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公开(公告)号：US20240052755A1
公开(公告)日：2024-02-15
申请号：US18081813
申请日：2022-12-15
Inventor： Stefan Joseph Cafaro , Inenhe Mohammed Khalid , James Ryan Reepmeyer , Amit Zutshi , Daniel Edward Mollmann , Arjan Johannes Hegeman , Rafal Sarba
CPC classification number: F01D17/162 , F01D7/00 , F05D2240/12 , F05D2220/323 , F05D2240/20
Abstract: A method of controlling an aeronautical gas turbine engine may be performed with an electronic controller. The method may include determining an airfoil pitch control command for at least one of a plurality of airfoils of the aeronautical gas turbine engine based at least in part on an excitation load acting upon the aeronautical gas turbine engine, and outputting the airfoil pitch control command to one or more actuators actuatable to change a pitch angle of the at least one of the plurality of airfoils. The airfoil pitch control command may be configured to augment and/or compensate for the excitation load acting upon the aeronautical gas turbine engine. The method may be embodied by a non-transitory computer-readable medium that includes computer-executable instructions, which when executed by a processor associated with the electronic controller, cause the electronic controller to perform the method.
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公开(公告)号：US12221893B2
公开(公告)日：2025-02-11
申请号：US18081813
申请日：2022-12-15
Inventor： Stefan Joseph Cafaro , Inenhe Mohammed Khalid , James Ryan Reepmeyer , Amit Zutshi , Daniel Edward Mollmann , Arjan Johannes Hegeman , Rafal Sarba
Abstract: A method of controlling an aeronautical gas turbine engine may be performed with an electronic controller. The method may include determining an airfoil pitch control command for at least one of a plurality of airfoils of the aeronautical gas turbine engine based at least in part on an excitation load acting upon the aeronautical gas turbine engine, and outputting the airfoil pitch control command to one or more actuators actuatable to change a pitch angle of the at least one of the plurality of airfoils. The airfoil pitch control command may be configured to augment and/or compensate for the excitation load acting upon the aeronautical gas turbine engine. The method may be embodied by a non-transitory computer-readable medium that includes computer-executable instructions, which when executed by a processor associated with the electronic controller, cause the electronic controller to perform the method.
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公开(公告)号：US20240052753A1
公开(公告)日：2024-02-15
申请号：US18081862
申请日：2022-12-15
Inventor： Amit Zutshi , Rafal Sarba , James Ryan Reepmeyer , Stefan Joseph Cafaro , Inenhe Mohammed Khalid , Daniel Edward Mollmann , Arjan Johannes Hegeman
Abstract: An open rotor engine includes a core engine, a plurality of guide vanes positioned within or extending from the core engine; and a pitch change assembly operably coupled to the plurality of guide vanes. The pitch change assembly includes one or more actuators configured to change a pitch angle of respective ones of the plurality of guide vanes, and a plurality of linkage arms that are respectively movable by actuation of at least one of the one or more actuators. The plurality of linkage arms are directly or indirectly coupled to a corresponding one of the plurality of guide vanes. The plurality of linkage arms may have a length that differs from one another, and such length may orient a displacement or a range of motion of the respective linkage arm to an envelope of rotation about a guide vane axis that differs as between the plurality of guide vanes.
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公开(公告)号：US20240051656A1
公开(公告)日：2024-02-15
申请号：US18085112
申请日：2022-12-20
Inventor： Amit Zutshi , Rafal Sarba , James Ryan Reepmeyer , Stefan Joseph Cafaro , Inenhe Mohammed Khalid , Daniel Edward Mollmann , Arjan Johannes Hegeman
Abstract: An open rotor aeronautical engine may include a core engine, a plurality of unducted airfoils, and a pitch change assembly. The pitch change assembly may include an ensemble actuator assembly and a unitary actuator assembly. The ensemble actuator assembly may have one or more ensemble actuators and a unison ring that is movable by actuation of the one or more ensemble actuators to collectively change a pitch angle of the plurality of unducted airfoils. The unitary actuator assembly comprising a plurality of unitary actuators respectively coupled to a corresponding one of the plurality of unducted airfoils, the plurality of unitary actuators respectively movable to change the pitch angle of the corresponding one of the plurality of unducted airfoils.
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公开(公告)号：US20220364894A1
公开(公告)日：2022-11-17
申请号：US17732945
申请日：2022-04-29
Applicant: General Electric Company
IPC: G01F1/667 , F01D21/00 , G01N29/036 , G01N29/44
Abstract: A fuel flow measuring system includes an ultrasonic fuel flow sensor. The fuel flow sensor includes a first transducer and a second transducer. The first transducer is excited at multiple different excitation frequencies and a voltage, an electric current, and a phase difference between the voltage and the electric current is sensed at the first transducer during excitation. Data points are generated based on the sensed readings and a model is fit to the data points to determine a complex impedance spectrum. The complex impedance spectrum indicates a range of excitation frequencies within a range of a peak resonance frequency of the first transducer. One or more characteristics of excitation signals directed to the second transducer are set based on the determined complex impedance spectrum. In this manner, the signal to noise ratio of ultrasonic signals emitted by the second transducer and received by the first transducer can be maximized.
