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公开(公告)号：US06775984B2
公开(公告)日：2004-08-17
申请号：US09988522
申请日：2001-11-20
申请人： Alain Lavie , Stéphanie Martelli , Marion Michau , José Rodrigues , Alain Tiepel
发明人： Alain Lavie , Stéphanie Martelli , Marion Michau , José Rodrigues , Alain Tiepel
IPC分类号： F23R328
CPC分类号： F23R3/283 , F23D11/36 , F23D2214/00
摘要： An injector of a two-headed combustion chamber of a turbomachine has a first feed tube which is connected to an annular injection piece for discharging primary fuel into the combustion chamber. It also has a second feed tube surrounding the first feed tube and connected to a cylindrical endpiece for discharging secondary fuel into said combustion chamber. This endpiece has an annular channel of diameter that is greater than the diameter of the second feed tube and that extends over its entire length. A third tube is provided that surrounds the second tube and that is connected to a tubular separation element which is inserted in the annular channel of the cylindrical endpiece so as to form two annular spaces in which a cooling fluid can flow over 360° all the way to the end of the injector.
摘要翻译： 涡轮机的两头燃烧室的喷射器具有第一进料管，其连接到用于将一次燃料排放到燃烧室中的环形喷射件。 它还具有围绕第一进料管的第二进料管并且连接到用于将二次燃料排放到所述燃烧室中的圆柱形端部件。 该端件具有直径大于第二进料管的直径并且在其整个长度上延伸的环形通道。 提供第三管，其围绕第二管并且连接到管状分离元件，管状分离元件插入圆柱形端件的环形通道中，以便形成两个环形空间，冷却流体可以一直流过360度 到注射器的末端。
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2.发明授权Fuel atomization method for turbine combustion engines having aerodynamic turning vanes 有权具有空气动力学转向叶片的涡轮内燃机的燃料雾化方法公开(公告)号：US06460344B1
公开(公告)日：2002-10-08
申请号：US09532534
申请日：2000-03-22
IPC分类号： F23R328
CPC分类号： F23R3/14 , F23D11/107 , F23D2900/11101 , F23R3/30
摘要： A fuel nozzle for dispensing an atomized fluid spray into the combustion chamber of a gas turbine engine. The nozzle includes a body assembly with an inner fuel passage and an annular outer atomizing air passage. The inner fuel passage extends axially along a longitudinal axis to a first terminal end defining a first discharge orifice of the nozzle. The outer air passage extends coaxially with the inner fuel passage along the longitudinal axis to a second terminal end disposed concentrically with the first terminal end and defining a second discharge orifice oriented such that the discharge therefrom impinges on the fuel discharge from the first discharge orifice. An array of turning vanes is disposed within the outer air passage in a circular locus about the longitudinal axis. Each of the vanes is configured generally in the shape of an airfoil and has a pressure side and an opposing suction side. The vanes extend axially from a leading edge surface to a tapering trailing edge surface along a corresponding array of chordal axes, each of axes is disposed at a given turning angle to the longitudinal axis. The suction side of each vane is spaced-apart from a juxtaposing pressure side of an adjacent vane to define a corresponding one of a plurality of aligned air flow channels therebetween. Atomizing air is directed through the air flow channels to be issued from the second discharge orifice as a generally helical flow having a substantial uniform velocity profile.
摘要翻译： 一种用于将雾化的流体喷雾分配到燃气涡轮发动机的燃烧室中的燃料喷嘴。 喷嘴包括具有内部燃料通道和环形外部雾化空气通道的主体组件。 内部燃料通道沿着纵向轴线延伸到限定喷嘴的第一排出孔的第一终端。 外部空气通道沿着纵向轴线与内部燃料通道同轴地延伸到与第一终端同心设置的第二终端并且限定第二排放孔，其定向成使得其排出物从第一排放孔撞击燃料排放。 旋转叶片阵列围绕纵向轴线设置在外部空气通道内的圆形轨迹中。 每个叶片大体上构成翼型的形状，并且具有压力侧和相对的吸力侧。 叶片从前缘表面沿着相应的弦弦阵列轴向延伸到渐缩的后缘表面，每个轴线以相对于纵向轴线的给定转角设置。 每个叶片的吸入侧与相邻叶片的并置压力侧间隔开，以限定其间的多个对准的空气流动通道中的相应一个。 雾化空气被引导通过空气流动通道，以从第二排放孔排出，作为具有基本均匀速度分布的大致螺旋流。
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公开(公告)号：US06786046B2
公开(公告)日：2004-09-07
申请号：US10241352
申请日：2002-09-11
IPC分类号： F23R328
CPC分类号： F23R3/286 , F23D2214/00 , F23D2900/00008
摘要： A flame-holding nozzle for a combustion turbine engine is disclosed. The nozzle includes several elongated sleeves in a substantially concentric arrangement. The sleeves cooperatively provide distinct passageways for fluids to move through the nozzle. The nozzle includes conduits that advantageously direct fluids to designated regions of the nozzle, allowing fuel and cooling fluid to move within the nozzle without becoming commingled. Portions of the nozzle sleeves are also strategically arranged to transmit fluids in a manner that provides substantially-uniform thermal expansion, thereby reducing the need for sliding joints or bellows arrangements.
