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公开(公告)号：US5256352A
公开(公告)日：1993-10-26
申请号：US939275
申请日：1992-09-02
CPC分类号： F23C7/02 , B05B7/065 , B05B7/0861 , F23D11/107
摘要： An impinging jet mixer 40 includes a central atomizer 42 for providing a conical fuel stream 50 and means 56, 58 for providing a plurality of intersecting gas jets 62, 66 which meet the conical fuel spray 50 at an interaction zone 64 spaced downstream of the atomizer discharge opening 70.
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公开(公告)号：US09057523B2
公开(公告)日：2015-06-16
申请号：US13193696
申请日：2011-07-29
申请人： Frank J. Cunha , Timothy S. Snyder
发明人： Frank J. Cunha , Timothy S. Snyder
CPC分类号： F23R3/002 , F02C7/12 , F23R3/04 , F23R3/06 , F23R3/12 , F23R3/14 , F23R2900/00018 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
摘要： A combustor component of a gas turbine engine including a heat shield panel. The heat shield panel a defines microcircuit flow path within a thickness of said heat shield panel.
摘要翻译： 包括隔热板的燃气涡轮发动机的燃烧器部件。 隔热板a限定了所述隔热板的厚度内的微电路流动路径。
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公开(公告)号：US20130192233A1
公开(公告)日：2013-08-01
申请号：US13399399
申请日：2012-02-17
申请人： Jonathan Jeffery Eastwood , Joey Wong , Robert M. Sonntag , Albert K. Cheung , Timothy S. Snyder
发明人： Jonathan Jeffery Eastwood , Joey Wong , Robert M. Sonntag , Albert K. Cheung , Timothy S. Snyder
CPC分类号： F23R3/002 , F23R3/06 , F23R3/10 , F23R3/44 , F23R2900/03044 , Y02T50/675
摘要： A heat shield includes a panel having a forward face and an aft face, a circumferential outer side and a circumferential inner side such that the panel subtends a predetermined arc, and a first radially extending side and a second radially extending side each extending from the circumferential outer side to the circumferential inner side. The panel defines an opening extending between the forward face and the aft face, a lip projecting from the forward face and extending around the opening, a rail projecting from the forward face and extending around the lip to define a cavity region between the lip and the rail, and a plurality of holes in the cavity region. Each of the plurality of holes extends from the forward face to the aft face. A region of the panel extending from the lip to the circumferential outer side is free of any aft-projecting features.
摘要翻译： 隔热罩包括具有前表面和后表面的面板，周向外侧和周向内侧，使得面板对准预定弧度，以及第一径向延伸侧和第二径向延伸侧，每个从圆周方向延伸 外侧到周向内侧。 面板限定了在前表面和后表面之间延伸的开口，从前表面突出并围绕开口延伸的边缘，从前表面突出并围绕唇缘延伸的轨道，以在唇缘和唇部之间限定空腔区域 导轨，以及在空腔区域中的多个孔。 多个孔中的每一个从前表面延伸到后表面。 从唇缘延伸到周向外侧的面板区域没有任何后突出的特征。
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公开(公告)号：US08069648B2
公开(公告)日：2011-12-06
申请号：US12167780
申请日：2008-07-03
CPC分类号： F01D25/30 , F02C7/18 , F02K1/822 , F05D2260/201 , F05D2260/202 , Y02T50/67 , Y02T50/676
摘要： A cooling system for a turbine exhaust assembly comprises an annular case, a flowpath ring and a splash plate. The flowpath ring is coaxially disposed within the annular case. The splash plate extends axially between the annular case and the flowpath ring. A plurality of cooling fluid apertures is formed in the annular case, in order to provide cooling fluid flow onto the splash plate. A plurality of impingement holes is formed in the splash plate, in order to provide impingement flow onto the flowpath ring.
摘要翻译： 用于涡轮排气组件的冷却系统包括环形壳体，流路环和飞溅板。 流路环同轴地设置在环形壳体内。 飞溅板在环形壳体和流路环之间轴向延伸。 在环形壳体中形成多个冷却流体孔，以便提供冷却流体流到飞溅板上。 在飞溅板中形成多个冲击孔，以便在流路环上提供冲击流。
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公开(公告)号：US07798765B2
公开(公告)日：2010-09-21
申请号：US11786672
申请日：2007-04-12
IPC分类号： F01D25/14
CPC分类号： F01D25/26 , F01D25/30 , F02C7/18 , F02K1/822 , F02K3/10 , F05D2240/55 , F05D2250/314 , F05D2250/322 , F05D2260/201 , F05D2260/202 , F05D2270/112 , F05D2270/303 , Y02T50/675
摘要： A cooled turbine exhaust case assembly includes a plenum defined at least in part by a forward outer diameter flowpath ring and a turbine case, a probe positioned at a probe opening formed in the forward outer diameter flowpath ring, and an inlet opening in the turbine case for introducing cooling air to the plenum.
摘要翻译： 冷却的涡轮机排气箱组件包括至少部分地由前外径流径环和涡轮机壳限定的增压室，位于形成在前外径流径环中的探针开口处的探头和涡轮机壳体中的入口开口 用于将冷却空气引入通风室。
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6.发明申请公开(公告)号：US20100050643A1
公开(公告)日：2010-03-04
申请号：US12204272
申请日：2008-09-04
IPC分类号： F23R3/10
CPC分类号： F23R3/20 , F01D25/305 , F02C7/22 , F02C7/2365 , F02K1/822 , F02K3/10 , F05D2240/36 , F05D2260/202 , F05D2260/30 , F23D2207/00 , F23R3/28
摘要： Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.
