Patents by Inventor David Tibbs
David Tibbs 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: 11655979Abstract: A fuel injector for a gas turbine engine of an aircraft having a fuel nozzle including a fuel swirler and/or an outer air swirler. The fuel swirler may include a manifold for receiving fuel from a fuel conduit, and a plurality of fuel passages to direct fuel from the manifold to discharge orifices that direct fuel with swirling flow. The fuel swirler may be configured to provide uniform spray while minimizing recirculation zones; reduce residence time as fuel enters the manifold; minimize flow disruptions, boundary layer growth, and/or pressure drop as fuel flows through the fuel passages; reduces coking internally of the nozzle; reduces thermal stresses; and is simple and low-cost to manufacture. The outer air swirler may include first and second outer air swirler portions with respective vanes and air passages that provide swirling air flow.Type: GrantFiled: June 15, 2022Date of Patent: May 23, 2023Assignee: Parker-Hannifin CorporationInventors: Luther Wirtz, Jeffrey Lehtinen, Adel Mansour, David Tibbs, Robert Pelletier, Jon Stockill
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Publication number: 20230071579Abstract: A fuel injector for a gas turbine engine of an aircraft having a fuel nozzle including a fuel swirler and/or an outer air swirler. The fuel swirler may include a manifold for receiving fuel from a fuel conduit, and a plurality of fuel passages to direct fuel from the manifold to discharge orifices that direct fuel with swirling flow. The fuel swirler may be configured to provide uniform spray while minimizing recirculation zones; reduce residence time as fuel enters the manifold; minimize flow disruptions, boundary layer growth, and/or pressure drop as fuel flows through the fuel passages; reduces coking internally of the nozzle; reduces thermal stresses; and is simple and low-cost to manufacture. The outer air swirler may include first and second outer air swirler portions with respective vanes and air passages that provide swirling air flow.Type: ApplicationFiled: June 15, 2022Publication date: March 9, 2023Inventors: Luther Wirtz, Jeffrey Lehtinen, Adel Mansour, David Tibbs, Robert Pelletier, Jon Stockill
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Patent number: 11391463Abstract: A fuel injector for a gas turbine engine of an aircraft having a fuel nozzle including a fuel swirler and/or an outer air swirler. The fuel swirler may include a manifold for receiving fuel from a fuel conduit, and a plurality of fuel passages to direct fuel from the manifold to discharge orifices that direct fuel with swirling flow. The fuel swirler may be configured to provide uniform spray while minimizing recirculation zones; reduce residence time as fuel enters the manifold; minimize flow disruptions, boundary layer growth, and/or pressure drop as fuel flows through the fuel passages; reduces coking internally of the nozzle; reduces thermal stresses; and is simple and low-cost to manufacture. The outer air swirler may include first and second outer air swirler portions with respective vanes and air passages that provide swirling air flow.Type: GrantFiled: January 12, 2021Date of Patent: July 19, 2022Assignee: Parker-Hannifin CorporationInventors: Luther Wirtz, Jeffrey Lehtinen, Adel Mansour, David Tibbs, Robert Pelletier, Jon Stockill
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Publication number: 20210131665Abstract: A fuel injector for a gas turbine engine of an aircraft having a fuel nozzle including a fuel swirler and/or an outer air swirler. The fuel swirler may include a manifold for receiving fuel from a fuel conduit, and a plurality of fuel passages to direct fuel from the manifold to discharge orifices that direct fuel with swirling flow. The fuel swirler may be configured to provide uniform spray while minimizing recirculation zones; reduce residence time as fuel enters the manifold; minimize flow disruptions, boundary layer growth, and/or pressure drop as fuel flows through the fuel passages; reduces coking internally of the nozzle; reduces thermal stresses; and is simple and low-cost to manufacture. The outer air swirler may include first and second outer air swirler portions with respective vanes and air passages that provide swirling air flow.Type: ApplicationFiled: January 12, 2021Publication date: May 6, 2021Inventors: Luther Wirtz, Jeffrey Lehtinen, Adel Mansour, David Tibbs, Robert Pelletier, Jon Stockill
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Patent number: 10955138Abstract: A fuel injector for a gas turbine engine of an aircraft having a fuel nozzle including a fuel swirler and/or an outer air swirler. The fuel swirler may include a manifold for receiving fuel from a fuel conduit, and a plurality of fuel passages to direct fuel from the manifold to discharge orifices that direct fuel with swirling flow. The fuel swirler may be configured to provide uniform spray while minimizing recirculation zones; reduce residence time as fuel enters the manifold; minimize flow disruptions, boundary layer growth, and/or pressure drop as fuel flows through the fuel passages; reduces coking internally of the nozzle; reduces thermal stresses; and is simple and low-cost to manufacture.Type: GrantFiled: April 23, 2018Date of Patent: March 23, 2021Assignee: Parker-Hannifin CorporationInventors: Luther Wirtz, Jeffrey Lehtinen, Adel Mansour, David Tibbs, Robert Pelletier, Jon Stockill
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Patent number: 10920984Abstract: A fuel injector for a gas turbine engine of an aircraft having a fuel nozzle including a fuel swirler and/or an outer air swirler. The fuel swirler may include a manifold for receiving fuel from a fuel conduit, and a plurality of fuel passages to direct fuel from the manifold to discharge orifices that direct fuel with swirling flow. The fuel swirler may be configured to provide uniform spray while minimizing recirculation zones; reduce residence time as fuel enters the manifold; minimize flow disruptions, boundary layer growth, and/or pressure drop as fuel flows through the fuel passages; reduces coking internally of the nozzle; reduces thermal stresses; and is simple and low-cost to manufacture.Type: GrantFiled: April 23, 2018Date of Patent: February 16, 2021Assignee: Parker-Hannifin CorporationInventors: Luther Wirtz, Jeffrey Lehtinen, Adel Mansour, David Tibbs, Robert Pelletier, Jon Stockill
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Publication number: 20180304281Abstract: A fuel injector for a gas turbine engine of an aircraft having a fuel nozzle including a fuel swirler and/or an outer air swirler. The fuel swirler may include a manifold for receiving fuel from a fuel conduit, and a plurality of fuel passages to direct fuel from the manifold to discharge orifices that direct fuel with swirling flow. The fuel swirler may be configured to provide uniform spray while minimizing recirculation zones; reduce residence time as fuel enters the manifold; minimize flow disruptions, boundary layer growth, and/or pressure drop as fuel flows through the fuel passages; reduces coking internally of the nozzle; reduces thermal stresses; and is simple and low-cost to manufacture.Type: ApplicationFiled: April 23, 2018Publication date: October 25, 2018Inventors: Luther Wirtz, Jeffrey Lehtinen, Adel Mansour, David Tibbs, Robert Pelletier, Jon Stockill
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Publication number: 20180058404Abstract: A gas turbine fuel injector assembly including one or more dampers for damping vibration of one or more fuel conduits in the assembly. The dampers may at least partially surround the fuel conduits, and each damper has an intermediate portion that is bowed relative to axial end portions to form a pocket, which enables the damper to be free to flex radially for damping vibration experienced by the fuel conduit during operation. The damper may be a wire mesh damper formed with interwoven wires that are configured to move relative to each other in response to vibrational movement of the fuel conduit. The wire mesh damper also may enable fluids, such as gases or fuel, to flow through gaps in the wire mesh. The damper may support and damp individual fuel conduits, thereby enabling the fuel conduits to thermally expand independently of each other in the assembly.Type: ApplicationFiled: August 23, 2017Publication date: March 1, 2018Inventor: David Tibbs