Patents by Inventor David Gelwan
David Gelwan 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: 11807378Abstract: A system is provided for alternating starter use during multi-engine motoring in an aircraft. The system includes a first engine starting system of a first engine. A first controller is in communication with a second controller that controls a second engine starting system of a second engine, the first controller being configured to intermittently direct power to the first engine starting system to alternately accelerate and decelerate the first engine during motoring with respect to the second engine.Type: GrantFiled: March 25, 2020Date of Patent: November 7, 2023Assignee: RTX CORPORATIONInventors: David Gelwan, Jesse W. Clauson, Frederick M. Schwarz
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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: 20230160347Abstract: A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.Type: ApplicationFiled: January 12, 2023Publication date: May 25, 2023Inventors: Timothy J. Crowley, Sorin Bengea, Manuj Dhingra, David Gelwan, Kevin Hendricks, Joshua Adams, Martin Richard Amari, Richard P. Meisner, David Lei Ma
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Patent number: 11555455Abstract: A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine an estimate of hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a model predictive control state and a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the model predictive control state and the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.Type: GrantFiled: February 6, 2020Date of Patent: January 17, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Timothy J. Crowley, Sorin Bengea, Manuj Dhingra, David Gelwan, Kevin Hendricks, Joshua Adams, Martin Richard Amari, Richard P. Meisner, David Lei Ma
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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: 20200347787Abstract: A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine an estimate of hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a model predictive control state and a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the model predictive control state and the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.Type: ApplicationFiled: February 6, 2020Publication date: November 5, 2020Inventors: Timothy J. Crowley, Sorin Bengea, Manuj Dhingra, David Gelwan, Kevin Hendricks, Joshua Adams, Martin Richard Amari, Richard P. Meisner, David Lei Ma
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Patent number: 10787968Abstract: A system for gas turbine engine motoring includes an air turbine starter coupled to a gearbox of a gas turbine engine and a starter air valve in fluid communication with the air turbine starter to drive motoring of the gas turbine engine responsive to a regulated pressure from a compressed air source. A manual override of the starter air valve is adjustable to one or more predefined intermediate positions that partially open the starter air valve to limit a motoring speed of the gas turbine engine below a resonance speed of a starting spool of the gas turbine engine responsive to the regulated pressure.Type: GrantFiled: September 30, 2016Date of Patent: September 29, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Jesse W. Clauson, David Gelwan
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Publication number: 20200239151Abstract: A system is provided for alternating starter use during multi-engine motoring in an aircraft. The system includes a first engine starting system of a first engine. A first controller is in communication with a second controller that controls a second engine starting system of a second engine, the first controller being configured to intermittently direct power to the first engine starting system to alternately accelerate and decelerate the first engine during motoring with respect to the second engine.Type: ApplicationFiled: March 25, 2020Publication date: July 30, 2020Inventors: David Gelwan, Jesse W. Clauson, Frederick M. Schwarz
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Gas turbine start system to enable rotor thermal stabilization with backup bleed bypass cooling mode
Patent number: 10711700Abstract: A system is provided comprising: a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source; a manual override operably connected to the starter air valve, the manual override is operable to open the starter air valve a select percentage by moving the manual override to a detent engaged position, wherein the select percentage is operable to allow enough airflow to achieve the maximum allowed motoring speed of the gas turbine engine; and a pressure regulating bleed valve in fluid communication with the starter air valve, the pressure regulating bleed valve operable to bleed a portion of the compressed air flow to regulate a motoring speed of the gas turbine engine in response to detection of the manual override in a detent engaged position.Type: GrantFiled: February 1, 2017Date of Patent: July 14, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Michael D. Greenberg, Robert Goodman, David Gelwan, Jesse W. Clauson -
Patent number: 10669945Abstract: According to an aspect, a system includes a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source. The system also includes a variable-position electromechanical device operable to adjust positioning of the starter air valve and a discrete-position electromechanical device operable to adjust positioning of the starter air valve and limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to a pulse width modulation control based on a failure of the variable-position electromechanical device.Type: GrantFiled: February 6, 2017Date of Patent: June 2, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Michael D. Greenberg, David Gelwan, Jesse W. Clauson, Robert Goodman, John M. Dehais, Myles R. Kelly
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Patent number: 10633106Abstract: A system is provided for alternating starter use during multi-engine motoring in an aircraft. The system includes a first engine starting system of a first engine and a controller. The controller is operable to coordinate control of the first engine starting system to alternate use of power from a power source relative to use of the power by one or more other engine starting systems of the aircraft while maintaining a starting spool speed of the first engine below a resonance speed of the starting spool during motoring of the first engine.Type: GrantFiled: July 18, 2017Date of Patent: April 28, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: David Gelwan, Jesse W. Clauson, Frederick M. Schwarz
