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1.发明授权公开(公告)号：US10184665B2
公开(公告)日：2019-01-22
申请号：US14735732
申请日：2015-06-10
Applicant: General Electric Company
Abstract: A fuel nozzle is provided for a gas turbine engine, and can include a pilot fuel injector having an axially-elongated, inner pilot centerbody wall and an outer pilot centerbody wall, with the axially-elongated, inner pilot centerbody wall extending from an upstream end to an annular fuel passage defining the downstream end of the pilot fuel injector. The fuel passage intersects with the inner pilot centerbody wall at a pilot fuel metering orifice. The fuel nozzle also includes a pilot fuel film surface downstream from the annular fuel passage and an annular splitter surrounding the pilot fuel injector. The annular splitter comprises, in axial sequence: an upstream section, a splitter throat having a diameter that is larger than a downstream diameter defined by the pilot fuel film surface, and a downstream diverging surface having an average diverging angle of about 24° to about 40° in relation to a centerline axis.
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Patent Agency Ranking
公开(公告)号：US20160363321A1
公开(公告)日：2016-12-15
申请号：US14735694
申请日：2015-06-10
Applicant: General Electric Company
IPC: F23R3/34
CPC classification number: F23R3/343 , F23D11/104 , F23D11/105 , F23D11/14 , F23D2900/11101 , F23R3/14 , F23R3/32
Abstract: A pilot fuel injector is provided for a fuel nozzle of a gas turbine engine. The pilot fuel injector can include an axially-elongated, inner pilot centerbody wall extending from an upstream end to a downstream end, with the axially-elongated, inner pilot centerbody wall having a diverging-converging orientation with respect to a centerline axis to define a hollow tube having an upstream diameter, a throat, and a downstream diameter such that the throat has an inner diameter that is less than both of the upstream diameter and the downstream diameter. The pilot fuel injector also includes a center air circuit positioned at the upstream end, and an annular fuel passage defining the downstream end and intersecting with the centerbody wall at a pilot fuel metering orifice. A pilot fuel film surface is downstream from the annular fuel passage.
Abstract translation: 为燃气涡轮发动机的燃料喷嘴设置了先导燃料喷射器。 引燃燃料喷射器可以包括从上游端延伸到下游端的轴向细长的内导向中心体壁，其中轴向延伸的内导向中心体壁相对于中心线轴线具有发散会聚方向，以限定 中空管具有上游直径，喉部和下游直径，使得喉部具有小于上游直径和下游直径两者的内径。 驾驶员燃料喷射器还包括位于上游端的中心空气回路和限定下游端的环形燃料通道，并且在导向燃料计量孔口处与中心体壁相交。 导向燃料膜表面在环形燃料通道的下游。
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3.发明申请PREFILMING AIR BLAST (PAB) PILOT HAVING ANNULAR SPLITTER SURROUNDING A PILOT FUEL INJECTOR 审中-公开预制空气喷枪（PAB）具有环形分流器的引导器引导燃油喷射器公开(公告)号：US20160363320A1
公开(公告)日：2016-12-15
申请号：US14735732
申请日：2015-06-10
Applicant: General Electric Company
CPC classification number: F23R3/286 , F02C7/22 , F23D11/107 , F23D2900/11101
Abstract: A fuel nozzle is provided for a gas turbine engine, and can include a pilot fuel injector having an axially-elongated, inner pilot centerbody wall and an outer pilot centerbody wall, with the axially-elongated, inner pilot centerbody wall extending from an upstream end to an annular fuel passage defining the downstream end of the pilot fuel injector. The fuel passage intersects with the inner pilot centerbody wall at a pilot fuel metering orifice. The fuel nozzle also includes a pilot fuel film surface downstream from the annular fuel passage and an annular splitter surrounding the pilot fuel injector. The annular splitter comprises, in axial sequence: an upstream section, a splitter throat having a diameter that is larger than a downstream diameter defined by the pilot fuel film surface, and a downstream diverging surface having an average diverging angle of about 24° to about 40° in relation to a centerline axis.
Abstract translation: 为燃气涡轮发动机提供燃料喷嘴，并且可以包括具有轴向细长的内导向中心体壁和外导向中心体壁的引燃燃料喷射器，其中轴向延伸的内导向中心体壁从上游端延伸 到限定引燃燃料喷射器的下游端的环形燃料通道。 燃料通道在导向燃料计量孔处与内部先导中心体壁相交。 燃料喷嘴还包括在环形燃料通道下游的导向燃料膜表面和围绕引燃燃料喷射器的环形分流器。 环形分流器轴向地包括：上游部分，具有大于由导向燃料膜表面限定的下游直径的直径的分流喉部，以及具有约24°至约平均发散角的下游发散表面 相对于中心线轴线为40°。
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公开(公告)号：US11846423B2
公开(公告)日：2023-12-19
申请号：US17232691
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Clayton Stuart Cooper , Michael Anthony Benjamin , Hiranya Kumar Nath , Rameshkumar Muthuvel Chandrasekaran
IPC: F23R3/28 , F02M61/18 , B01F23/21 , B01F25/10 , B01F23/213 , B01F101/00
CPC classification number: F23R3/286 , B01F23/2132 , B01F25/10 , F02M61/18 , B01F2101/503
Abstract: A mixer assembly having a plurality of mixer vanes, each of the plurality of mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist, wherein each of the plurality of mixer vanes has a 3-dimensional shape defined by the length, width, thickness, cross-sectional area, curvature, and twist of the body portion, and wherein at least one of the plurality of mixer vanes has a non-uniform 3-dimensional shape.
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公开(公告)号：US20220333782A1
公开(公告)日：2022-10-20
申请号：US17232691
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Clayton Stuart Cooper , Michael Anthony Benjamin , Hiranya Kumar Nath , Rameshkumar Muthuvel Chandrasekaran
Abstract: A mixer assembly having a plurality of mixer vanes, each of the plurality of mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist, wherein each of the plurality of mixer vanes has a 3-dimensional shape defined by the length, width, thickness, cross-sectional area, curvature, and twist of the body portion, and wherein at least one of the plurality of mixer vanes has a non-uniform 3-dimensional shape.
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公开(公告)号：US09927126B2
公开(公告)日：2018-03-27
申请号：US14735694
申请日：2015-06-10
Applicant: General Electric Company
CPC classification number: F23R3/343 , F23D11/104 , F23D11/105 , F23D11/14 , F23D2900/11101 , F23R3/14 , F23R3/32
Abstract: A pilot fuel injector is provided for a fuel nozzle of a gas turbine engine. The pilot fuel injector can include an axially-elongated, inner pilot centerbody wall extending from an upstream end to a downstream end, with the axially-elongated, inner pilot centerbody wall having a diverging-converging orientation with respect to a centerline axis to define a hollow tube having an upstream diameter, a throat, and a downstream diameter such that the throat has an inner diameter that is less than both of the upstream diameter and the downstream diameter. The pilot fuel injector also includes a center air circuit positioned at the upstream end, and an annular fuel passage defining the downstream end and intersecting with the centerbody wall at a pilot fuel metering orifice. A pilot fuel film surface is downstream from the annular fuel passage.
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