摘要翻译： 公开了一种用于燃气涡轮发动机的火焰保持喷嘴。 喷嘴包括基本上同心的布置的几个细长的套管。 袖子协同提供不同的通道，用于流体移动通过喷嘴。 喷嘴包括有利地将流体引导到喷嘴的指定区域的导管，允许燃料和冷却流体在喷嘴内移动而不会混合。 喷嘴套管的部分也有策略地布置成以提供基本上均匀的热膨胀的方式传输流体，从而减少对滑动接头或波纹管布置的需要。
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4.发明授权公开(公告)号：US06560964B2
公开(公告)日：2003-05-13
申请号：US10091940
申请日：2002-03-06
IPC分类号： F23R328
CPC分类号： F23R3/14 , F23D11/107 , F23D2900/11101 , F23R3/30
摘要： A fuel nozzle for dispensing an atomized fluid spray into the combustion chamber of a gas turbine engine. The nozzle includes a body assembly with an inner fuel passage and an annular outer atomizing air passage. The inner fuel passage extends axially along a longitudinal axis to a first terminal end defining a first discharge orifice of the nozzle. The outer air passage extends coaxially with the inner fuel passage along the longitudinal axis to a second terminal end disposed concentrically with the first terminal end and defining a second discharge orifice oriented such that the discharge therefrom impinges on the fuel discharge from the first discharge orifice. An array of turning vanes is disposed within the outer air passage in a circular locus about the longitudinal axis. Each of the vanes is configured generally in the shape of an airfoil and has a pressure side and an opposing suction side. The vanes extend axially from a leading edge surface to a tapering trailing edge surface along a corresponding array of chordal axes, each of axes is disposed at a given turning angle to the longitudinal axis. The suction side of each vane is spaced-apart from a juxtaposing pressure side of an adjacent vane to define a corresponding one of a plurality of aligned air flow channels therebetween. Atomizing air is directed through the air flow channels to be issued from the second discharge orifice as a generally helical flow having a substantial uniform velocity profile.
摘要翻译： 一种用于将雾化的流体喷雾分配到燃气涡轮发动机的燃烧室中的燃料喷嘴。 喷嘴包括具有内部燃料通道和环形外部雾化空气通道的主体组件。 内部燃料通道沿着纵向轴线延伸到限定喷嘴的第一排出孔的第一终端。 外部空气通道沿着纵向轴线与内部燃料通道同轴地延伸到与第一终端同心设置的第二终端并且限定第二排放孔，其定向成使得其排出物从第一排放孔撞击燃料排放。 旋转叶片阵列围绕纵向轴线设置在外部空气通道内的圆形轨迹中。 每个叶片大体上构成翼型的形状，并且具有压力侧和相对的吸力侧。 叶片从前缘表面沿着相应的弦弦阵列轴向延伸到渐缩的后缘表面，每个轴线以相对于纵向轴线的给定转角设置。 每个叶片的吸入侧与相邻叶片的并置压力侧间隔开，以限定其间的多个对准的空气流动通道中的相应一个。 雾化空气被引导通过空气流动通道，以从第二排放孔排出，作为具有基本均匀速度分布的大致螺旋流。
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公开(公告)号：US06263676B1
公开(公告)日：2001-07-24
申请号：US09369838
申请日：1999-08-09
申请人： Jakob Keller
发明人： Jakob Keller
IPC分类号： F23R328
CPC分类号： F23C7/002 , F23C2900/07002 , F23D14/64 , F23D17/00
摘要： A burner for operating an internal combustion machine, a combustion chamber of a gas turbine group or firing installation is described, having at least two hollow half truncated-cone shaped bodies which are assembled within one another in such way that their longitudinal axes of symmetry extend so that they are mutually radially offset and which enclose at least two tangential air inlet slots for a combustion inlet airflow and also enclose a hollow conical space, and having a nozzle arrangement for injecting liquid, highly reactive fuel into the hollow conical space, which nozzle arrangement is located in the region of the narrowest internal diameter of the hollow conical space. The invention is distinguished by the fact that one injection appliance for fuel is respectively provided, in the direction of the combustion airflow, upstream of each of the tangential air inlet slots, which injection appliance injects the fuel into the air inlet slot with a flow direction parallel to the combustion inlet airflow.
摘要翻译： 描述了用于操作内燃机，燃气轮机组的燃烧室或燃烧装置的燃烧器，其具有至少两个中空的半截锥形体，其彼此组装成使得它们的纵向对称轴线延伸 使得它们相互径向偏移并且包围用于燃烧入口气流的至少两个切向空气入口狭槽并且还包围中空圆锥形空间，并且具有用于将液体高反应性燃料喷射到中空锥形空间中的喷嘴装置，该喷嘴 排列位于中空锥形空间最窄内径的区域。 本发明的特征在于，一种用于燃料的注射器具分别设置在燃烧气流的方向上，每个切向空气入口狭槽的上游，该注射器具将燃料喷射到进气口中，流动方向 平行于燃烧入口气流。
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