Patents by Inventor Joseph Lawrence Simonetti
Joseph Lawrence Simonetti 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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Publication number: 20240060425Abstract: A hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator and configured to be driven by a power turbine, an output power shaft mated to the power turbine and extending through a central axis of the gas generator and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member, wherein the at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.Type: ApplicationFiled: October 16, 2023Publication date: February 22, 2024Applicant: Lockheed Martin CorporationInventors: Joseph Lawrence Simonetti, Mark P. Eisenhauer, Michael Strauss
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Patent number: 11788428Abstract: A hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator and configured to be driven by a power turbine, an output power shaft mated to the power turbine and extending through a central axis of the gas generator and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member. The at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.Type: GrantFiled: January 21, 2021Date of Patent: October 17, 2023Assignee: LOCKHEED MARTIN CORPORATIONInventors: Joseph Lawrence Simonetti, Mark P. Eisenhauer, Michael Strauss
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Publication number: 20220228505Abstract: A hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator and configured to be driven by a power turbine, an output power shaft mated to the power turbine and extending through a central axis of the gas generator and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member. The at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.Type: ApplicationFiled: January 21, 2021Publication date: July 21, 2022Applicant: Lockheed Martin CorporationInventors: Joseph Lawrence Simonetti, Mark P. Eisenhauer, Michael Strauss
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Patent number: 11268390Abstract: An exhaust system for an engine includes an exhaust nozzle located adjacent an outlet end of the engine to receive a primary flow of exhaust gasses expelled from the engine, an inlet opening formed between the exhaust nozzle and the outlet end of the engine through which a secondary flow is provided to the exhaust nozzle, and a vortex generator arranged within the exhaust system at a position where both the primary flow and the secondary flow are present. The vortex generator interrupts at least one of the primary flow and the secondary flow.Type: GrantFiled: July 19, 2018Date of Patent: March 8, 2022Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Joseph Lawrence Simonetti, Donald W. Lamb, Jr., Patrick Ormande Bowles
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Patent number: 10773814Abstract: A control system for an in-flight engine restart system of a rotorcraft includes an engine control unit that controls and detects status of an engine. The control system also includes a flight control computer that communicates with the engine control unit, an engine operation control system, and a pilot interface including pilot controls. The engine operation control system includes a processor that initiates a health check of the in-flight engine restart system to determine an in-flight engine restart system status. The engine operation control system processes engine mode of operation commands to establish an engine mode of operation, and delivers commands to aspects of the in-flight engine restart system including the engine control unit based on processing of the engine mode of operation commands. The engine operation control system reports the in-flight engine restart system status and results of the engine mode of operation commands to the flight control computer.Type: GrantFiled: July 20, 2016Date of Patent: September 15, 2020Assignee: Sikorsky Aircraft CorporationInventors: Michael Peter Strauss, Michael Joseph DeVita, Mark Denton Bystry, Jr., Joseph Lawrence Simonetti, Carl A. Palmer
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Patent number: 10738698Abstract: A method of operating a multi-engine, rotary wing aircraft in a single engine, in-flight mode, the method includes stopping a first engine while operating a second engine; closing variable inlet guide vanes on the first engine; and turning a gas generator of the first engine at a reference rotational speed.Type: GrantFiled: March 22, 2016Date of Patent: August 11, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventor: Joseph Lawrence Simonetti
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Patent number: 10625868Abstract: A bleed air heat ejector includes a housing defining an inner passage extending in an axial direction from an inlet of the housing to an outlet of the housing, wherein the inlet is configured to channel ambient air into the housing, and wherein the outlet is configured to channel mixed heated and ambient air out of the housing. A dispenser is mounted in the housing between the inlet and the outlet. The dispenser includes an inner chamber configured to receive heated air from a bleed line. The dispenser includes a plurality of apertures therein for issuing heated air from the inner chamber into the inner passage of the housing to form a flow of mixed ambient and bleed air. The apertures of the inner chamber can be angled primary jets, vortex generators can be included, and/or secondary jets can be included to promote mixing of bleed and ambient air.Type: GrantFiled: July 10, 2017Date of Patent: April 21, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jose A. daSilva, Joseph Lawrence Simonetti, Donald William Lamb, Jr., Nhan R. Tran
