Patents by Inventor Michael M. Romero
Michael M. Romero 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: 11873766Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.Type: GrantFiled: March 1, 2023Date of Patent: January 16, 2024Assignee: RTX CORPORATIONInventors: Daniel Bernard Kupratis, Neil J. Terwilliger, Michael M. Romero
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Publication number: 20230212985Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.Type: ApplicationFiled: March 1, 2023Publication date: July 6, 2023Inventors: Daniel Bernard Kupratis, Neil J. Terwilliger, Michael M. Romero
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Patent number: 11649763Abstract: Techniques for determining a fan spool speed value associated with a hybrid electric gas engine (“engine”) are described herein. For example, a method includes generating a first fan spool speed value based on a base extraction amount. The method further includes generating a change in the first fan spool speed value based on a flight condition and a change in extraction amount. The method further includes generating a second fan spool speed value based on the extraction amount and an augmentation value for intersection of a combustion instability and burner pressure limit. The method further includes generating a second change in the second fan spool speed value based on the flight condition and the change in extraction amount. The method further includes determining a final fan spool speed value and operating the engine at the final fan spool speed value.Type: GrantFiled: June 23, 2022Date of Patent: May 16, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Michael M. Romero, Neil J. Terwilliger, Daniel B. Kupratis
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Patent number: 11629646Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.Type: GrantFiled: September 28, 2018Date of Patent: April 18, 2023Assignee: Raytheon Technologies CorporationInventors: Daniel Bernard Kupratis, Neil Terwilliger, Michael M. Romero
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Publication number: 20220349354Abstract: A surge control system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The surge control system also includes sensors configured to collect sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to detect surge event from the sensor data, determine an amount of power to apply to the rotor system, and increase the amount of power provided to the rotor system to recover from the surge event.Type: ApplicationFiled: July 18, 2022Publication date: November 3, 2022Applicant: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Michael M. Romero, Gary Collopy
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Patent number: 11473496Abstract: A hybrid engine includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid engine includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to monitor for a transient operation request of the hybrid engine, provide the transient operation request to one or more management systems of the hybrid engine to determine whether one or more faults are detected by the one or more management systems, modify one or more stall margin adjustment parameters of the gas turbine engine based on detecting the one or more faults by the one or more management system, and adjust operation of the hybrid engine based on the one or more stall margin adjustment parameters.Type: GrantFiled: February 5, 2020Date of Patent: October 18, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Michael M. Romero, Michael Hrach
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Patent number: 11448138Abstract: A surge control system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The surge control system also includes sensors configured to collect sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to detect surge event from the sensor data, determine an amount of power to apply to the rotor system, and increase the amount of power provided to the rotor system to recover from the surge event.Type: GrantFiled: February 6, 2020Date of Patent: September 20, 2022Assignee: Raytheon Technologies CorporationInventors: Michael M. Romero, Gary Collopy
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Patent number: 10934972Abstract: A method of maintaining rotor tip clearance and compressor operational line during a transient operation of a gas turbine engine is disclosed. In various embodiments, the method includes applying high spool auxiliary power to a high speed spool for a first time period, applying low spool auxiliary power to a low speed spool for a second time period, sensing one or more operational parameters of the gas turbine engine during the transient operation, and ceasing application of power to the high speed spool, based on the one or more operational parameters.Type: GrantFiled: July 19, 2018Date of Patent: March 2, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Michael Hrach, Michael M. Romero
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Publication number: 20200248619Abstract: A hybrid engine includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid engine includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to monitor for a transient operation request of the hybrid engine, provide the transient operation request to one or more management systems of the hybrid engine to determine whether one or more faults are detected by the one or more management systems, modify one or more stall margin adjustment parameters of the gas turbine engine based on detecting the one or more faults by the one or more management system, and adjust operation of the hybrid engine based on the one or more stall margin adjustment parameters.Type: ApplicationFiled: February 5, 2020Publication date: August 6, 2020Inventors: Michael M. Romero, Michael Hrach
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Publication number: 20200102885Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.Type: ApplicationFiled: September 28, 2018Publication date: April 2, 2020Inventors: Daniel Bernard Kupratis, Neil Terwilliger, Michael M. Romero
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Publication number: 20200056497Abstract: A method of operating an aircraft hybrid gas turbofan during an idle mode of operation includes reducing a fuel flow to a primary gas turbine engine and boosting a high spool of the primary gas turbine engine using a secondary gas turbine engine via a first power linkage connecting the primary and secondary gas turbine engines, such that a net fuel reduction is achieved. The net fuel reduction accounts for fuel flow to the primary gas turbine engine and fuel flow to the secondary gas turbine engine.Type: ApplicationFiled: June 4, 2019Publication date: February 20, 2020Inventors: Neil Terwilliger, Daniel Bernard Kupratis, Michael M. Romero
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Publication number: 20200025149Abstract: A method of maintaining rotor tip clearance and compressor operational line during a transient operation of a gas turbine engine is disclosed. In various embodiments, the method includes applying high spool auxiliary power to a high speed spool for a first time period, applying low spool auxiliary power to a low speed spool for a second time period, sensing one or more operational parameters of the gas turbine engine during the transient operation, and ceasing application of power to the high speed spool, based on the one or more operational parameters.Type: ApplicationFiled: July 19, 2018Publication date: January 23, 2020Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Michael Hrach, Michael M. Romero