Patents by Inventor Arthur M. Salve, JR.
Arthur M. Salve, JR. 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: 20240018901Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.Type: ApplicationFiled: August 2, 2023Publication date: January 18, 2024Applicant: RTX CORPORATIONInventors: Daniel Bernard Kupratis, Paul R. Hanrahan, Arthur M. Salve, JR.
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Patent number: 11753990Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.Type: GrantFiled: July 14, 2022Date of Patent: September 12, 2023Assignee: RTX CorporationInventors: Daniel Bernard Kupratis, Paul R. Hanrahan, Arthur M. Salve, Jr.
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Publication number: 20220349341Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.Type: ApplicationFiled: July 14, 2022Publication date: November 3, 2022Applicant: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Daniel Bernard Kupratis, Paul R. Hanrahan, Arthur M. Salve, JR.
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Patent number: 11448125Abstract: A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a high pressure turbine having a first stage and a second stage, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; a high pressure compressor connected to a high pressure compressor spool; and a differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear connected to the high pressure compressor spool.Type: GrantFiled: August 21, 2020Date of Patent: September 20, 2022Assignee: Raytheon Technologies CorporationInventors: Daniel Bernard Kupratis, Mark Tu, Paul R Hanrahan, Arthur M. Salve, Jr.
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Patent number: 11421590Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.Type: GrantFiled: October 18, 2019Date of Patent: August 23, 2022Assignee: Raytheon Technologies CorporationInventors: Daniel Bernard Kupratis, Paul R. Hanrahan, Arthur M. Salve, Jr.
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Patent number: 11193425Abstract: A turbine engine includes a core engine including a first spool and a second spool rotatable about a main engine longitudinal axis, a boost spool powered by a secondary drive system, and an accessory gearbox coupled to the core engine and the boost spool. A differential gear system is coupled between the core engine, the boost spool and the accessory gearbox for distributing power between the boost spool, the core engine and the accessory gearbox.Type: GrantFiled: June 19, 2019Date of Patent: December 7, 2021Assignee: Raytheon Technologies CorporationInventors: Paul R. Hanrahan, Arthur M. Salve, Jr., Daniel Bernard Kupratis
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Publication number: 20210054788Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.Type: ApplicationFiled: October 18, 2019Publication date: February 25, 2021Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Daniel Bernard Kupratis, Paul R. Hanrahan, Arthur M. Salve, JR.
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Publication number: 20210054809Abstract: A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a high pressure turbine having a first stage and a second stage, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; a high pressure compressor connected to a high pressure compressor spool; and a differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear connected to the high pressure compressor spool.Type: ApplicationFiled: August 21, 2020Publication date: February 25, 2021Applicant: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Daniel Bernard Kupratis, Mark Tu, Paul R. Hanrahan, Arthur M. Salve, JR.
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Publication number: 20210047970Abstract: Hybrid electric propulsion systems are described. The systems include a gas turbine engine having low and high speed spools, each spool having a respective compressor and turbine. A mechanical power transmission is configured to at least one of extract power from and supply power to at least one of the low speed spool and the high speed spool, an electric machine is configured to augment rotational power of at least one of the spools, and a controller is operable to determine a rotational speed of the low speed spool, determine a rotational speed of the high speed spool, determine if a predetermined operational zone of operation based on the determined rotational speeds is present, and when a predetermined operational zone is determined, control a power augmentation of at least one spool to limit dwell operation of the gas turbine engine within the predetermined operational zone.Type: ApplicationFiled: August 12, 2020Publication date: February 18, 2021Inventors: Gary Collopy, Arthur M. Salve, JR., Michael Winter
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Publication number: 20200400078Abstract: A turbine engine includes a core engine including a first spool and a second spool rotatable about a main engine longitudinal axis, a boost spool powered by a secondary drive system, and an accessory gearbox coupled to the core engine and the boost spool. A differential gear system is coupled between the core engine, the boost spool and the accessory gearbox for distributing power between the boost spool, the core engine and the accessory gearbox.Type: ApplicationFiled: June 19, 2019Publication date: December 24, 2020Inventors: Paul R. Hanrahan, Arthur M. Salve, JR., Daniel Bernard Kupratis
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Patent number: 10760423Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.Type: GrantFiled: April 6, 2018Date of Patent: September 1, 2020Assignee: Raytheon Technologies CorporationInventors: Gabriel L. Suciu, Stephen P. Muron, Ioannis Alvanos, Christopher M. Dye, Brian D. Merry, Arthur M. Salve, Jr., James W. Norris
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Publication number: 20180223668Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.Type: ApplicationFiled: April 6, 2018Publication date: August 9, 2018Inventors: Gabriel L. Suciu, Stephen P. Muron, Ioannis Alvanos, Christopher M. Dye, Brian D. Merry, Arthur M. Salve, JR., James W. Norris