Patents by Inventor Nathan L. Messersmith
Nathan L. Messersmith 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: 20240035392Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.Type: ApplicationFiled: October 12, 2023Publication date: February 1, 2024Applicant: RTX CorporationInventors: Dmitriy B. Sidelkovskiy, Pitchaiah Vijay Chakka, Michael Winter, Daniel Bernard Kupratis, Nathan L. Messersmith
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Patent number: 11846196Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.Type: GrantFiled: February 21, 2020Date of Patent: December 19, 2023Assignee: RTX CorporationInventors: Dmitriy B. Sidelkovskiy, Pitchaiah Vijay Chakka, Michael Winter, Daniel Bernard Kupratis, Nathan L. Messersmith
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Patent number: 11585294Abstract: A nacelle assembly of a gas turbine engine includes an annular structure defining a central axis, and having a radially inward surface and a radially outward surface, the radially inward surface at least partially defining a bypass duct. An aft portion of the radially inward surface at least partially defines an axially extending convergent-divergent exit nozzle. A secondary nozzle flap is radially spaced from the aft portion of the radially inward surface. The secondary nozzle flap and the aft portion of the radially inward surface define a secondary bypass duct therebetween. The secondary nozzle flap is operably connected to the annular structure such that the secondary nozzle flap is selectably movable relative to the aft portion of the radially inward surface, thereby changing a cross-sectional area of a secondary bypass duct exit.Type: GrantFiled: February 21, 2020Date of Patent: February 21, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Dmitriy B. Sidelkovskiy, Steven H. Zysman, Nathan L. Messersmith
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Publication number: 20210262415Abstract: A nacelle assembly of a gas turbine engine includes an annular structure defining a central axis, and having a radially inward surface and a radially outward surface, the radially inward surface at least partially defining a bypass duct. An aft portion of the radially inward surface at least partially defines an axially extending convergent-divergent exit nozzle. A secondary nozzle flap is radially spaced from the aft portion of the radially inward surface. The secondary nozzle flap and the aft portion of the radially inward surface define a secondary bypass duct therebetween. The secondary nozzle flap is operably connected to the annular structure such that the secondary nozzle flap is selectably movable relative to the aft portion of the radially inward surface, thereby changing a cross-sectional area of a secondary bypass duct exit.Type: ApplicationFiled: February 21, 2020Publication date: August 26, 2021Applicant: United Technologies CorporationInventors: Dmitriy B. Sidelkovskiy, Steven H. Zysman, Nathan L. Messersmith
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Publication number: 20210262359Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.Type: ApplicationFiled: February 21, 2020Publication date: August 26, 2021Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Dmitriy B. Sidelkovskiy, Pitchaiah Vijay Chakka, Michael Winter, Daniel Bernard Kupratis, Nathan L. Messersmith
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Patent number: 10975713Abstract: A hydrostatic seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a seal housing. The seal further includes a shoe operatively coupled to the base and extending axially from a forward end to an aft end. The seal yet further includes a plurality of teeth extending radially from a sealing surface of the shoe, one of the teeth being a longest tooth that extends furthest radially from the sealing surface, the axial distance from the forward end of the shoe to the longest tooth being greater than a radial distance from a radial tooth tip to the sealing surface.Type: GrantFiled: January 4, 2019Date of Patent: April 13, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Eric A. Grover, Brian F. Hilbert, Nathan L. Messersmith, Christopher W. Robak
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Publication number: 20200217216Abstract: A hydrostatic seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a seal housing. The seal further includes a shoe operatively coupled to the base and extending axially from a forward end to an aft end. The seal yet further includes a plurality of teeth extending radially from a sealing surface of the shoe, one of the teeth being a longest tooth that extends furthest radially from the sealing surface, the axial distance from the forward end of the shoe to the longest tooth being greater than a radial distance from a radial tooth tip to the sealing surface.Type: ApplicationFiled: January 4, 2019Publication date: July 9, 2020Inventors: Eric A. Grover, Brian F. Hilbert, Nathan L. Messersmith, Christopher W. Robak
