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公开(公告)号：US20120186256A1
公开(公告)日：2012-07-26
申请号：US13014388
申请日：2011-01-26
IPC分类号： F02C7/04
摘要： A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.
摘要翻译： 提供了一种用于燃气涡轮发动机的混合器组件，包括具有位于至少一个径向旋流器和至少一个轴向旋流器之间的燃料喷射孔的主混合器，其中喷射到主混合器中的燃料被流过的空气雾化和分散 径向旋流器和轴向旋流器。
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公开(公告)号：US08973368B2
公开(公告)日：2015-03-10
申请号：US13014388
申请日：2011-01-26
摘要： A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.
摘要翻译： 提供了一种用于燃气涡轮发动机的混合器组件，包括具有位于至少一个径向旋流器和至少一个轴向旋流器之间的燃料喷射孔的主混合器，其中喷射到主混合器中的燃料被流过的空气雾化和分散 径向旋流器和轴向旋流器。
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公开(公告)号：US20100126177A1
公开(公告)日：2010-05-27
申请号：US12323773
申请日：2008-11-26
IPC分类号： F02C1/00
摘要： A gas turbine engine augmenter has a gas flowpath. A number of vanes extend into the gas flowpath. A number of augmenter fuel conduits have outlets along at least some of the vanes. At least one burner discharge outlet is along at least one of the vanes for discharging a pilot gas.
摘要翻译： 燃气涡轮发动机增压器具有气体流路。 多个叶片延伸到气体流路中。 多个增压器燃料管道沿着至少一些叶片具有出口。 沿着用于排出先导气体的叶片中的至少一个叶片至少有一个燃烧器排出口。
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公开(公告)号：US08209987B2
公开(公告)日：2012-07-03
申请号：US12323773
申请日：2008-11-26
IPC分类号： F02K3/10
摘要： A gas turbine engine augmenter has a gas flowpath. A number of vanes extend into the gas flowpath. A number of augmenter fuel conduits have outlets along at least some of the vanes. At least one burner discharge outlet is along at least one of the vanes for discharging a pilot gas.
摘要翻译： 燃气涡轮发动机增压器具有气体流路。 多个叶片延伸到气体流路中。 多个增压器燃料管道沿着至少一些叶片具有出口。 沿着用于排出先导气体的叶片中的至少一个叶片至少有一个燃烧器排出口。
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公开(公告)号：US07712315B2
公开(公告)日：2010-05-11
申请号：US11407668
申请日：2006-04-20
IPC分类号： F02K3/10
摘要： A flameholder for an augmentor rotates about an axis radially positioned with a turbine engine. The flameholder is in a streamlined position when the augmentor is not operating to minimize pressure loss and radar cross-section and a turbulent position when the augmentor is operating. A linkage connects the flameholder to an actuator to control the rotational position of the flameholder on the axis. Bypass airflow from the fan cools the flameholders and linkages. The length of the linkages can be varied from one flameholder to another to create asymmetric heat release within the augmentor to avoid screech.
摘要翻译： 用于增压器的火焰稳定器围绕径向位于涡轮发动机的轴线旋转。 当增压器不工作时，火焰稳定器处于流线型位置，以最小化压力损失和雷达横截面以及增压器运行时的湍流位置。 连杆将火焰稳压器连接到致动器以控制火焰稳定器在轴上的旋转位置。 来自风扇的旁路气流冷却火焰支架和连杆。 连杆的长度可以从一个火焰稳定器变化到另一个，以在增压器内产生不对称的热释放以避免尖叫。
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公开(公告)号：US20130263572A1
公开(公告)日：2013-10-10
申请号：US13441031
申请日：2012-04-06
申请人： Jeffery A. Lovett , Donald J. Hautman , Torence P. Brogan , Christopher A. Eckett , Meredith B. Colket, III
发明人： Jeffery A. Lovett , Donald J. Hautman , Torence P. Brogan , Christopher A. Eckett , Meredith B. Colket, III
IPC分类号： F02C7/264
CPC分类号： F02K3/10
摘要： A gas turbine or rocket engine hot section includes a first duct case, a second duct case, a plurality of vanes arranged about an axial centerline, and an igniter located with a first of the plurality of vanes. The first of the plurality of vanes extends axially between a leading edge and a flame holder surface at a trailing edge. The flame holder surface extends radially between a first vane end connected to the first duct case and a second vane end connected to the second duct case. The flame holder surface includes a first section that tapers towards the first vane end, and a second section that tapers away from the first section and towards the second vane end.
摘要翻译： 燃气轮机或火箭发动机热部分包括第一管道壳体，第二管道壳体，围绕轴向中心线布置的多个叶片以及位于多个叶片中的第一个的点火器。 多个叶片中的第一个在后缘处在前缘和火焰保持器表面之间轴向延伸。 火焰保持器表面在连接到第一管道壳体的第一叶片端部和连接到第二管道壳体的第二叶片端部之间径向延伸。 火焰保持器表面包括朝着第一叶片端逐渐变细的第一部分和从第一部分逐渐变细并朝向第二叶片端的第二部分。
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公开(公告)号：US08534071B1
公开(公告)日：2013-09-17
申请号：US13441031
申请日：2012-04-06
申请人： Jeffrey A. Lovett , Donald J. Hautman , Torence P. Brogan , Christopher A. Eckett , Meredith B. Colket, III
发明人： Jeffrey A. Lovett , Donald J. Hautman , Torence P. Brogan , Christopher A. Eckett , Meredith B. Colket, III
IPC分类号： F02K3/10
CPC分类号： F02K3/10
摘要： A gas turbine or rocket engine hot section includes a first duct case, a second duct case, a plurality of vanes arranged about an axial centerline, and an igniter located with a first of the plurality of vanes. The first of the plurality of vanes extends axially between a leading edge and a flame holder surface at a trailing edge. The flame holder surface extends radially between a first vane end connected to the first duct case and a second vane end connected to the second duct case. The flame holder surface includes a first section that tapers towards the first vane end, and a second section that tapers away from the first section and towards the second vane end.
摘要翻译： 燃气轮机或火箭发动机热部分包括第一管道壳体，第二管道壳体，围绕轴向中心线布置的多个叶片以及位于多个叶片中的第一个的点火器。 多个叶片中的第一个在后缘处在前缘和火焰保持器表面之间轴向延伸。 火焰保持器表面在连接到第一管道壳体的第一叶片端部和连接到第二管道壳体的第二叶片端部之间径向延伸。 火焰保持器表面包括朝着第一叶片端逐渐变细的第一部分和从第一部分逐渐变细并朝向第二叶片端的第二部分。
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