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公开(公告)号：US20200317370A1
公开(公告)日：2020-10-08
申请号：US16376294
申请日：2019-04-05
Applicant: United Technologies Corporation
Inventor： Nagendra Somanath , Kurt R. Heinemann , Evan Selin , Glenn Levasseur
Abstract: A repair system for gas turbine engine components includes a computer system configured to receive a set of measured parameters for each gas turbine engine component in a plurality of substantially identical gas turbine engine components, and determine a variation model based on the set of measured parameters wherein each of the gas turbine engine components is an as-run component and has been exposed to a substantially identical general wear pattern. The computer system includes at least one simulated engine model. The simulated engine model is configured to determine a predicted operation of each gas turbine engine component in the plurality of substantially identical gas turbine engine components. A correlation system is configured to correlate variations in the set of parameters for each of the gas turbine engine components in the plurality of substantially identical gas turbine engine components with a set of the predicted operations of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, thereby generating a predictive model based on the variations. A repair module is configured to generate a repair formula based on the predictive model. The repair formula is configured to receive a set of measured parameters of an as-run gas turbine engine component and determine a suggested repair capable of repairing the as-run gas turbine engine component.
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2.发明申请公开(公告)号：US20200224588A1
公开(公告)日：2020-07-16
申请号：US16248861
申请日：2019-01-16
Applicant: United Technologies Corporation
Inventor： Nagendra Somanath , Brendan T. McAuliffe , Joseph B. Staubach
Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger is disposed in the primary flowpath downstream of the turbine section. The heat exchanger includes a first inlet for receiving fluid from the primary flowpath and a first outlet for expelling fluid received at the first inlet. The heat exchanger further includes a second inlet fluidly connected to a supercritical CO2 (sCO2) bottoming cycle and a second outlet connected to the sCO2 coolant circuit. The sCO2 bottoming cycle is a recuperated Brayton cycle.
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3.发明授权公开(公告)号：US10160550B1
公开(公告)日：2018-12-25
申请号：US15851136
申请日：2017-12-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nagendra Somanath , Edgar A Bernal , Michael J Giering
Abstract: Systems and methods for aircraft ice detection and mitigation. The system for aircraft ice detection and mitigation may comprise a controller, and a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving, by the controller, a video signal from a first data, mapping, by the controller, the video signal to a discriminative feature space in response to a mapping function, generating, by the controller, a first extracted feature in response to the mapping function and the discriminative feature space, generating, by the controller, a behavioral model in response to the first extracted feature, and determining, by the controller, an icing condition of the aircraft in response to the extracted feature and the behavioral model.
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公开(公告)号：US11485520B2
公开(公告)日：2022-11-01
申请号：US16104435
申请日：2018-08-17
Applicant: United Technologies Corporation
Inventor： Nagendra Somanath , Ryan B. Noraas , Michael J. Giering
Abstract: A method for designing a material for an aircraft component includes training a neural network to correlate microstructural features of an alloy with material properties of the alloy by at least providing a set of images of the alloy to the neural network. Each of the images in the set of images has varied constituent compositions. The method further includes providing the neural network with a set of determined material properties corresponding to each image, associating the microstructural features of each image with the set of empirically determined data corresponding to the image, and determining non-linear relationships between the microstructural features and corresponding empirically determined material properties via a machine learning algorithm, receiving a set of desired material properties of the alloy for aircraft component, and determining a set of microstructural features capable of achieving the desired material properties of the alloy based on the determined non-linear relationships.
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公开(公告)号：US11447271B2
公开(公告)日：2022-09-20
申请号：US16376324
申请日：2019-04-05
Applicant: United Technologies Corporation
Inventor： Nagendra Somanath , Kurt R. Heinemann , Evan Selin , Glenn Levasseur
Abstract: A maintenance scheduling system for gas turbine engine components includes a computer system configured to receive a set of measured parameters for each gas turbine engine component in a plurality of substantially identical gas turbine engine components, and determine a variation model based on the set of measured parameters. Each of the gas turbine engine components is a single route component and has been utilized in a substantially identical single route. The computer system includes at least one simulated engine model. The simulated engine model is configured to determine a predicted operation of each gas turbine engine component in the plurality of substantially identical gas turbine engine components. A correlation system is configured to correlate variations in the set of parameters for each of the gas turbine engine components in the plurality of substantially identical gas turbine engine components with a set of the predicted operations of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, thereby generating a predictive model based on the variations. A maintenance schedule module is configured determine a predictive model operable to determine a predicted wear pattern of a second single route component that is substantially identical to the gas turbine engine components.
