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公开(公告)号：US20240401490A1
公开(公告)日：2024-12-05
申请号：US18798993
申请日：2024-08-09
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Stefan Joseph Cafaro , Robert Jon McQuiston
IPC: F01D7/00 , B32B7/022 , B64C1/00 , B64C1/12 , B64C1/38 , B64D27/12 , B64D45/00 , F01D5/14 , F01D5/18 , F01D5/30 , F01D9/04 , F01D15/10 , F01D15/12 , F01D17/16 , F01D25/12 , F02C3/113 , F02C6/20 , F02C7/264 , F02C7/32 , F02C7/36 , F02C9/00 , F02C9/22 , F02K1/66 , F02K1/76
Abstract: A propulsion system is provided, the propulsion system including a variable pitch rotor assembly including a plurality of blades coupled to a disk. The plurality of blades includes a first blade configured to articulate a first blade pitch separately from a second blade configured to articulate a second blade pitch. A vane assembly is positioned in aerodynamic relationship with the variable pitch rotor assembly. A core engine including a high speed spool and a low speed spool, wherein the low speed spool is operably coupled to the rotor assembly. One or more controllers is configured to execute operations. The operations include articulating the first blade of the rotor assembly, wherein articulating the first blade alters the first blade pitch, and articulating the second blade of the rotor assembly, wherein articulating the second blade alters the second blade pitch.
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公开(公告)号：US11834196B2
公开(公告)日：2023-12-05
申请号：US17071000
申请日：2020-10-15
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Stefan Joseph Cafaro , Robert Jon McQuiston
IPC: F01D7/00 , B64D45/00 , B32B7/022 , B64C1/12 , B64C1/38 , B64D27/12 , F01D5/14 , F01D5/18 , F01D5/30 , F01D9/04 , F01D15/10 , F01D15/12 , F01D17/16 , F01D25/12 , F02C6/20 , F02C7/264 , F02C7/32 , F02C7/36 , F02C9/00 , F02C9/22 , F02K1/66 , F02K1/76 , B64C1/00 , F02C3/113
CPC classification number: B64D45/00 , B32B7/022 , B64C1/12 , B64C1/38 , B64D27/12 , F01D5/146 , F01D5/187 , F01D5/30 , F01D5/3007 , F01D7/00 , F01D9/041 , F01D15/10 , F01D15/12 , F01D17/162 , F01D25/12 , F02C6/206 , F02C7/264 , F02C7/32 , F02C7/36 , F02C9/00 , F02C9/22 , F02K1/66 , F02K1/76 , B32B2307/558 , B32B2307/72 , B32B2307/732 , B32B2571/02 , B32B2605/18 , B64C2001/0072 , F02C3/113 , F05D2220/323 , F05D2220/325 , F05D2230/60 , F05D2240/12 , F05D2240/24 , F05D2240/60 , F05D2250/37 , F05D2260/201 , F05D2260/30 , F05D2260/4031 , F05D2260/70 , F05D2270/05 , F05D2270/051 , F05D2270/121 , F05D2270/304 , F05D2270/71 , F05D2270/81
Abstract: A computing system for an unducted rotor engine with a variable pitch vane assembly in aerodynamic relationship with an unducted rotor assembly, including a sensor-based controller configured to execute a first set of operations and a model-based controller configured to execute a second set of operations. The first set of operations includes obtaining a first signal corresponding to a commanded low spool speed; obtaining a second signal indicative of a pitch angle corresponding to thrust output from the unducted rotor assembly and variable pitch vane assembly; generating a pitch feedback signal corresponding to a commanded adjustment to the pitch angle based at least on one or both of a variable blade pitch angle or a variable vane pitch angle. The second set of operations include obtaining a desired thrust output via a throttle input; determining, at least via a power management block, a commanded thrust output signal; receiving the commanded thrust output signal; and generating an output signal.
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公开(公告)号：US20210262398A1
公开(公告)日：2021-08-26
申请号：US17317199
申请日：2021-05-11
Applicant: General Electric Company
Inventor： Paul Robert Gemin , Sridhar Adibhatla , Arthur Vorwerk Radun , Kevin Richard Leamy
Abstract: A method for operating a gas turbine engine having a starter-electric generator driven by one of a plurality of shafts of the gas turbine engine is provided. The method includes determining a desired amount of thrust to be produced by the gas turbine engine, as well as a desired amount of electrical power to be generated by the starter-electric generator of the gas turbine engine. The method operates the gas turbine engine to produce the desired amount of thrust, while producing less than the desired amount of electrical power using the starter-electric generator. Producing less than the desired amount of electrical power using the starter-electric generator allows for the desired amount of thrust production, or allows for the desired amount of thrust production more quickly.
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公开(公告)号：US20210108576A1
公开(公告)日：2021-04-15
申请号：US17071045
申请日：2020-10-15
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Stefan Joseph Cafaro , Robert Jon McQuiston
Abstract: A propulsion system is provided, the propulsion system including a variable pitch rotor assembly including a plurality of blades coupled to a disk. The plurality of blades includes a first blade configured to articulate a first blade pitch separately from a second blade configured to articulate a second blade pitch. A vane assembly is positioned in aerodynamic relationship with the variable pitch rotor assembly. A core engine including a high speed spool and a low speed spool, wherein the low speed spool is operably coupled to the rotor assembly. One or more controllers is configured to execute operations. The operations include articulating the first blade of the rotor assembly, wherein articulating the first blade alters the first blade pitch, and articulating the second blade of the rotor assembly, wherein articulating the second blade alters the second blade pitch.
