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81. 发明授权

US08171734B2 Swirlers 有权
标题翻译：旋流器
公开(公告)号：US08171734B2
公开(公告)日：2012-05-08
申请号：US12200956
申请日：2008-08-29
申请人： Marie Ann McMasters , Michael A. Benjamin , Alfred Mancini
发明人： Marie Ann McMasters , Michael A. Benjamin , Alfred Mancini
IPC分类号： F02C1/00
CPC分类号： B23P6/007 , B22F2007/068 , B23P6/005 , B23P2700/13 , B33Y80/00 , F23D2213/00 , F23D2900/00018 , F23D2900/14701 , F23R3/14 , F23R3/28 , F23R3/283 , F23R3/286 , F23R3/343 , F23R2900/00018 , Y02T50/675 , Y10T29/49318 , Y10T29/4932 , Y10T29/49746 , Y10T137/265
摘要： A unitary swirler is disclosed, comprising a body having a swirler axis, and a plurality of vanes arranged in a circumferential direction around the swirler axis, wherein the swirler has a unitary construction. In one embodiment, the unitary swirler has a rim located coaxially with the swirler axis, and a wall extending between a portion of the rim and a portion of the hub. In another embodiment, the unitary swirler has an adaptor having a passage that is configured to direct a flow of air towards at least some of the plurality of vanes.
摘要翻译：公开了一种单一旋流器，包括具有旋流器轴线的主体和围绕旋流器轴线沿圆周方向布置的多个叶片，其中旋流器具有整体结构。在一个实施例中，整体旋流器具有与旋流器轴线同轴的边缘，以及在轮缘的一部分和轮毂的一部分之间延伸的壁。在另一个实施例中，单一旋流器具有适配器，该适配器具有通道，该通道被配置为将空气流引向多个叶片中的至少一些。

82. 发明申请

US20110296840A1 GAS TURBINE COMBUSTOR INJECTION ASSEMBLY, AND COMBUSTOR FUEL MIXTURE FEED METHOD 有权
标题翻译：燃气轮机燃油喷射装置，燃料燃料混合物进料方法
公开(公告)号：US20110296840A1
公开(公告)日：2011-12-08
申请号：US13100761
申请日：2011-05-04
申请人： Fabio Turrini , Antonio Peschiulli , Marco Motta
发明人： Fabio Turrini , Antonio Peschiulli , Marco Motta
IPC分类号： F23R3/34 , F23R3/14 , F02C7/228
CPC分类号： F23R3/286 , F23D2900/11101 , F23D2900/14701 , F23R3/12
摘要： A fuel mixture is fed to a gas turbine combustor by an injection assembly, which has an outer body with combustion-supporting air inlets; a conical tubular portion housed inside the outer body and partly defining an inner conduit and an outer annular conduit; and a first and second feed circuit for feeding liquid fuel to the inner conduit and outer annular conduit respectively; the first circuit having a ring of conduits with respective axes parallel to a generating line of an outer surface of the conical tubular portion.
摘要翻译：燃料混合物通过注射组件供给到燃气轮机燃烧器，注射组件具有带有燃烧支撑空气入口的外部主体; 锥形管状部分，容纳在外部本体内部并且部分地限定内部导管和外部环形导管; 以及分别将液体燃料供给到内部管道和外部环形管道的第一和第二进料回路; 所述第一回路具有导管环，所述管环的相应轴线平行于所述锥形管状部分的外表面的生成线。