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Patent Agency Ranking
公开(公告)号：US11248989B2
公开(公告)日：2022-02-15
申请号：US16448365
申请日：2019-06-21
Applicant: United Technologies Corporation
Inventor： Nagendra Somanath , Justin R. Urban , Michael J. Giering , Quan Long , Alexandria Dorgan
Abstract: A system for providing real time aircraft engine sensor analysis includes a computer system configured to receive an engine operation data set in real time. The computer system includes a machine learning based analysis tool and a user interface configured to display a real time analysis of the engine operation data set. The user interface includes at least one portion configured to identify a plurality of anomalies in the engine operation data set.
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公开(公告)号：US20200317371A1
公开(公告)日：2020-10-08
申请号：US16376324
申请日：2019-04-05
Applicant: United Technologies Corporation
Inventor： Nagendra Somanath , Kurt R. Heinemann , Evan Selin , Glenn Levasseur
Abstract: A maintenance scheduling system for gas turbine engine components includes a computer system configured to receive a set of measured parameters for each gas turbine engine component in a plurality of substantially identical gas turbine engine components, and determine a variation model based on the set of measured parameters. Each of the gas turbine engine components is a single route component and has been utilized in a substantially identical single route. The computer system includes at least one simulated engine model. The simulated engine model is configured to determine a predicted operation of each gas turbine engine component in the plurality of substantially identical gas turbine engine components. A correlation system is configured to correlate variations in the set of parameters for each of the gas turbine engine components in the plurality of substantially identical gas turbine engine components with a set of the predicted operations of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, thereby generating a predictive model based on the variations. A maintenance schedule module is configured determine a predictive model operable to determine a predicted wear pattern of a second single route component that is substantially identical to the gas turbine engine components.
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公开(公告)号：US12162627B2
公开(公告)日：2024-12-10
申请号：US16376294
申请日：2019-04-05
Applicant: United Technologies Corporation
Inventor： Nagendra Somanath , Kurt R. Heinemann , Evan Selin , Glenn Levasseur
Abstract: A repair system for gas turbine engine components includes a computer system configured to receive a set of measured parameters for each gas turbine engine component in a plurality of substantially identical gas turbine engine components, and determine a variation model based on the set of measured parameters wherein each of the gas turbine engine components is an as-run component and has been exposed to a substantially identical general wear pattern. The computer system includes at least one simulated engine model. The simulated engine model is configured to determine a predicted operation of each gas turbine engine component in the plurality of substantially identical gas turbine engine components. A correlation system is configured to correlate variations in the set of parameters for each of the gas turbine engine components in the plurality of substantially identical gas turbine engine components with a set of the predicted operations of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, thereby generating a predictive model based on the variations. A repair module is configured to generate a repair formula based on the predictive model. The repair formula is configured to receive a set of measured parameters of an as-run gas turbine engine component and determine a suggested repair capable of repairing the as-run gas turbine engine component.
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公开(公告)号：US11230948B2
公开(公告)日：2022-01-25
申请号：US16248884
申请日：2019-01-16
Applicant: United Technologies Corporation
Inventor： Brendan T. McAuliffe , Joseph B. Staubach , Nagendra Somanath
Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger is disposed in the primary flowpath downstream of the turbine section. The heat exchanger includes a first inlet for receiving fluid from the primary flowpath and a first outlet for expelling fluid received at the first inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) bottoming cycle and a second outlet connected to the sCO2 bottoming cycle. The sCO2 bottoming cycle is an overexpanded, recuperated Brayton cycle.
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10.发明申请公开(公告)号：US20200224589A1
公开(公告)日：2020-07-16
申请号：US16248884
申请日：2019-01-16
Applicant: United Technologies Corporation
Inventor： Brendan T. McAuliffe , Joseph B. Staubach , Nagendra Somanath
Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger is disposed in the primary flowpath downstream of the turbine section. The heat exchanger includes a first inlet for receiving fluid from the primary flowpath and a first outlet for expelling fluid received at the first inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) bottoming cycle and a second outlet connected to the sCO2 bottoming cycle. The sCO2 bottoming cycle is an overexpanded, recuperated Brayton cycle.
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