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公开(公告)号：US10196928B2
公开(公告)日：2019-02-05
申请号：US15059116
申请日：2016-03-02
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Jeffrey Wayne Litzler
Abstract: A pipe fault detection system is provided for a gas turbine engine having a compressor and a turbine. The pipe fault detection system includes a cooling manifold configured to direct cooling air from the compressor to the turbine. The cooling manifold includes at least two cooling pipes, a sensor configured to detect an operating condition indicative of a pipe break, and a controller configured to control the amount of cooling air through the cooling manifold in response to the operating condition detected by the sensor.
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Patent Agency Ranking
公开(公告)号：US20180306054A1
公开(公告)日：2018-10-25
申请号：US15493044
申请日：2017-04-20
Applicant: General Electric Company
Inventor： Sridhar Adibhatla
CPC classification number: F01D25/002 , F04D29/70 , F05D2260/80 , F05D2260/81 , F05D2260/821
Abstract: A compressor water-wash advisory system generates compressor water-wash notifications or initiates on-line water-wash cycles for a gas turbine or turbofan jet engine based on monitored health parameters of the engine. A high-fidelity model of engine compressor performance defines nominal expected values of engine performance parameters, such as compressor efficiency and air flow, as a function of current operating conditions. A tracking filter component compares the modeled performance parameters with actual calculated performance parameters obtained from sensor data, and maintains a separate actual model of engine performance that modifies the nominal performance parameter values to match the calculated parameter values using parameter modifiers. A health index is derived as a function of the parameter modifiers, and a water-wash notification is generated when the health index is indicative of a significant loss of fuel efficiency due to dirt accumulation in the engine's compressor.
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公开(公告)号：US20180297718A1
公开(公告)日：2018-10-18
申请号：US15490524
申请日：2017-04-18
Applicant: General Electric Company
Inventor： Sridhar Adibhatla
Abstract: Methods, apparatus, and articles of manufacture to monitor health information of a turbine engine are disclosed. An example apparatus includes a parameter calculator to determine a baseline value of a set of health parameters for a turbine engine of a vehicle based on a first set of sensor measurements to estimate an initial health of turbine engine components, and determine an operational value of the set of health parameters based on a second set of sensor measurements to estimate an operational health of the turbine engine components. The apparatus further includes a difference calculator to calculate a difference between the baseline value and the operational value to assess a health of the turbine engine, a database to store the first set of sensor measurements or the initial health of the turbine engine components, and an alert generator to generate an alert when the difference satisfies a threshold, the alert including a notification to perform maintenance on the component based on the difference and the threshold.
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公开(公告)号：US10604278B2
公开(公告)日：2020-03-31
申请号：US15490524
申请日：2017-04-18
Applicant: General Electric Company
Inventor： Sridhar Adibhatla
Abstract: An example apparatus includes a parameter calculator to determine a baseline value of a set of health parameters for a turbine engine of a vehicle based on a first set of sensor measurements to estimate an initial health of turbine engine components, and determine an operational value of the set of health parameters based on a second set of sensor measurements to estimate an operational health of the turbine engine components. The apparatus further includes a difference calculator to calculate a difference between the baseline value and the operational value to assess a health of the turbine engine, a database to store the first set of sensor measurements or the initial health of the turbine engine components, and an alert generator to generate an alert when the difference satisfies a threshold, the alert including a notification to perform maintenance on the component based on the difference and the threshold.
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公开(公告)号：US20190376408A1
公开(公告)日：2019-12-12
申请号：US16001369
申请日：2018-06-06
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , John Thomas Herbon
Abstract: A system and method for determining performance of a turbine engine, and operation thereof. The system and method includes a plurality of sensors and one or more computing devices executing operations including acquiring a plurality of parameter sets each corresponding to a plurality of engine conditions in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine; comparing the plurality of parameter sets to determine a health condition corresponding to a location at the engine; and generating a health condition prediction at the engine based on the compared parameters.
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公开(公告)号：US20180357840A1
公开(公告)日：2018-12-13
申请号：US15621279
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Michael Thomas Gansler , Sridhar Adibhatla , Brandon Wayne Miller
Abstract: A computer-implemented method of assessing a health of a gas turbine engine of a hybrid-electric propulsion system for an aircraft includes receiving, by one or more computing devices, data indicative of an amount of electrical power provided to, or extracted from, an electric machine. The method also includes receiving, by the one or more computing devices, data indicative of an operating parameter of the hybrid-electric propulsion system. The method also includes assessing, by the one or more computing devices, a health of the gas turbine engine based at least in part on the received data indicative of the amount of electrical power provided to, or extracted from, the electric machine and the received data indicative of the operating parameter of the hybrid electric propulsion system. The method also includes providing, by the one or more computing devices, information to a user indicative of the health of the gas turbine engine.
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