摘要翻译： 提供了燃气涡轮发动机系统和涉及增强的燃料分散的方法。 在这方面，用于操作燃气涡轮发动机的代表性方法包括：提供通过发动机的气体路径; 沿着发动机的涡轮机下游的气体路径引入燃料喷射; 并以相对较高速度的空气流冲击燃料喷射，使得燃料的雾化增加。
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公开(公告)号：US20100000197A1
公开(公告)日：2010-01-07
申请号：US12167780
申请日：2008-07-03
CPC分类号： F01D25/30 , F02C7/18 , F02K1/822 , F05D2260/201 , F05D2260/202 , Y02T50/67 , Y02T50/676
摘要： A cooling system for a turbine exhaust assembly comprises an annular case, a flowpath ring and a splash plate. The flowpath ring is coaxially disposed within the annular case. The splash plate extends axially between the annular case and the flowpath ring. A plurality of cooling fluid apertures is formed in the annular case, in order to provide cooling fluid flow onto the splash plate. A plurality of impingement holes is formed in the splash plate, in order to provide impingement flow onto the flowpath ring.
摘要翻译： 用于涡轮排气组件的冷却系统包括环形壳体，流路环和飞溅板。 流路环同轴地设置在环形壳体内。 飞溅板在环形壳体和流路环之间轴向延伸。 在环形壳体中形成多个冷却流体孔，以便提供冷却流体流到飞溅板上。 在飞溅板中形成多个冲击孔，以便在流路环上提供冲击流。
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公开(公告)号：US20080253884A1
公开(公告)日：2008-10-16
申请号：US11786672
申请日：2007-04-12
IPC分类号： F01D1/02
CPC分类号： F01D25/26 , F01D25/30 , F02C7/18 , F02K1/822 , F02K3/10 , F05D2240/55 , F05D2250/314 , F05D2250/322 , F05D2260/201 , F05D2260/202 , F05D2270/112 , F05D2270/303 , Y02T50/675
摘要： A cooled turbine exhaust case assembly includes a plenum defined at least in part by a forward outer diameter flowpath ring and a turbine case, a probe positioned at a probe opening formed in the forward outer diameter flowpath ring, and an inlet opening in the turbine case for introducing cooling air to the plenum.
摘要翻译： 冷却的涡轮机排气箱组件包括至少部分地由前外径流径环和涡轮机壳限定的增压室，位于形成在前外径流径环中的探针开口处的探头和涡轮机壳体中的入口开口 用于将冷却空气引入通风室。
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公开(公告)号：US5899076A
公开(公告)日：1999-05-04
申请号：US771408
申请日：1996-12-20
IPC分类号： F02C7/232 , F02M61/16 , F23C7/00 , F23C7/02 , F23C99/00 , F23D11/12 , F23D11/36 , F23D17/00 , F23R3/12 , F23R3/28 , F23R3/30 , F23R3/34 , F02C7/20
CPC分类号： F23D17/002 , F23C7/002 , F05B2250/322 , F23C2900/07002
摘要： A tangential air entry fuel nozzle has a longitudinal axis and two cylindrical-arc scrolls with the centerline of each offset from that of the other. Overlapping ends of these scrolls form an air inlet slot therebetween for the introduction of an air/fuel mixture into the fuel nozzle. A combustor-end endplate has a central opening to permit air and fuel to exit into a combustor, while at the opposite end another endplate blocks the nozzle flow area. The scrolls are secured between these endplates. A centerbody is located between the scrolls coaxial with the axis. The centerbody has a base which includes at least one air supply port extending therethrough, and an internal passageway. The centerbody includes a frustum portion and aerodynamic ramps that prevent flow reversal and flame stabilization between the endplates.
摘要翻译： 切向进气燃料喷嘴具有纵向轴线和两个圆柱形涡卷，其中心线各自偏离另一个。 这些涡卷的重叠端部在其间形成空气入口狭缝，用于将空气/燃料混合物引入燃料喷嘴。 燃烧器端端板具有中心开口，以允许空气和燃料排出到燃烧器中，而在相对端，另一个端板阻挡喷嘴流动区域。 涡卷固定在这些端板之间。 中心体位于与轴线同轴的涡卷之间。 中心体具有包括至少一个延伸穿过其中的空气供应口的基部和内部通道。 中心体包括截头锥部分和空气动力学坡道，防止端板之间的流动反转和火焰稳定。
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公开(公告)号：US5461865A
公开(公告)日：1995-10-31
申请号：US201310
申请日：1994-02-24
CPC分类号： F23C7/002 , F23D17/002 , F23R3/12 , F23C2900/07002 , F23D2206/10
摘要： A premix liquid fuel nozzle has longitudinal air entrance slots (24) into a cylindrical chamber (20). A centerbody (42) produces an axially increasing flow area toward the chamber outlet (32). Liquid fuel is atomized in a specified location (58) adjacent the conical centerbody (42). This area has a high axial shear velocity producing thorough vaporization and uniform mixing before combustion.
摘要翻译： 预混液体燃料喷嘴具有纵向空气入口槽（24）进入圆柱形腔室（20）。 中心体（42）朝向腔室出口（32）产生轴向增加的流动面积。 液体燃料在与圆锥形中心体（42）相邻的指定位置（58）内雾化。 该区域具有高的轴向剪切速度，在燃烧前产生完全蒸发和均匀混合。
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