatwa , Arthur W Sibbach
Abstract: Systems, apparatus, articles of manufacture, and methods are disclosed to improve fan operability control using smart materials. An engine comprising an engine surface in an airflow path, a sensor positioned on the engine surface, and a smart-material-based feature positioned on the engine surface, the smart-material-based feature triggered to modify the airflow path when the sensor outputs an indication of a detected deviation from a reference value of an operating parameter of the engine.
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公开(公告)号：US20250129747A1
公开(公告)日：2025-04-24
申请号：US18592651
申请日：2024-03-01
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Tomasz Iglewski
Abstract: A nacelle for a gas turbine engine includes an interior portion along a radial direction of the gas turbine engine and a heat exchanger. The interior portion defines a heat exchanger duct including an inlet and an outlet. The heat exchanger is disposed in the heat exchanger duct between the inlet and the outlet. The inlet is disposed aft of the outlet along a central axis of the nacelle.
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公开(公告)号：US20250129723A1
公开(公告)日：2025-04-24
申请号：US18489533
申请日：2023-10-18
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor assembly and a stator assembly. The turbine engine including a primary stage of airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor assembly. A subsidiary stage of airfoils located upstream of the primary stage of airfoils and circumferentially arranged about the engine centerline.
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