Patents by Inventor Patrick Gomez
Patrick Gomez 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: 20240159190Abstract: An ignition and combustion assist system and method comprising a plasma igniter and electronic driver unit for use with gas turbine engines operating under low air densities, reduced voltage conditions and overall pressure ratios of 3:1 to 7:1. The plasma igniter has an inner chamber housing a centrally positioned and electrically isolated electrode attached to an electrical lead, driver unit, and AC or DC power supply. The electrode features a corner positioned near an outlet end of the igniter, where a plasma arc ignites a fuel-air mixture creating a flame extending into a primary burn region of a combustor of the gas turbine. The driver unit is in two embodiments and configured with low-cost microsecond voltage wave time periods or energy-efficient nano-second pulses. The method uses the plasma igniter and the electronic driver units described herein separately with other components or together.Type: ApplicationFiled: March 18, 2023Publication date: May 16, 2024Inventors: Mark Harris, Patrick Bailey, David Monk, Felipe Gomez del Campo, Drew Weibel, Ilya Gulko, Munetake Nishihara, Ford McClure
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Patent number: 11563642Abstract: A high availability aircraft network architecture incorporating smart points of presence (SPoP) is disclosed. In embodiments, the network architecture divides the aircraft into districts, or physical subdivisions. Each district includes one or more mission systems (MS) smart network access point (SNAP) devices for connecting MS components and devices located within its district to the MS network. Similarly, each district includes one or more air vehicle systems (AVS) SNAP devices for connecting AVS components and devices within the district to the AVS network. The AVS network may remain in a star or hub-and-spoke topology, while the MS network may be configured in a ring or mesh topology. Selected MS and AVS SNAP devices may be connected to each other via guarded network bridges to securely interconnect the MS and AVS networks.Type: GrantFiled: October 9, 2020Date of Patent: January 24, 2023Assignee: Rockwell Collins, Inc.Inventors: Patrick Gomez, Abdul A. Khan, Brian S. Rach, Charles Adams, Mitchell A. Riley, Max G. Taylor
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Patent number: 11477088Abstract: A smart network access point (SNAP) device is disclosed. In embodiments, the SNAP device includes trunk ports for accepting a network trunk cable (e.g., fiber optic trunk) and thereby connecting the SNAP device to an aircraft-based network of SNAP devices. The SNAP device includes switch ports for incorporating physical connections to mission systems (MS) or air vehicle systems (AVS) components and devices, providing a local smart point of presence (SPoP) throughout a physical subdivision (e.g., network district) of an aircraft. The SNAP device is configured for monitoring data exchanges between local MS/AVS components and the aircraft network. The SNAP device includes a cybersecurity module for connecting to local security components (e.g., data guards and multiple levels of security (MLS) encryption/decryption) or for providing built-in data guard and encryption/decryption services. The SNAP device includes power control components for managing power distribution to the connected local network components.Type: GrantFiled: October 9, 2020Date of Patent: October 18, 2022Assignee: Rockwell Collins, Inc.Inventors: Patrick Gomez, Abdul A. Khan, Brian S. Rach, Charles Adams, Mitchell A. Riley, Max G. Taylor
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Publication number: 20210351987Abstract: A high availability aircraft network architecture incorporating smart points of presence (SPoP) is disclosed. In embodiments, the network architecture divides the aircraft into districts, or physical subdivisions. Each district includes one or more mission systems (MS) smart network access point (SNAP) devices for connecting MS components and devices located within its district to the MS network. Similarly, each district includes one or more air vehicle systems (AVS) SNAP devices for connecting AVS components and devices within the district to the AVS network. The AVS network may remain in a star or hub-and-spoke topology, while the MS network may be configured in a ring or mesh topology. Selected MS and AVS SNAP devices may be connected to each other via guarded network bridges to securely interconnect the MS and AVS networks.Type: ApplicationFiled: October 9, 2020Publication date: November 11, 2021Applicant: Rockwell Collins, Inc.Inventors: Patrick Gomez, Abdul A. Khan, Brian S. Rach, Charles Adams, Mitchell A. Riley, Max G. Taylor
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Publication number: 20210351988Abstract: A smart network access point (SNAP) device is disclosed. In embodiments, the SNAP device includes trunk ports for accepting a network trunk cable (e.g., fiber optic trunk) and thereby connecting the SNAP device to an aircraft-based network of SNAP devices. The SNAP device includes switch ports for incorporating physical connections to mission systems (MS) or air vehicle systems (AVS) components and devices, providing a local smart point of presence (SPoP) throughout a physical subdivision (e.g., network district) of an aircraft. The SNAP device is configured for monitoring data exchanges between local MS/AVS components and the aircraft network. The SNAP device includes a cybersecurity module for connecting to local security components (e.g., data guards and multiple levels of security (MLS) encryption/decryption) or for providing built-in data guard and encryption/decryption services. The SNAP device includes power control components for managing power distribution to the connected local network components.Type: ApplicationFiled: October 9, 2020Publication date: November 11, 2021Applicant: Rockwell Collins, Inc.Inventors: Patrick Gomez, Abdul A. Khan, Brian S. Rach, Charles Adams, Mitchell A. Riley, Max G. Taylor
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Patent number: 10926444Abstract: An assembly for manufacturing a wax moulding of a turbine engine blade has a wax injection mould in which a core is able to be mounted in a predetermined moulding position, the core including a main element and at least a first secondary element each including at least one functional part and a non-functional part, wherein the non-functional part of the first secondary element includes a rod portion extending in a longitudinal direction of the blade and housed in a first slot of the non-functional part of the main member, the mould including a first internal boss clamping said rod portion at the bottom of the first slot.Type: GrantFiled: April 26, 2018Date of Patent: February 23, 2021Assignees: Safran, Safran Aircraft EnginesInventors: Jean-Claude Marcel Auguste Hanny, Pascal Francis Patrick Gomez, Daniel Quach, Adrien Bernard Vincent Rollinger, Joseph Toussaint Tami Lizuzu, Matthieu Jean Luc Vollebregt
