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公开(公告)号：US07048496B2
公开(公告)日：2006-05-23
申请号：US10285891
申请日：2002-10-31
申请人： Robert Proctor , James Patrick Dolan , John Christopher Brauer , Christopher Charles Glynn , Kenneth Martin Lewis
发明人： Robert Proctor , James Patrick Dolan , John Christopher Brauer , Christopher Charles Glynn , Kenneth Martin Lewis
IPC分类号： F01D25/12
CPC分类号： F01D25/14 , F01D1/26 , F01D11/006 , Y02T50/675
摘要： A rotor system for a gas turbine engine is provided having an outer rotor which includes an annular outer spool that comprises at least one ring portion of increased thickness with respect to the remainder of the outer spool, attached to a relatively thinner, axially extending arm portion. A plurality of outer turbine blades are attached to the ring portion of the outer spool and extend radially inwardly into a working gas flowpath of the engine. A casing surrounds the outer spool and defines an annular cavity between the casing and the outer spool, which is sealed by forward and aft brush seals at the forward and aft ends thereof. At least one inlet port is formed through the casing for admitting a flow of cooling air to the annular cavity. Means are provided for directing this cooling air flow to the ring portion of the outer spool.
摘要翻译： 提供了一种用于燃气涡轮发动机的转子系统，其具有外转子，该外转子包括环形外卷轴，该环形外卷轴包括相对于外卷轴的其余部分增加的厚度的至少一个环部分，附接到相对较薄的轴向延伸的臂部分 。 多个外涡轮叶片附接到外卷轴的环部分并且径向向内延伸到发动机的工作气体流动路径中。 壳体围绕外部卷轴并且在壳体和外部卷轴之间限定出一个环形空腔，其在其前端和后端由前后刷密封件密封。 通过壳体形成至少一个入口端口，用于允许冷却空气流进入环形空腔。 提供了用于将该冷却空气流引导到外部卷轴的环部的装置。
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公开(公告)号：US06719296B2
公开(公告)日：2004-04-13
申请号：US10194391
申请日：2002-07-12
IPC分类号： F16J15447
CPC分类号： F16J15/38 , F01D11/003 , F01D11/025 , F05D2250/611 , F16J15/342 , F16J15/3452
摘要： A face seal assembly is provided having an annular seal body mounted in an axially moveable relationship to a seal support structure. A piston ring is disposed between the annular seal body and the seal support structure forming a secondary seal. A first locator spring, which is an annular wave spring, is disposed between said seal support structure and the piston ring to urge the piston ring in an axial direction. Optionally, a second locator spring, also a wave spring, may be disposed between the piston ring and the seal support structure for urging the piston ring in a radial direction.
摘要翻译： 提供一种面密封组件，其具有环形密封体，所述环形密封体以与所述密封件支撑结构轴向移动的关系安装。 活塞环设置在环形密封体和密封支撑结构之间，形成二次密封。 作为环形波形弹簧的第一定位弹簧设置在所述密封支撑结构和活塞环之间，以沿轴向推动活塞环。 可选地，第二定位弹簧（也可以是波形弹簧）可以设置在活塞环和密封支撑结构之间，用于沿径向推动活塞环。
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公开(公告)号：US07007488B2
公开(公告)日：2006-03-07
申请号：US10885147
申请日：2004-07-06
申请人： Robert Joseph Orlando , Thomas Ory Moniz , John Christopher Brauer , Ian Francis Prentice , Erich Alois Krammer , James Patrick Dolan , Robert Alan Frederick
发明人： Robert Joseph Orlando , Thomas Ory Moniz , John Christopher Brauer , Ian Francis Prentice , Erich Alois Krammer , James Patrick Dolan , Robert Alan Frederick
IPC分类号： F02C7/12
摘要： A gas turbine engine includes a compressor powered by a turbine. The turbine includes a nozzle having vanes extending between outer and inner bands. Each vane includes an internal cooling plenum and a bypass tube extending through the bands. First and second manifolds surround the outer band and are disposed in flow communication with the plenums and bypass tubes, respectively. A bleed circuit joins the compressor to the manifolds for providing pressurized air thereto. A control valve modulates airflow to the first manifold and in turn through the cooling plenums of the vanes.
摘要翻译： 燃气涡轮发动机包括由涡轮机供电的压缩机。 涡轮机包括具有在外带和内带之间延伸的叶片的喷嘴。 每个叶片包括一个内部冷却通风室和一个延伸穿过该带的旁通管。 第一和第二歧管围绕外部带并分别设置成与集气室和旁通管流动连通。 泄放回路将压缩机连接到歧管，以向其提供加压空气。 控制阀调节到第一歧管的气流，并依次通过叶片的冷却增压室。
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公开(公告)号：US06884028B2
公开(公告)日：2005-04-26
申请号：US10261072
申请日：2002-09-30
CPC分类号： F01D5/3015 , Y02T50/671
摘要： A blade retention assembly is provided that comprises: a disk, a plurality of blades, each having a dovetail disposed in one of an array of slots formed in the outer periphery of the disk, an annular inner retainer attached to the disk, and a plurality of arcuate blade retainers, the blade retainers being secured to the inner retainer by a hooked rabbet joint. A blade retainer is also provided, comprising an arcuate body having a planar inner face having an arcuate depression formed therein defining a sealing lip, and an aft face disposed opposite the inner face which has an arcuate rim formed therein.