83. 发明授权

US08061142B2 Mixer for a combustor 有权
标题翻译：燃烧器用混合器
公开(公告)号：US08061142B2
公开(公告)日：2011-11-22
申请号：US12120785
申请日：2008-05-15
申请人： David Allen Kastrup , Marie Ann McMasters
发明人： David Allen Kastrup , Marie Ann McMasters
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： B23P6/007 , B22F2007/068 , B23P6/005 , B23P2700/13 , B33Y80/00 , F23D2213/00 , F23D2900/00018 , F23D2900/14701 , F23R3/14 , F23R3/28 , F23R3/283 , F23R3/286 , F23R3/343 , F23R2900/00018 , Y02T50/675 , Y10T29/49318 , Y10T29/4932 , Y10T29/49746 , Y10T137/265
摘要： A mixer having a unitary construction is disclosed comprising an annular housing having an axis and at least a first swirler having a plurality of vanes arranged circumferentially around the axis such that circumferentially adjacent vanes form at least one flow passage that is oriented at least partially in an axial direction with respect to the axis. In another exemplary embodiment, a mixer having a unitary construction is disclosed comprising a swirler having a plurality of radial vanes arranged circumferentially around the axis and oriented at least partially in a radial direction.
摘要翻译：公开了一种具有整体结构的混合器，其包括具有轴线的环形壳体和至少第一旋流器，其具有围绕所述轴线周向布置的多个叶片，使得周向相邻的叶片形成至少一个流动通道，其至少部分定向在相对于轴线的轴向。在另一个示例性实施例中，公开了一种具有整体结构的混合器，其包括旋流器，所述旋流器具有围绕所述轴线周向布置并且至少部分地沿径向定向的多个径向叶片。

84. 发明申请

US20110168801A1 STEPPED SWIRLER FOR DYNAMIC CONTROL 有权
标题翻译：用于动态控制的STEPPED SWIRLER
公开(公告)号：US20110168801A1
公开(公告)日：2011-07-14
申请号：US13119476
申请日：2009-08-05
申请人： Phillip Hubbard
发明人： Phillip Hubbard
IPC分类号： B05B7/10
CPC分类号： F23R3/286 , F23C2900/07001 , F23D2900/14701 , F23R3/14 , F23R2900/00014
摘要： A swirling device for injecting a medium into a turbine is provided. The swirling device includes a central axis, a central passage in an axial direction along the central axis and an outer perimeter. The swirling device further includes a first duct and a second duct. The first duct and the second duct are adapted for guiding the medium from a region surrounding the outer perimeter to the central passage. The first duct includes a first depth in the axial direction and the second duct includes a second depth in the axial direction. The first depth and the second depth are different.
摘要翻译：提供了一种用于将介质注入到涡轮机中的旋转装置。旋转装置包括中心轴线，沿中心轴线的轴向方向的中心通道和外周边。旋转装置还包括第一管道和第二管道。第一管道和第二管道适于将介质从围绕外周边的区域引导到中心通道。第一管道包括在轴向方向上的第一深度，而第二管道在轴向方向上包括第二深度。第一个深度和第二个深度是不同的。

85. 发明申请

US20110030376A1 Gas injection in a burner 有权
标题翻译：在燃烧器中注入气体
公开(公告)号：US20110030376A1
公开(公告)日：2011-02-10
申请号：US12935940
申请日：2009-03-26
申请人： Vladimir Milosavljevic , Allan Persson , Magnus Persson
发明人： Vladimir Milosavljevic , Allan Persson , Magnus Persson
IPC分类号： F02C7/22
CPC分类号： F23C7/004 , F23C2900/07001 , F23D14/02 , F23D14/58 , F23D14/70 , F23D2900/14003 , F23D2900/14701 , F23R3/286
摘要： A burner including a gas injector for injecting fuel into the burner for a gas turbine engine is provided. The burner is provided with a quarl, which surrounds a combustion room, at least a first channel emerging into the combustion room for providing the combustion room with air mixed with fuel, a swirler for mixing the air and the fuel located at the inlet of the channel, at least one tube for the provision of fuel at an inlet of at least one channel, wherein the tube is provided with a plurality of diffuser holes distributed along the tube acting as gas injectors for effectively distributing fuel in a flow of air passing through the channel.
摘要翻译：提供一种燃烧器，其包括用于将燃料喷射到用于燃气涡轮发动机的燃烧器中的气体喷射器。燃烧器设置有四周，其围绕燃烧室，至少第一通道出现在燃烧室中，用于向燃烧室提供与燃料混合的空气，用于混合空气的旋流器和位于燃烧室入口处的燃料通道，用于在至少一个通道的入口处提供燃料的至少一个管，其中所述管设置有沿着作为气体喷射器的管分布的多个扩散器孔，用于在通过的空气流中有效地分配燃料这个频道。