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Patent Agency Ranking
公开(公告)号：US20220357190A1
公开(公告)日：2022-11-10
申请号：US17732960
申请日：2022-04-29
Applicant: General Electric Company
Abstract: A fuel flow measuring system includes an ultrasonic fuel flow sensor. The fuel flow sensor includes a first transducer and a second transducer. The first transducer is excited at multiple different excitation frequencies and a voltage, an electric current, and a phase difference between the voltage and the electric current is sensed at the first transducer during excitation. Data points are generated based on the sensed readings and a model is fit to the data points to determine a complex impedance spectrum. The complex impedance spectrum indicates a range of excitation frequencies within a range of a peak resonance frequency of the first transducer. One or more characteristics of excitation signals directed to the second transducer are set based on the determined complex impedance spectrum. In this manner, the signal to noise ratio of ultrasonic signals emitted by the second transducer and received by the first transducer can be maximized.
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公开(公告)号：US12264952B2
公开(公告)日：2025-04-01
申请号：US17732960
申请日：2022-04-29
Applicant: General Electric Company
Abstract: A fuel flow measuring system includes an ultrasonic fuel flow sensor. The fuel flow sensor includes a first transducer and a second transducer. The first transducer is excited at multiple different excitation frequencies and a voltage, an electric current, and a phase difference between the voltage and the electric current is sensed at the first transducer during excitation. Data points are generated based on the sensed readings and a model is fit to the data points to determine a complex impedance spectrum. The complex impedance spectrum indicates a range of excitation frequencies within a range of a peak resonance frequency of the first transducer. One or more characteristics of excitation signals directed to the second transducer are set based on the determined complex impedance spectrum. In this manner, the signal to noise ratio of ultrasonic signals emitted by the second transducer and received by the first transducer can be maximized.
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公开(公告)号：US20200049540A1
公开(公告)日：2020-02-13
申请号：US16059160
申请日：2018-08-09
Applicant: General Electric Company
Inventor： James Ryan Reepmeyer , Gagan Adibhatla
Abstract: A monitoring and control system for a flow duct and a method for determining a component status of an operational component disposed within a flow passage of the flow duct utilizing the system are provided. In one exemplary aspect, the system includes at least two sensors that are disposed within the flow passage and configured to sense a characteristic of a fluid flowing therethrough. The sensors may be averaging sensors. Each sensor extends circumferentially about an axial centerline defined by the flow duct. The sensors are arranged in an overlapped arrangement. Particularly, the sensors extend circumferentially about the axial centerline such that the sensors physically overlap one another circumferentially. Additionally, the sensors may be disposed within the same or substantially the same plane axially. Signals generated by the sensors may be utilized to monitor and control the fluid and various operational components disposed within the flow passage.
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公开(公告)号：US12270337B1
公开(公告)日：2025-04-08
申请号：US18501173
申请日：2023-11-03
Applicant: General Electric Company
Inventor： James Ryan Reepmeyer , Arthur William Sibbach
Abstract: A gas turbine engine oil flow control system can include a variable flow oil pump useful to provide oil at varying rates to a variety of oil consumers, such as, power gearboxes, engine shaft bearings, electrical generators, etc. Oil flow control valves that have an ability to provide a variable flow of oil can be used in conjunction with the variable flow oil pump. Flow sensors can be used along with an oil flow controller to measure a flow of oil at various points in the gas turbine engine oil flow control system. The oil flow controller can use information from the flow sensors along with a variable consumption demand association with one or more of the oil consumers (either provided to the oil controller or calculated based upon an operational need of the oil consumer) to change operation of the variable flow oil pump and/or oil flow control valve.
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公开(公告)号：US20240218836A1
公开(公告)日：2024-07-04
申请号：US18089845
申请日：2022-12-28
Applicant: General Electric Company
Inventor： Manxue Lu , James Ryan Reepmeyer , R. Sheldon Carpenter
IPC: F02C9/00 , B64D13/06 , G06F1/3206 , G06F1/329
CPC classification number: F02C9/00 , B64D13/06 , G06F1/3206 , G06F1/329 , B64D2013/0618 , F05D2220/323 , F05D2260/81 , F05D2270/335 , F05D2270/44
Abstract: An integrated system and methods therefore are provided. An integrated system has individual power and/or thermal systems and a coordinated control system. The coordinated control system receives mission demands and priorities from an upstream system. The coordinated control system also receives a status and a prediction from each individual system, such as an individual system's operating mode status and its capability margin. The coordinated control system performs a conflict of interest check and generates a relative status for each individual system based on the status and predictions associated with the individual systems. The coordinated control system determines an operating mode and an allowed demand for each individual system based on the relative statuses and the mission demands and priorities. The coordinated control system outputs the operating modes to the individual systems and maps the allowed demands to individual system demands. The individual system demands are output to the individual systems.
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