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Patent number: 10612421Abstract: A gas turbine exhaust assembly includes an exhaust flow path configured to receive an exhaust flow from a gas turbine engine, the exhaust flow path defined by an inner hub and a radially outer wall. The gas turbine exhaust assembly also includes a plurality of vanes circumferentially spaced from each other and operatively coupled to the radially outer wall of the exhaust flow path, each of the plurality of vanes extending only partially toward the inner hub and terminating at an inner end of the vanes, the inner end defining an open portion.Type: GrantFiled: February 25, 2016Date of Patent: April 7, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Joseph Lawrence Simonetti, Donald William Lamb, Jr., Shyam Neerarambam
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Patent number: 10569892Abstract: Embodiments are directed to selecting, by a computing device comprising a processor, the size of at least one prime mover associated with an aircraft to satisfy a baseline power requirement for operation of the aircraft during a steady state load condition, selecting at least one power source configuration to supplement power provided by the at least one prime mover during a transient load condition associated with the operation of the aircraft, and selecting, by the computing device, a parameter of the at least one power source configuration to provide a total power in an amount that is greater than a threshold during the transient condition.Type: GrantFiled: May 5, 2014Date of Patent: February 25, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Joseph Lawrence Simonetti, Mark Denton Bystry, Michael Joseph DeVita, Matthew J. Tarascio, Michael Peter Strauss, Hayden M. Reeve, Niranjan Desai, Brian St. Rock, Charles E. Lents, Lawrence E. Zeidner, Alfred Russell Smiley
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Publication number: 20200024983Abstract: An exhaust system for an engine includes an exhaust nozzle located adjacent an outlet end of the engine to receive a primary flow of exhaust gasses expelled from the engine, an inlet opening formed between the exhaust nozzle and the outlet end of the engine through which a secondary flow is provided to the exhaust nozzle, and a vortex generator arranged within the exhaust system at a position where both the primary flow and the secondary flow are present. The vortex generator interrupts at least one of the primary flow and the secondary flow.Type: ApplicationFiled: July 19, 2018Publication date: January 23, 2020Inventors: Joseph Lawrence Simonetti, Donald W. Lamb, JR., Patrick Ormande Bowles
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Patent number: 10519867Abstract: An integrated inlet particle separator (IPS) blower/engine starter including a housing having an inlet and an outlet. A turbine member is rotatably supported in the housing. A geared member operatively connected to the turbine member extends outward from the housing. The integrated IPS blower/engine starter is operable in a first configuration receiving a first fluid flow to rotate the geared member and in a second configuration generating a fluid flow through powered rotation of the geared member.Type: GrantFiled: September 27, 2017Date of Patent: December 31, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Joseph Lawrence Simonetti, Andrew G. Keith
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Patent number: 10309304Abstract: One aspect is an electrical augmentation system for a gas turbine engine. The electrical augmentation system includes an electric motor operably coupled to a shaft of the gas turbine engine, and an energy storage device operable to provide a temporary increased current source to the electric motor. The electrical augmentation system includes a control system having a torque demand anticipation circuit operable to determine an anticipated torque increase condition for the gas turbine engine. Based on the anticipated torque increase condition, the torque demand anticipation circuit commands a temporary torque increase by the electric motor using the energy storage device.Type: GrantFiled: March 4, 2014Date of Patent: June 4, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Frederick L. Bourne, Mark Denton Bystry, Jr., Joseph Lawrence Simonetti
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Publication number: 20190093558Abstract: An integrated inlet particle separator (IPS) blower/engine starter including a housing having an inlet and an outlet. A turbine member is rotatably supported in the housing. A geared member operatively connected to the turbine member extends outward from the housing. The integrated IPS blower/engine starter is operable in a first configuration receiving a first fluid flow to rotate the geared member and in a second configuration generating a fluid flow through powered rotation of the geared member.Type: ApplicationFiled: September 27, 2017Publication date: March 28, 2019Inventors: Joseph Lawrence Simonetti, Andrew G. Keith
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Patent number: 10131442Abstract: The disclosure herein relates to power leveling mechanisms comprising a high frequency controller. The power leveling mechanism receives a power demand signal indicating a power requirement of a vehicle and determines a high frequency component of the power demand signal. The power leveling mechanism also provides a signal to a primary propulsion system and provides, via the high frequency controller, a high bandwidth signal based on the high frequency component to an auxiliary propulsion system.Type: GrantFiled: October 28, 2016Date of Patent: November 20, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Peter James Waltner, Joseph Lawrence Simonetti, Nicholas D. Lappos, Jonathan Hartman