86. 发明申请

US20100170253A1 METHOD AND APPARATUS FOR FUEL INJECTION IN A TURBINE ENGINE 审中-公开
标题翻译：一种涡轮发动机燃油喷射的方法和装置
公开(公告)号：US20100170253A1
公开(公告)日：2010-07-08
申请号：US12350051
申请日：2009-01-07
申请人： Jonathan Dwight Berry , James T. Brown , Hasan Karim , Girard A. Simons
发明人： Jonathan Dwight Berry , James T. Brown , Hasan Karim , Girard A. Simons
IPC分类号： F02C7/22
CPC分类号： F23R3/286 , F23D2900/14701 , F23R3/12 , F23R3/34 , F23R3/36 , F23R2900/00002 , Y02T50/675 , Y02T50/678
摘要： In one embodiment, a turbine system, may include a fuel nozzle, that includes a plurality of fuel passages and a plurality of air passages offset in a downstream direction from the fuel passages. In the embodiment, an air flow from the air passages is configured to intersect with a fuel flow from the fuel passages at an angle to induce swirl and mixing of the air flow and the fuel flow downstream of the fuel nozzle.
摘要翻译：在一个实施例中，涡轮机系统可以包括燃料喷嘴，燃料喷嘴包括多个燃料通道和沿着下游方向偏离燃料通道的多个空气通道。在该实施例中，来自空气通道的空气流被构造成与来自燃料通道的燃料流以一定角度相交，以引起气流和燃料喷嘴下游的燃料流的涡流和混合。

87. 发明申请

US20100107644A1 COMBUSTION PRE-CHAMBER 审中-公开
标题翻译：燃烧前房
公开(公告)号：US20100107644A1
公开(公告)日：2010-05-06
申请号：US12593705
申请日：2008-03-27
申请人： Nigel Wilbraham
发明人： Nigel Wilbraham
IPC分类号： F02C7/22
CPC分类号： F23R3/286 , B01F5/0473 , B01F5/0614 , B01F2005/0017 , B01F2005/0621 , B01F2005/0636 , F23C2900/07002 , F23D14/70 , F23D2900/14021 , F23D2900/14701 , F23R3/14 , F23R2900/03041
摘要： A combustion pre-chamber including an upstream end and a downstream end is provided. The combustion pre-chamber includes a transition channel formed by a wall, the wall extending between the upstream end and the downstream end, and at least one flow trip arranged on the wall and tapering in height and width to the downstream end. Also provided are a burner assembly including a combustion pre-chamber, and a gas turbine engine.
摘要翻译：提供包括上游端和下游端的燃烧预燃室。燃烧预燃室包括由壁形成的过渡通道，在上游端和下游端之间延伸的壁，以及布置在壁上的至少一个流动脱落，并且在高度和宽度上向下游端渐缩。还提供了一种燃烧器组件，其包括燃烧预燃室和燃气涡轮发动机。

88. 发明申请

US20100065142A1 METHOD OF MANUFACTURING A UNITARY CONDUIT FOR TRANSPORTING FLUIDS 有权
标题翻译：制造用于运输流体的单元管道的方法
公开(公告)号：US20100065142A1
公开(公告)日：2010-03-18
申请号：US12182485
申请日：2008-07-30
申请人： MARIE ANN MCMASTERS , Michael A. Benjamin , Alfred Mancini
发明人： MARIE ANN MCMASTERS , Michael A. Benjamin , Alfred Mancini
IPC分类号： F16L9/02 , B22F7/02
CPC分类号： B23P6/007 , B22F2007/068 , B23P6/005 , B23P2700/13 , B33Y80/00 , F23D2213/00 , F23D2900/00018 , F23D2900/14701 , F23R3/14 , F23R3/28 , F23R3/283 , F23R3/286 , F23R3/343 , F23R2900/00018 , Y02T50/675 , Y10T29/49318 , Y10T29/4932 , Y10T29/49746 , Y10T137/265
摘要： A method for fabricating a unitary conduit is disclosed the method comprising the steps of determining three-dimensional information of the unitary conduit having at least one flow passage, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary conduit, and successively forming each layer of the unitary conduit by fusing a metallic powder using laser energy. A unitary conduit is disclosed, comprising a body and a flow passage, wherein the flow passage and the body have a unitary construction, and made by using a rapid manufacturing process.
摘要翻译：公开了一种用于制造单一管道的方法，该方法包括以下步骤：确定具有至少一个流动通道的单一管道的三维信息，将三维信息转换成多个切片，每个切片限定横截面层的单一导管，并且通过使用激光能量融合金属粉末来连续地形成单层管道的每一层。公开了一种单体导管，其包括主体和流动通道，其中流动通道和主体具有整体结构，并且通过使用快速制造工艺制成。