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Publication number: 20190316544Abstract: A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors. Each of the multiple of doors is operable to control a passage entrance into at least one of a multiple of circumferentially arrayed vanes with a respective strut flow passage which essentially alters its bypass ratio during flight to match requirements.Type: ApplicationFiled: June 3, 2019Publication date: October 17, 2019Inventors: Jeffery A. Lovett, Nathan L. Messersmith, Sean P. Zamora
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Patent number: 10371090Abstract: A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors. Each of the multiple of doors is operable to control a passage entrance into at least one of a multiple of circumferentially arrayed vanes with a respective strut flow passage which essentially alters its bypass ratio during flight to match requirements.Type: GrantFiled: January 13, 2015Date of Patent: August 6, 2019Assignee: United Technologies CorporationInventors: Jeffery A. Lovett, Nathan L. Messersmith, Sean P. Zamora
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Publication number: 20150198116Abstract: A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors. Each of the multiple of doors is operable to control a passage entrance into at least one of a multiple of circumferentially arrayed vanes with a respective strut flow passage which essentially alters its bypass ratio during flight to match requirements.Type: ApplicationFiled: January 13, 2015Publication date: July 16, 2015Inventors: Jeffery A. Lovett, Nathan L. Messersmith, Sean P. Zamora
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Patent number: 7775460Abstract: A fluid flow system for use with a gas turbine engine includes an exhaust nozzle, a primary air supply valve, a distribution manifold connected to the primary fluid supply valve and in fluid communication therewith, and a plurality of fluid injector assemblies positioned at the exhaust nozzle and connected in fluid communication with the distribution manifold. Each fluid injector assembly includes a first tube, a secondary air valve positioned at least partially within the first tube and in fluid communication with the distribution manifold, a fuel valve positioned at least partially within the first tube and located downstream of the air valve, an igniter extending into the first tube downstream of the fuel valve, and an outlet in fluid communication with the first tube and connected in fluid communication with the exhaust nozzle. The outlet has a different geometry than the first tube.Type: GrantFiled: October 24, 2006Date of Patent: August 17, 2010Assignee: United Technologies CorporationInventors: Gerald R. Berg, Nathan L. Messersmith, Gary L. Lidstone, John Hinkey
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Patent number: 7481038Abstract: An exhaust nozzle assembly provides fluidic thrust vectoring of the primary stream to enhance aircraft maneuverability. The exhaust nozzle assembly includes a cooling air passage that supplies cooling air to a plurality of cooling holes that generate an insulating layer of air. A vector slot injects cooling airflow into the exhaust passage normal to the primary stream. A cover plate partially blocks the vector slot to direct cooling airflow into the exhaust passage that in turn directs portions of the primary stream.Type: GrantFiled: October 28, 2004Date of Patent: January 27, 2009Assignee: United Technologies CorporationInventors: Jack T. Blozy, Charles M. Willard, Nathan L. Messersmith, Miquel A. Velazquez
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Publication number: 20080092543Abstract: A fluid flow system for use with a gas turbine engine includes an exhaust nozzle, a primary air supply valve, a distribution manifold connected to the primary fluid supply valve and in fluid communication therewith, and a plurality of fluid injector assemblies positioned at the exhaust nozzle and connected in fluid communication with the distribution manifold. Each fluid injector assembly includes a first tube, a secondary air valve positioned at least partially within the first tube and in fluid communication with the distribution manifold, a fuel valve positioned at least partially within the first tube and located downstream of the air valve, an igniter extending into the first tube downstream of the fuel valve, and an outlet in fluid communication with the first tube and connected in fluid communication with the exhaust nozzle. The outlet has a different geometry than the first tube.Type: ApplicationFiled: October 24, 2006Publication date: April 24, 2008Applicant: United Technologies CorporationInventors: Gerald R. Berg, Nathan L. Messersmith, Gary L. Lidstone, John Hinkey