Patents by Inventor Subhradeep Chowdhury
Subhradeep Chowdhury has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11905891Abstract: An engine control system includes an engine controller configured to execute an open-loop model of the engine control system. The open-loop model receives a measured effector and boundary condition parameter vector and generates a synthesized engine operating parameter based on the measured effector and boundary condition parameter vector. The engine controller calculates a corrector error value between the synthesized engine operating parameter and a measured engine operating parameter, and determines an open loop corrector error calculated as a difference between the corrector error and a vector-matrix product of corrector state vector and a gain map/function. The engine controller applies the gain map/function to the open loop corrector error to determine an effector and boundary condition error vector of the measured effector and boundary condition parameter vector.Type: GrantFiled: August 20, 2021Date of Patent: February 20, 2024Assignee: RTX CORPORATIONInventors: Boris Karpman, Mark A. Bushman, Subhradeep Chowdhury, Richard P. Meisner
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Patent number: 11674411Abstract: A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.Type: GrantFiled: June 28, 2021Date of Patent: June 13, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Subhradeep Chowdhury, David M. Bostwick, David Gelwan, Frederick M. Schwarz
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Publication number: 20230090879Abstract: An engine control system includes an engine controller configured to execute an open-loop model of the engine control system. The open-loop model receives a measured effector and boundary condition parameter vector and generates a synthesized engine operating parameter based on the measured effector and boundary condition parameter vector. The engine controller calculates a corrector error value between the synthesized engine operating parameter and a measured engine operating parameter, and determines an open loop corrector error calculated as a difference between the corrector error and a vector-matrix product of corrector state vector and a gain map/function. The engine controller applies the gain map/function to the open loop corrector error to determine an effector and boundary condition error vector of the measured effector and boundary condition parameter vector.Type: ApplicationFiled: August 20, 2021Publication date: March 23, 2023Inventors: Boris Karpman, Mark A. Bushman, Subhradeep Chowdhury, Richard P. Meisner
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Publication number: 20220243653Abstract: 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.Type: ApplicationFiled: April 14, 2022Publication date: August 4, 2022Inventors: Stephen A. Witalis, Ramesh Rajagopalan, Subhradeep Chowdhury
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Patent number: 11319834Abstract: An engine control system includes an electronic hardware engine controller in signal communication with at least one engine sensor, which measures an engine operating parameter (Ycrtr_t). The engine controller generates a synthesized engine operating parameter (Ycrtr) calculates an error (ERRcrtr) between the engine operating parameter (Ycrtr_t) and the synthesized engine operating parameter (Ycrtr). The engine controller further determines a corrector error parameter (Xcrtr) and determines a faulty sensor among the at least one engine sensor based on a comparison between the error value (ERRcrtr) and the corrector error parameter (Xcrtr).Type: GrantFiled: January 25, 2018Date of Patent: May 3, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Boris Karpman, Richard P. Meisner, Subhradeep Chowdhury
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Patent number: 11306654Abstract: 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 an idle fuel burn schedule in a taxi mode of the aircraft and operate the second gas turbine engine with a sub-idle fuel burn schedule in the taxi mode of the aircraft. The sub-idle fuel burn schedule includes a reduction of the idle fuel burn schedule. A fuel flow of the first gas turbine engine and the second gas turbine engine is increased above the idle fuel burn schedule prior to takeoff of the aircraft.Type: GrantFiled: November 26, 2019Date of Patent: April 19, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Stephen A. Witalis, Ramesh Rajagopalan, Subhradeep Chowdhury
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Patent number: 11203950Abstract: An engine control system includes an electronic hardware engine controller in signal communication with an actuator and an engine sensor. The actuator operates at a plurality of different positions to control operation of an engine. The engine sensor measures an engine operating parameter. The engine controller generates a synthesized engine operating parameter, and adjusts the position of the actuator based on the synthesized engine operating parameter in response to detecting a faulty engine sensor.Type: GrantFiled: January 25, 2018Date of Patent: December 21, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Boris Karpman, Richard P. Meisner, Subhradeep Chowdhury
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Patent number: 11199139Abstract: 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 an idle fuel burn schedule in a taxi mode of the aircraft and dry crank the second gas turbine engine in a first pre-takeoff portion of the taxi mode to cool the second gas turbine engine absent fuel burn by the second gas turbine engine. The control system operates the second gas turbine engine with a sub-idle fuel burn schedule in a second pre-takeoff portion of the taxi mode of the aircraft. The sub-idle fuel burn schedule includes a reduction of the idle fuel burn schedule. A fuel flow of the first gas turbine engine and the second gas turbine engine is increased above the idle fuel burn schedule prior to takeoff of the aircraft.Type: GrantFiled: March 20, 2019Date of Patent: December 14, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Ramesh Rajagopalan, Subhradeep Chowdhury, Stephen A Witalis, William C. Lamberti
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Publication number: 20210324758Abstract: A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.Type: ApplicationFiled: June 28, 2021Publication date: October 21, 2021Inventors: Subhradeep Chowdhury, David M. Bostwick, David Gelwan, Frederick M. Schwarz