89. 发明申请

US20100058767A1 SWIRL ANGLE OF SECONDARY FUEL NOZZLE FOR TURBOMACHINE COMBUSTOR 审中-公开
标题翻译：涡轮燃烧器二次燃油喷嘴的SWIRL角
公开(公告)号：US20100058767A1
公开(公告)日：2010-03-11
申请号：US12205503
申请日：2008-09-05
申请人： Derrick Walter Simons , Alberto Jose Negroni , Larry Lou Thomas , Jeffrey Scott LeBegue
发明人： Derrick Walter Simons , Alberto Jose Negroni , Larry Lou Thomas , Jeffrey Scott LeBegue
IPC分类号： F02C1/00
CPC分类号： F23R3/14 , F23D2900/14701 , F23R3/286 , F23R3/34
摘要： A combustor includes a primary combustion chamber and a secondary combustion chamber, one or more primary nozzles disposed in the primary combustion chamber and providing fuel to the primary combustion chamber, a centerbody assembly, a venturi disposed downstream of the centerbody assembly, and a secondary fuel nozzle housed within the centerbody assembly and extending towards the venturi and providing fuel to the secondary combustion chamber. The secondary fuel nozzle includes a fuel passage and an air passage, and a swirler positioned around the fuel passage and having one or more vanes projecting radially within the air passage, each vane having a trailing edge arranged at a swirl angle relative to a longitudinal axis of the secondary fuel nozzle, the swirl angle is greater than 45°.
摘要翻译：燃烧器包括主燃烧室和二次燃烧室，设置在主燃烧室中的一个或多个主喷嘴并向主燃烧室提供燃料，中心体组件，设置在中心体组件下游的文丘里管和辅助燃料喷嘴容纳在中心体组件内并且朝向文丘里管延伸并向第二燃烧室提供燃料。二次燃料喷嘴包括燃料通道和空气通道，以及旋转器，其位于燃料通道周围并且具有一个或多个径向地在空气通道内突出的叶片，每个叶片具有相对于纵向轴线以旋转角度布置的后缘的二次燃料喷嘴，旋转角度大于45°。

90. 发明申请

US20090320490A1 Gas Turbine Combustor 有权
标题翻译：燃气轮机燃烧器
公开(公告)号：US20090320490A1
公开(公告)日：2009-12-31
申请号：US12226069
申请日：2007-04-04
申请人： Ulf Nilsson , Peter Senior
发明人： Ulf Nilsson , Peter Senior
IPC分类号： F23C7/00 , F23R3/12 , F23R3/28
CPC分类号： F23C7/002 , F23D2900/14701 , F23R3/12 , F23R3/34 , F23R3/36
摘要： A gas turbine combustor is provided, which comprises: a combustion chamber having an axial direction and a radial direction; air passages for feeding an air stream into the combustion chamber which are oriented such that the flowing direction for each air stream flowing into the combustion chamber includes an angle with the combustion chamber's radial direction so as to introduce a swirl in the in-flowing air and an angle of at least 60° with the combustion chamber's axial direction; and fuel injection openings which are located in the air passages. Each air passage defines a turning flow path with a turning between 70° and 150° in a radial direction of the combustion chamber and a turning between 0° and 235° in an axial direction of the combustion chamber.
摘要翻译：提供一种燃气轮机燃烧器，其包括：具有轴向和径向方向的燃烧室; 用于将空气流供给到燃烧室中的空气通道，其被定向成使得流入燃烧室的每个气流的流动方向与燃烧室的径向方向成一角度，以便在流入的空气中引入涡流，并且与燃烧室的轴向方向至少为60°的角度; 和位于空气通道中的燃料喷射开口。每个空气通道限定在燃烧室的径向方向上在70°和150°之间的转动和在燃烧室的轴向方向上在0°和235°之间的转动的转向流动路径。

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