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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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公开(公告)号：US10774651B1
公开(公告)日：2020-09-15
申请号：US15869124
申请日：2018-01-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Kurt R. Heinemann , Sumin Tao , Christopher B. Jelks , Xuedong Zhou , Mark David Ring , Konstantinos Panagiotis Giannakopolous , Lisa I. Brilliant
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.85-3.15 inch (72.4-80.0 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.52-1.82 inch (38.6-46.2 mm). The airfoil element includes at least two of a first mode with a frequency of 506±10% Hz, a second mode with a frequency of 1732±10% Hz, a third mode with a frequency of 2268±10% Hz, a fourth mode with a frequency of 4007±10% Hz, a fifth mode with a frequency of 4851±10% Hz and a sixth mode with a frequency of 6416±10% Hz.
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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：US11236616B1
公开(公告)日：2022-02-01
申请号：US15868499
申请日：2018-01-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Kurt R. Heinemann , Sumin Tao , Christopher B. Jelks , Xuedong Zhou , Mark David Ring , Konstantinos Panagiotis Giannakopoulos , Kate Hudon , John Joseph Papalia
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 4.47-4.77 inch (113.5-121.2 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 2.57-2.87 inch (65.3-72.9 mm). The airfoil element includes at least two of a first mode with a frequency of 297±10% Hz, a second mode with a frequency of 1035±10% Hz, a third mode with a frequency of 1488±10% Hz, a fourth mode with a frequency of 1524±10% Hz, a fifth mode with a frequency of 2855±10% Hz and a sixth mode with a frequency of 4462±10% Hz.
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公开(公告)号：US10815785B1
公开(公告)日：2020-10-27
申请号：US15869119
申请日：2018-01-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Kurt R. Heinemann , Sumin Tao , Christopher B. Jelks , Xuedong Zhou , Mark David Ring , Konstantinos Panagiotis Giannakopoulos , Kate Hudon , John Joseph Papalia
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.99-3.29 inch (75.9-83.6 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.44-1.74 inch (36.6-44.2 mm). The airfoil element includes at least two of a first mode with a frequency of 430±10% Hz, a second mode with a frequency of 1459±10% Hz, a third mode with a frequency of 2036±10% Hz, a fourth mode with a frequency of 3615±10% Hz, a fifth mode with a frequency of 4722±10% Hz and a sixth mode with a frequency of 5591±10% Hz.
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Patent Agency Ranking
公开(公告)号：US20200012751A1
公开(公告)日：2020-01-09
申请号：US16026627
申请日：2018-07-03
Applicant: United Technologies Corporation
Inventor： Daniel A. Snyder , Kurt R. Heinemann , Glenn Levasseur
IPC: G06F17/50
Abstract: A method for qualifying a gas turbine engine component includes creating a first set of substantially identical gas turbine engine components via a uniform manufacturing procedure, determining a set of as-manufactured parameters of each gas turbine engine component in the first set, and determining a variance model of the first set. The variance model includes a representative parameter profile, which includes a plurality of component parameter profiles. The sum of each of the component parameter profiles is the representative parameter profile. The method also includes determining at least one predicted response models based at least in part on the variance model, identifying as-manufactured parameters of a second engine component, applying the as-manufactured parameters of the second engine component to the at least one predicted response models, thereby generating a predicted response output, and qualifying the second engine component for usage in at least one gas turbine engine corresponding to the at least one predicted response model.
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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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公开(公告)号：US11170140B2
公开(公告)日：2021-11-09
申请号：US16026627
申请日：2018-07-03
Applicant: United Technologies Corporation
Inventor： Daniel A. Snyder , Kurt R. Heinemann , Glenn Levasseur
IPC: G06F30/20 , G06F111/10 , G06N20/00
Abstract: A method for qualifying a gas turbine engine component includes creating a first set of substantially identical gas turbine engine components via a uniform manufacturing procedure, determining a set of as-manufactured parameters of each gas turbine engine component in the first set, and determining a variance model of the first set. The variance model includes a representative parameter profile, which includes a plurality of component parameter profiles. The sum of each of the component parameter profiles is the representative parameter profile. The method also includes determining at least one predicted response models based at least in part on the variance model, identifying as-manufactured parameters of a second engine component, applying the as-manufactured parameters of the second engine component to the at least one predicted response models, thereby generating a predicted response output, and qualifying the second engine component for usage in at least one gas turbine engine corresponding to the at least one predicted response model.
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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：US09965572B1
公开(公告)日：2018-05-08
申请号：US14596599
申请日：2015-01-14
Applicant: United Technologies Corporation
Inventor： Joshua Daniel Winn , William A. Sowa , Michael D. Werkheiser , Kurt R. Heinemann
IPC: G06F17/50
CPC classification number: G06F17/50
Abstract: A system for collaborating on a component according to an exemplary aspect of the present disclosure includes, among other things, a computing device configured to execute a first multi-user CAx environment including a synchronization module. The synchronization module is configured to selectively cause a display module at a first multi-user CAx environment to display data corresponding to changes to at least one subcomponent feature relating to an assembly model caused by a second multi-user CAx environment during an assembly session when at least one predetermined criterion is met. A method for collaborating on a component design is also disclosed.
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