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Patent number: 11047257Abstract: A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.Type: GrantFiled: July 21, 2017Date of Patent: June 29, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Subhradeep Chowdhury, David M. Bostwick, David Gelwan, Frederick M. Schwarz
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Publication number: 20200200099Abstract: 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 an idle fuel burn schedule in a taxi mode of the aircraft and dry crank the second gas turbine engine in a first pre-takeoff portion of the taxi mode to cool the second gas turbine engine absent fuel burn by the second gas turbine engine. The control system operates the second gas turbine engine with a sub-idle fuel burn schedule in a second pre-takeoff portion of the taxi mode of the aircraft. The sub-idle fuel burn schedule includes a reduction of the idle fuel burn schedule. A fuel flow of the first gas turbine engine and the second gas turbine engine is increased above the idle fuel burn schedule prior to takeoff of the aircraft.Type: ApplicationFiled: March 20, 2019Publication date: June 25, 2020Inventors: Ramesh Rajagopalan, Subhradeep Chowdhury, Stephen A Witalis, William C. Lamberti
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Publication number: 20200200127Abstract: 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 an idle fuel burn schedule in a taxi mode of the aircraft and operate the second gas turbine engine with a sub-idle fuel burn schedule in the taxi mode of the aircraft. The sub-idle fuel burn schedule includes a reduction of the idle fuel burn schedule. A fuel flow of the first gas turbine engine and the second gas turbine engine is increased above the idle fuel burn schedule prior to takeoff of the aircraft.Type: ApplicationFiled: November 26, 2019Publication date: June 25, 2020Inventors: Stephen A. Witalis, Ramesh Rajagopalan, Subhradeep Chowdhury
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Patent number: 10557418Abstract: An engine control system includes an electronic hardware engine controller and an actuator that operates at different positions to control operation of an engine. An actuator sensor measures an actuator position, and the engine controller generates a synthesized actuator position. In response to detecting a faulty actuator, a faulty actuator sensor, or both, the engine controller adjusts the position of the actuator based on the synthesized actuator position.Type: GrantFiled: January 25, 2018Date of Patent: February 11, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Boris Karpman, Richard P. Meisner, Subhradeep Chowdhury
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Publication number: 20190226407Abstract: An engine control system includes an electronic hardware engine controller and an actuator that operates at different positions to control operation of an engine. An actuator sensor measures an actuator position, and the engine controller generates a synthesized actuator position. In response to detecting a faulty actuator, a faulty actuator sensor, or both, the engine controller adjusts the position of the actuator based on the synthesized actuator position.Type: ApplicationFiled: January 25, 2018Publication date: July 25, 2019Inventors: Boris Karpman, Richard P. Meisner, Subhradeep Chowdhury
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Publication number: 20190226354Abstract: An engine control system includes an electronic hardware engine controller in signal communication with at least one engine sensor, which measures an engine operating parameter (Ycrtr_t). The engine controller generates a synthesized engine operating parameter (Ycrtr) calculates an error (ERRcrtr) between the engine operating parameter (Ycrtr_t) and the synthesized engine operating parameter (Ycrtr). The engine controller further determines a corrector error parameter (Xcrtr) and determines a faulty sensor among the at least one engine sensor based on a comparison between the error value (ERRcrtr) and the corrector error parameter (Xcrtr).Type: ApplicationFiled: January 25, 2018Publication date: July 25, 2019Inventors: Boris Karpman, Richard P. Meisner, Subhradeep Chowdhury
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Publication number: 20190226353Abstract: An engine control system includes an electronic hardware engine controller in signal communication with an actuator and an engine sensor. The actuator operates at a plurality of different positions to control operation of an engine. The engine sensor measures an engine operating parameter. The engine controller generates a synthesized engine operating parameter, and adjusts the position of the actuator based on the synthesized engine operating parameter in response to detecting a faulty engine sensor.Type: ApplicationFiled: January 25, 2018Publication date: July 25, 2019Inventors: Boris Karpman, Richard P. Meisner, Subhradeep Chowdhury
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Publication number: 20180023413Abstract: A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.Type: ApplicationFiled: July 21, 2017Publication date: January 25, 2018Inventors: Subhradeep Chowdhury, David M. Bostwick, David Gelwan, Frederick M. Schwarz
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Patent number: 6925883Abstract: A probe includes a first tube having a first end positioned at a measurement location, and a second end; a second tube having a first end, and a second end; a connector having a transducer for connecting the second end of the first tube to the second end of the second tube; and a terminating element attached to the first end of the second tube, wherein the second tube is of a length sufficient to substantially eliminate the incidence of resonance.Type: GrantFiled: August 28, 2003Date of Patent: August 9, 2005Assignee: United Technologies CorporationInventor: Subhradeep Chowdhury
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Publication number: 20050044958Abstract: A probe comprising a first tube comprising a first end positioned at a measurement location, and a second end, a second tube comprising a first end, and a second end, a connector comprising a transducer for connecting the second end of the first tube to the second end of the second tube, and a terminating element attached to said first end of the second tube wherein the second tube is of a length sufficient to substantially eliminate the incidence of resonance.Type: ApplicationFiled: August 28, 2003Publication date: March 3, 2005Inventor: Subhradeep Chowdhury