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Patent number: 10906089Abstract: The invention relates to the making, on a support plate (34), of an annular space (76) in a ceramic paste covering this plate, in order, by successive deposits and firing of layers of said ceramic paste, to create a base of a ceramic shell (40) for the moulding of parts, the base having said annular space (76). For this purpose, between two deposits of said ceramic paste, and on the plate, said deformable annular element (82) will be deformed in order to break the ceramic layer.Type: GrantFiled: December 19, 2019Date of Patent: February 2, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Hervé Bruno Marc Osmont, Pascal Francis Patrick Gomez
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Publication number: 20200198001Abstract: The invention relates to the making, on a support plate (34), of an annular space (76) in a ceramic paste covering this plate, in order, by successive deposits and firing of layers of said ceramic paste, to create a base of a ceramic shell (40) for the moulding of parts, the base having said annular space (76). For this purpose, between two deposits of said ceramic paste, and on the plate, said deformable annular element (82) will be deformed in order to break the ceramic layer.Type: ApplicationFiled: December 19, 2019Publication date: June 25, 2020Inventors: Hervé Bruno Marc OSMONT, Pascal Francis Patrick GOMEZ
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Patent number: 10682685Abstract: A method of making a multi-vane model for a nozzle guide out of sacrificial material, includes the steps of fabricating a single-vane model out of sacrificial material, assembling at least two sacrificial material single-vane models with each other, and positioning (104, 108) a holder element on at least one sacrificial material single-vane model so as to hold a predetermined spacing between an inner platform and an outer platform. An assembly of a sacrificial material single-vane model for a nozzle guide together with a holder element, and also an assembly of a sacrificial material multi-vane model for a nozzle guide together with a holder element.Type: GrantFiled: January 11, 2019Date of Patent: June 16, 2020Assignee: Safran Aircraft EnginesInventors: Joseph Toussaint Tami Lizuzu, Thierry Eric Cogneras, Pascal Francis Patrick Gomez, Hervé Bruno Marc Osmont, Anthony Dominique Désiré Scattolini
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Patent number: 10486226Abstract: A core used in the manufacture, by lost-wax casting, of a turbomachine blade, includes a main element and at least one first secondary element, each including a functional part and a non-functional part. The non-functional part of the main element and the non-functional part of the at least one first secondary element are assembled and shaped so as to cooperate with each other by sliding in a longitudinal direction extending between the base and the top of a blade and by rotating around the longitudinal direction.Type: GrantFiled: April 26, 2018Date of Patent: November 26, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Daniel Quach, Pascal Francis Patrick Gomez, Coralie Cinthia Guerard, Jean-Claude Marcel Auguste Hanny, Patrick Emilien Paul Emile Huchin, Joseph Toussaint Tami Lizuzu, Matthieu Jean Luc Vollebregt, Vincent Marc Herb, Laetitia Person
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Publication number: 20190217377Abstract: A method of making a multi-vane model for a nozzle guide out of sacrificial material, includes the steps of fabricating a single-vane model out of sacrificial material, assembling at least two sacrificial material single-vane models with each other, and positioning (104, 108) a holder element on at least one sacrificial material single-vane model so as to hold a predetermined spacing between an inner platform and an outer platform. An assembly of a sacrificial material single-vane model for a nozzle guide together with a holder element, and also an assembly of a sacrificial material multi-vane model for a nozzle guide together with a holder element.Type: ApplicationFiled: January 11, 2019Publication date: July 18, 2019Applicant: Safran Aircraft EnginesInventors: Joseph Toussaint TAMI LIZUZU, Thierry Eric COGNERAS, Pascal Francis Patrick GOMEZ, Hervé Bruno Marc OSMONT, Anthony Dominique Désiré SCATTOLINI
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Publication number: 20180311876Abstract: An assembly for manufacturing a wax moulding of a turbine engine blade has a wax injection mould in which a core is able to be mounted in a predetermined moulding position, the core including a main element and at least a first secondary element each including at least one functional part and a non-functional part, wherein the non-functional part of the first secondary element includes a rod portion extending in a longitudinal direction of the blade and housed in a first slot of the non-functional part of the main member, the mould including a first internal boss clamping said rod portion at the bottom of the first slot.Type: ApplicationFiled: April 26, 2018Publication date: November 1, 2018Applicants: Safran Aircraft Engines, SafranInventors: Jean-Claude Marcel Auguste Hanny, Pascal Francis Patrick Gomez, Daniel Quach, Adrien Bernard Vincent Rollinger, Joseph Toussaint Tami Lizuzu, Matthieu Jean Luc Vollebregt
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Publication number: 20180311722Abstract: A core used in the manufacture, by lost-wax casting, of a turbomachine blade, includes a main element and at least one first secondary element, each including a functional part and a non-functional part. The non-functional part of the main element and the non-functional part of the at least one first secondary element are assembled and shaped so as to cooperate with each other by sliding in a longitudinal direction extending between the base and the top of a blade and by rotating around the longitudinal direction.Type: ApplicationFiled: April 26, 2018Publication date: November 1, 2018Applicant: Safran Aircraft EnginesInventors: Daniel Quach, Pascal Francis Patrick Gomez, Coralie Cinthia Guerard, Jean-Claude Marcel Auguste Hanny, Patrick Emilien Paul Emile Huchin, Joseph Toussaint Tami Lizuzu, Matthieu Jean Luc Vollebregt, Vincent Marc Herb, Laetitia Person