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公开(公告)号：US10955138B2
公开(公告)日：2021-03-23
申请号：US15959362
申请日：2018-04-23
发明人： Luther Wirtz , Jeffrey Lehtinen , Adel Mansour , David Tibbs , Robert Pelletier , Jon Stockill
摘要： 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.
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公开(公告)号：US10920984B2
公开(公告)日：2021-02-16
申请号：US15959362
申请日：2018-04-23
发明人： Luther Wirtz , Jeffrey Lehtinen , Adel Mansour , David Tibbs , Robert Pelletier , Jon Stockill
摘要： 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.
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公开(公告)号：US11655979B2
公开(公告)日：2023-05-23
申请号：US17841210
申请日：2022-06-15
发明人： Luther Wirtz , Jeffrey Lehtinen , Adel Mansour , David Tibbs , Robert Pelletier , Jon Stockill
CPC分类号： F23R3/12 , F23R3/14 , F23R3/28 , F23R2900/00005
摘要： 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. The outer air swirler may be configured to improve atomization and spray uniformity with a wide spray angle; and minimize flow disruptions for enhancing flow performance.
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公开(公告)号：US20230071579A1
公开(公告)日：2023-03-09
申请号：US17841210
申请日：2022-06-15
发明人： Luther Wirtz , Jeffrey Lehtinen , Adel Mansour , David Tibbs , Robert Pelletier , Jon Stockill
摘要： 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. The outer air swirler may be configured to improve atomization and spray uniformity with a wide spray angle; and minimize flow disruptions for enhancing flow performance.
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公开(公告)号：US20210131665A1
公开(公告)日：2021-05-06
申请号：US17147078
申请日：2021-01-12
发明人： Luther Wirtz , Jeffrey Lehtinen , Adel Mansour , David Tibbs , Robert Pelletier , Jon Stockill
摘要： 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. The outer air swirler may be configured to improve atomization and spray uniformity with a wide spray angle; and minimize flow disruptions for enhancing flow performance.
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公开(公告)号：US20180304281A1
公开(公告)日：2018-10-25
申请号：US15959362
申请日：2018-04-23
发明人： Luther Wirtz , Jeffrey Lehtinen , Adel Mansour , David Tibbs , Robert Pelletier , Jon Stockill
CPC分类号： B05B1/3415 , F23D11/107 , F23R3/14 , F23R3/28
摘要： 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.
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