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公开(公告)号：US20240175409A1
公开(公告)日：2024-05-30
申请号：US18071141
申请日：2022-11-29
Applicant: Raytheon Technologies Corporation
Inventor： David Wasselin , Nancy Poisson , Brian V. Winebrenner , Bradley C. Schafer , Ramesh Rajagopalan
CPC classification number: F02K1/76 , B64D31/09 , B64D45/04 , B64F5/60 , G05D1/617 , G05D1/654 , B64D2045/0085 , G05D2109/22
Abstract: A system of an aircraft includes a thrust reverser control configured to control deployment of one or more thrust reversers of the aircraft, a brake control configured to control operation of one or more brakes of the aircraft, and a controller. The controller is configured to detect a landing condition of the aircraft, determine one or more thrust reverser deployment and brake control parameters for one or more current conditions at a target location of the aircraft, and control the one or more thrust reversers and the one or more brakes upon landing at the target location based on the one or more thrust reverser deployment and brake control parameters. The controller can modify one or more control parameters of the aircraft based on detecting a change in the one or more current conditions at the target location or a fault condition of the aircraft.
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公开(公告)号：US20230332547A1
公开(公告)日：2023-10-19
申请号：US18185111
申请日：2023-03-16
Applicant: Raytheon Technologies Corporation
Inventor： Bradley C. Schafer , Ramesh Rajagopalan
IPC: F02C9/00
CPC classification number: F02C9/00 , F05D2270/303 , F05D2270/301
Abstract: Aircraft control architectures include a triplex sensor configured to output three signals. First and second channels are configured to receive respective signals of the three output signals, with each channel having a respective processor and are configured to output respective control signals. A remote interface device is configured to receive a third signal of the three output signals and an effector is configured to receive the first and second control signals and perform an action in response to the control signals. An output from the remote interface device is transmitted to the first and second channels and an output from each channel is received at the other channel. The control signals are based on the received signals, the received outputs from the remote interface device, and the received output from the other channel.
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公开(公告)号：US20230219693A1
公开(公告)日：2023-07-13
申请号：US18152920
申请日：2023-01-11
Applicant: Raytheon Technologies Corporation
Inventor： Stephen A. Witalis , Ramesh Rajagopalan , Manuj Dhingra
CPC classification number: B64D31/06 , B64D27/10 , F02C6/00 , F02C7/26 , B64D27/24 , F05D2260/85 , B64D2027/026
Abstract: An engine system for an aircraft includes a gas turbine engine and a control system. The control system is configured to motor the gas turbine engine, absent fuel burn, during a taxi mode of the aircraft. The control system is further configured to accelerate a motoring speed of the gas turbine engine, absent fuel burn, above an idle speed of the gas turbine engine to provide propulsion during the taxi mode. The control system is configured to decrease the motoring speed of the gas turbine engine, absent fuel burn, based on a change in a starting mode of the gas turbine engine or the aircraft reaching a targeted new position.
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Patent Agency Ranking
公开(公告)号：US20220243653A1
公开(公告)日：2022-08-04
申请号：US17720900
申请日：2022-04-14
Applicant: Raytheon Technologies Corporation
Inventor： Stephen A. Witalis , Ramesh Rajagopalan , Subhradeep Chowdhury
Abstract: An engine system for an aircraft includes a first gas turbine engine, a second gas turbine engine, and a control system. The control system is configured to operate the first gas turbine engine with a sub-idle fuel burn schedule based on detecting landing of the aircraft, where the sub-idle fuel burn schedule includes a reduction of an idle fuel burn schedule. The control system is configured to operate the second gas turbine engine with the idle fuel burn schedule based on detecting landing of the aircraft.
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公开(公告)号：US20210071585A1
公开(公告)日：2021-03-11
申请号：US17012600
申请日：2020-09-04
Applicant: Raytheon Technologies Corporation
Inventor： Daniel Bernard Kupratis , Coy Bruce Wood , Ramesh Rajagopalan , Zubair Ahmed Baig
Abstract: A gas turbine engine includes a generator that is configured to be driven by a turbine section, an electric motor that is configured to receive at least a portion of electric power from the generator, a gearbox that is mechanically coupled to both the electric motor and the generator, and a control system that has an operational amplifier that is configured to synchronize operation of the electric motor and the generator. The operational amplifier electrically couples the electric motor to the generator and is configured to define an electrical gain that matches a mechanical gain that is defined by the gearbox.
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公开(公告)号：US20240271784A1
公开(公告)日：2024-08-15
申请号：US18110186
申请日：2023-02-15
Applicant: Raytheon Technologies Corporation
Inventor： Orin G. Avidane , Andre M. Ajami , Coy Bruce Wood , Joseph V. Mantese , David L. Lincoln , Stephen K. Kramer , Ramesh Rajagopalan
CPC classification number: F23N5/082 , F23N1/005 , F23R3/28 , F23N2229/04 , F23N2229/16 , F23N2229/18
Abstract: A combustion assembly for a gas turbine engine includes a combustor, a monochromator, and a photodetector assembly. The combustor forms a combustion chamber. The monochromator is disposed outside the combustion chamber. The monochromator is configured to receive an optical input from the combustion chamber and direct an optical output. The optical input has a range of light wavelengths. The optical output has a subset of the range of light wavelengths. The photodetector assembly is disposed outside the combustion chamber. The photodetector assembly is configured to receive the optical output from the monochromator and generate an output signal representative of one or more optical characteristics of the optical output.
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公开(公告)号：US20230166857A1
公开(公告)日：2023-06-01
申请号：US18071138
申请日：2022-11-29
Applicant: Raytheon Technologies Corporation
Inventor： David Wasselin , Nancy Poisson , Brian V. Winebrenner , Bradley C. Schafer , Ramesh Rajagopalan
Abstract: A system of an aircraft includes one or more gas turbine engines and a controller. The controller is configured to detect a pre-takeoff condition of the aircraft and determine one or more control parameters for one or more current conditions at a target location of the aircraft. The controller is further configured to determine a final takeoff speed of the one or more gas turbine engines based on the one or more control parameters. At least one of the one or more gas turbine engines is controlled to accelerate to the final takeoff speed after transitioning from the pre-takeoff condition to a takeoff condition.
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公开(公告)号：US11319882B2
公开(公告)日：2022-05-03
申请号：US17012600
申请日：2020-09-04
Applicant: Raytheon Technologies Corporation
Inventor： Daniel Bernard Kupratis , Coy Bruce Wood , Ramesh Rajagopalan , Zubair Ahmed Baig
Abstract: A gas turbine engine includes a generator that is configured to be driven by a turbine section, an electric motor that is configured to receive at least a portion of electric power from the generator, a gearbox that is mechanically coupled to both the electric motor and the generator, and a control system that has an operational amplifier that is configured to synchronize operation of the electric motor and the generator. The operational amplifier electrically couples the electric motor to the generator and is configured to define an electrical gain that matches a mechanical gain that is defined by the gearbox.
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