摘要翻译： 提供了一种刀片保持组件，其包括：盘，多个刀片，每个刀片具有设置在形成在盘的外周中的槽阵列之一中的燕尾形，附接到盘的环形内保持器，以及多个 的弓形刀片保持器，刀片保持器通过钩形的拉头接头固定到内部保持器。 还提供了一种刀片保持器，其包括具有平面内表面的弓形体，该内表面具有形成在其中的形成密封唇的弧形凹部，以及与形成在其中的弧形边缘相对的内表面设置的后表面。
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公开(公告)号：US07287959B2
公开(公告)日：2007-10-30
申请号：US11294210
申请日：2005-12-05
CPC分类号： F01D5/20 , F05D2250/29 , F05D2250/292 , Y02T50/673
摘要： A turbine airfoil includes opposite pressure and suction sidewalls, and extends in chord between opposite leading and trailing edges and in span from a root to an outer tip cap. The tip cap bridges the sidewalls, and a flute extends chordally along the pressure sidewall and below the tip cap.
摘要翻译： 涡轮机翼片包括相对的压力和吸力侧壁，并且在相对的前缘和后缘之间并且从根部到外部尖端的跨度中延伸。 尖端帽桥接侧壁，并且凹槽沿着压力侧壁并在尖端帽下方延伸。
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公开(公告)号：US06935837B2
公开(公告)日：2005-08-30
申请号：US10376892
申请日：2003-02-27
CPC分类号： F01D9/065 , F01D11/005 , F01D25/162 , F01D25/24 , F02C7/20 , F05D2230/60 , F05D2230/642
摘要： A method enables a gas turbine engine including a first rotor assembly and a second rotor assembly coupled in axial flow communication downstream from the first rotor assembly to be assembled. The method comprises coupling an upstream end of an extension duct to an outlet of the first rotor assembly, wherein the extension duct includes a plurality of panels coupled circumferentially, and coupling a downstream end of the extension duct to an inlet of the second rotor assembly using at least one fish mouth seal.
摘要翻译： 一种方法使得能够包括第一转子组件和第二转子组件的燃气涡轮发动机，该第一转子组件和第二转子组件在与第一转子组件的下游轴向流动连通地联接以被组装。 该方法包括将延伸管道的上游端连接到第一转子组件的出口，其中延伸管道包括沿圆周方向连接的多个面板，并且将延伸管道的下游端部与第二转子组件的入口连接，该第二转子组件的入口使用 至少有一个鱼嘴密封。
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公开(公告)号：US07578134B2
公开(公告)日：2009-08-25
申请号：US11329783
申请日：2006-01-11
IPC分类号： F02C7/20
摘要： A method for assembling a gas turbine engine is provided. The method includes providing a combustor liner support including a first portion formed with a plurality of circumferentially-spaced recessed areas, and a second portion extending from the first portion. The method also includes coupling the combustor liner support within a combustor such that during engine operations cooling air is channeled through the plurality of recessed areas to facilitate cooling the combustor liner support.
摘要翻译： 提供一种用于组装燃气涡轮发动机的方法。 该方法包括提供包括形成有多个周向间隔开的凹陷区域的第一部分和从第一部分延伸的第二部分的燃烧器衬套支撑件。 该方法还包括将燃烧器衬套支撑件联接在燃烧器内，使得在发动机操作期间，冷却空气被引导通过多个凹陷区域以便于冷却燃烧器衬套支撑件。
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公开(公告)号：US20080145218A1
公开(公告)日：2008-06-19
申请号：US11612289
申请日：2006-12-18
CPC分类号： F01D9/042 , F05D2230/64 , Y10T29/49245
摘要： A method of assembling a turbine includes positioning a turbine nozzle against a forward inner nozzle support extending from a rotor assembly, and coupling a cover to the forward inner nozzle support. The method also includes inserting a tab that extends from the cover within at least one aperture defined in the turbine nozzle.
摘要翻译： 组装涡轮机的方法包括将涡轮喷嘴定位在从转子组件延伸的前向内部喷嘴支撑件上，以及将盖子连接到前部内部喷嘴支撑件。 该方法还包括在限定在涡轮喷嘴中的至少一个孔内插入从盖延伸的突片。
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公开(公告)号：US07771164B2
公开(公告)日：2010-08-10
申请号：US11612289
申请日：2006-12-18
IPC分类号： F03B3/16
CPC分类号： F01D9/042 , F05D2230/64 , Y10T29/49245
摘要： A method of assembling a turbine includes positioning a turbine nozzle against a forward inner nozzle support extending from a rotor assembly, and coupling a cover to the forward inner nozzle support. The method also includes inserting a tab that extends from the cover within at least one aperture defined in the turbine nozzle.
摘要翻译： 组装涡轮机的方法包括将涡轮喷嘴定位在从转子组件延伸的前向内部喷嘴支撑件上，以及将盖子连接到前部内部喷嘴支撑件。 该方法还包括在限定在涡轮喷嘴中的至少一个孔内插入从盖延伸的突片。
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