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Publication number: 20180201386Abstract: A control system for an in-flight engine restart system of a rotorcraft includes an engine control unit that controls and detects status of an engine. The control system also includes a flight control computer that communicates with the engine control unit, an engine operation control system, and a pilot interface including pilot controls. The engine operation control system includes a processor that initiates a health check of the in-flight engine restart system to determine an in-flight engine restart system status. The engine operation control system processes engine mode of operation commands to establish an engine mode of operation, and delivers commands to aspects of the in-flight engine restart system including the engine control unit based on processing of the engine mode of operation commands. The engine operation control system reports the in-flight engine restart system status and results of the engine mode of operation commands to the flight control computer.Type: ApplicationFiled: July 20, 2016Publication date: July 19, 2018Inventors: Michael Peter Strauss, Michael Joseph DeVita, Mark Denton Bystry, Jr., Joseph Lawrence Simonetti, Carl A. Palmer
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Publication number: 20180080380Abstract: A method of operating a multi-engine, rotary wing aircraft in a single engine, in-flight mode, the method includes stopping a first engine while operating a second engine; closing variable Stop engine inlet guide vanes on the first engine; and turning a gas generator of the first engine at a reference rotational speed.Type: ApplicationFiled: March 22, 2016Publication date: March 22, 2018Inventor: Joseph Lawrence Simonetti
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Publication number: 20180058264Abstract: A gas turbine exhaust assembly includes an exhaust flow path configured to receive an exhaust flow from a gas turbine engine, the exhaust flow path defined by an inner hub and a radially outer wall. The gas turbine exhaust assembly also includes a plurality of vanes circumferentially spaced from each other and operatively coupled to the radially outer wall of the exhaust flow path, each of the plurality of vanes extending only partially toward the inner hub and terminating at an inner end of the vanes, the inner end defining an open portion.Type: ApplicationFiled: February 25, 2016Publication date: March 1, 2018Inventors: Joseph Lawrence Simonetti, Donald William Lamb, Jr., Shyam Neerarambam
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Publication number: 20180016017Abstract: A bleed air heat ejector includes a housing defining an inner passage extending in an axial direction from an inlet of the housing to an outlet of the housing, wherein the inlet is configured to channel ambient air into the housing, and wherein the outlet is configured to channel mixed heated and ambient air out of the housing. A dispenser is mounted in the housing between the inlet and the outlet. The dispenser includes an inner chamber configured to receive heated air from a bleed line. The dispenser includes a plurality of apertures therein for issuing heated air from the inner chamber into the inner passage of the housing to form a flow of mixed ambient and bleed air. The apertures of the inner chamber can be angled primary jets, vortex generators can be included, and/or secondary jets can be included to promote mixing of bleed and ambient air.Type: ApplicationFiled: July 10, 2017Publication date: January 18, 2018Inventors: Jose A. daSilva, Joseph Lawrence Simonetti, Donald William Lamb, JR., Nhan R. Tran
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Publication number: 20170297732Abstract: The disclosure herein relates to power leveling mechanisms comprising a high frequency controller. The power leveling mechanism receives a power demand signal indicating a power requirement of a vehicle and determines a high frequency component of the power demand signal. The power leveling mechanism also provides a signal to a primary propulsion system and provides, via the high frequency controller, a high bandwidth signal based on the high frequency component to an auxiliary propulsion system.Type: ApplicationFiled: October 28, 2016Publication date: October 19, 2017Inventors: Peter James Waltner, Joseph Lawrence Simonetti, Nicholas D. Lappos, Jonathan Hartman
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Publication number: 20170089261Abstract: One aspect is an electrical augmentation system for a gas turbine engine. The electrical augmentation system includes an electric motor operably coupled to a shaft of the gas turbine engine, and an energy storage device operable to provide a temporary increased current source to the electric motor. The electrical augmentation system includes a control system having a torque demand anticipation circuit operable to determine an anticipated torque increase condition for the gas turbine engine. Based on the anticipated torque increase condition, the torque demand anticipation circuit commands a temporary torque increase by the electric motor using the energy storage device.Type: ApplicationFiled: March 4, 2014Publication date: March 30, 2017Inventors: Frederick L. Bourne, Mark Denton Bystry, Jr., Joseph Lawrence Simonetti