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Patent number: 10384791Abstract: A system is provided for cross engine coordination during gas turbine engine motoring. The system includes a first gas turbine engine of a first engine system, a first air turbine starter of the first engine system, a first starter air valve of the first engine system, and a controller. The controller is operable to command the first starter air valve to control delivery of compressed air to the first air turbine starter during motoring of the first gas turbine engine, monitor cross engine data of a second gas turbine engine of a second engine system to detect a present condition or a commanded action that modifies an aspect of the compressed air received at the first starter air valve, and command an adjustment to the first engine system to compensate for the modified aspect of the compressed air based on the cross engine data.Type: GrantFiled: July 18, 2017Date of Patent: August 20, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: David Gelwan, Jesse W. Clauson, James K. Berry
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Patent number: 10221774Abstract: A system is provided for speed control during motoring of a gas turbine engine of an aircraft. The system includes an air turbine starter, a starter air valve operable to deliver compressed air to the air turbine starter, and a controller. The controller is operable to adjust the starter air valve to control motoring of the gas turbine engine based on measured feedback with lead compensation to reject disturbances attributable to dual to single or single to dual engine starting transitions.Type: GrantFiled: July 21, 2016Date of Patent: March 5, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: David Gelwan, Jesse W. Clauson, Jason B. Solomonides, Timothy J. Gaudet, Joshua Adams
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Publication number: 20190040799Abstract: Systems and methods for rotating a gas turbine engine during a motoring cycle are provided. The system may comprise a controller in electronic communication with an auxiliary power unit (APU), a starter air valve, and a gas turbine engine. The APU may supply compressed air to the starter air valve which may supply the compressed air to an engine starter in mechanical communication with the engine. The rotational speed of the engine may be controlled by the engine starter based on the pressure of the compressed air received from the starter air valve. The controller may be configured to control airflow and air pressure through the system, by modulating the airflow from the APU and/or from the starter air valve.Type: ApplicationFiled: August 7, 2017Publication date: February 7, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: David Gelwan, David M. Bostwick, Jesse W. Clauson
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Publication number: 20180223738Abstract: According to an aspect, a system includes a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source. The system also includes a variable-position electromechanical device operable to adjust positioning of the starter air valve and a discrete-position electromechanical device operable to adjust positioning of the starter air valve and limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to a pulse width modulation control based on a failure of the variable-position electromechanical device.Type: ApplicationFiled: February 6, 2017Publication date: August 9, 2018Inventors: Michael D. Greenberg, David Gelwan, Jesse W. Clauson, Robert Goodman, John M. Dehais, Myles R. Kelly
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GAS TURBINE START SYSTEM TO ENABLE ROTOR THERMAL STABILIZATION WITH BACKUP BLEED BYPASS COOLING MODE
Publication number: 20180216537Abstract: A system is provided comprising: a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source; a manual override operably connected to the starter air valve, the manual override is operable to open the starter air valve a select percentage by moving the manual override to a detent engaged position, wherein the select percentage is operable to allow enough airflow to achieve the maximum allowed motoring speed of the gas turbine engine; and a pressure regulating bleed valve in fluid communication with the starter air valve, the pressure regulating bleed valve operable to bleed a portion of the compressed air flow to regulate a motoring speed of the gas turbine engine in response to detection of the manual override in a detent engaged position.Type: ApplicationFiled: February 1, 2017Publication date: August 2, 2018Inventors: Michael D. Greenberg, Robert Goodman, David Gelwan, Jesse W. Clauson -
Publication number: 20180094588Abstract: A system for gas turbine engine motoring includes an air turbine starter coupled to a gearbox of a gas turbine engine and a starter air valve in fluid communication with the air turbine starter to drive motoring of the gas turbine engine responsive to a regulated pressure from a compressed air source. A manual override of the starter air valve is adjustable to one or more predefined intermediate positions that partially open the starter air valve to limit a motoring speed of the gas turbine engine below a resonance speed of a starting spool of the gas turbine engine responsive to the regulated pressure.Type: ApplicationFiled: September 30, 2016Publication date: April 5, 2018Inventors: Jesse W. Clauson, David Gelwan
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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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Publication number: 20180022464Abstract: A system is provided for cross engine coordination during gas turbine engine motoring. The system includes a first gas turbine engine of a first engine system, a first air turbine starter of the first engine system, a first starter air valve of the first engine system, and a controller. The controller is operable to command the first starter air valve to control delivery of compressed air to the first air turbine starter during motoring of the first gas turbine engine, monitor cross engine data of a second gas turbine engine of a second engine system to detect a present condition or a commanded action that modifies an aspect of the compressed air received at the first starter air valve, and command an adjustment to the first engine system to compensate for the modified aspect of the compressed air based on the cross engine data.Type: ApplicationFiled: July 18, 2017Publication date: January 25, 2018Inventors: David Gelwan, Jesse W. Clauson, James K. Berry