Patents by Inventor Adel Mansour
Adel Mansour 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: 20050103019Abstract: An injector assembly includes a barrel-shaped housing and an injector, the injector including a feed ring formed of multiple, etched, T-shaped plates. A plurality of nozzles are arranged in an evenly-spaced array around the injector and direct fluid radially inward into the central annulus of the injector assembly. The injector includes an air inlet port with an internal feed passage fluidly connected to swirl chambers and exit orifices to provide individual sprays of fuel from the nozzles. Integral air swirlers impart a swirling component of motion to the fuel sprays. A venturi configuration is provided by the housing. The nozzles are provided along the venturi configuration, which maintains fluid separation from the walls of the housing downstream from the venturi.Type: ApplicationFiled: July 13, 2004Publication date: May 19, 2005Inventors: Adel Mansour, Andrew Odar, Erlendur Steinthorsson
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Patent number: 6258166Abstract: There is claimed a method for depositing fluid material from a linear nozzle in a substantially uniform manner across and along a surface. The method includes directing gaseous medium through said nozzle to provide a gaseous stream at the nozzle exit that entrains fluid material supplied to the nozzle, said gaseous stream being provided with a velocity profile across the nozzle width that compensates for the gaseous medium's tendency to assume an axisymmetric configuration after leaving the nozzle and before reaching the surface. There is also claimed a nozzle divided into respective side-by-side zones, or preferably chambers, through which a gaseous stream can be delivered in various velocity profiles across the width of said nozzle to compensate for the tendency of this gaseous medium to assume an axisymmetric configuration.Type: GrantFiled: August 23, 1999Date of Patent: July 10, 2001Assignee: Alcoa Inc.Inventors: David D. Leon, Robert L. Kozarek, Adel Mansour, Norman Chigier
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Patent number: 5968601Abstract: There is claimed a method for depositing fluid material from a linear nozzle in a substantially uniform manner across and along a surface. The method includes directing gaseous medium through said nozzle to provide a gaseous stream at the nozzle exit that entrains fluid material supplied to the nozzle, said gaseous stream being provided with a velocity profile across the nozzle width that compensates for the gaseous medium's tendency to assume an axisymmetric configuration after leaving the nozzle and before reaching the surface. There is also claimed a nozzle divided into respective side-by-side zones, or preferably chambers, through which a gaseous stream can be delivered in various velocity profiles across the width of said nozzle to compensate for the tendency of this gaseous medium to assume an axisymmetric configuration.Type: GrantFiled: August 20, 1997Date of Patent: October 19, 1999Assignee: Aluminum Company of AmericaInventors: David D. Leon, Robert L. Kozarek, Adel Mansour, Norman Chigier