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公开(公告)号：US06609885B2
公开(公告)日：2003-08-26
申请号：US10028931
申请日：2001-12-28
IPC分类号： F01D904
CPC分类号： F01D11/005 , F01D9/041 , F16J15/0812
摘要： In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a pair of sheet metal shims overlaid by a woven metallic cloth. A bracket and a portion of the supplemental seal are received in a groove along a radial inward facing surface of the inner rail. The projecting margin of the cloth seal bears against the annular sealing surface of the nozzle support ring. The shims of the distal margin of the supplemental seal are slit and staggered in a chord-wise direction relative to one another to provide flexibility and effective sealing engagement with the nozzle support ring.
摘要翻译： 在具有在每个喷嘴段的内轨道和喷嘴支撑环的环形轴向相对的密封表面之间具有弦状铰链密封件的燃气轮机中，在高压下在喷嘴段的支撑环和内轨道之间设置补充密封 侧面铰链密封。 补充密封件包括由金属编织布覆盖的一对钣金垫片。 支架和补充密封件的一部分被容纳在沿着内轨的径向向内的表面的凹槽中。 布密封件的突出部分靠在喷嘴支撑环的环形密封表面上。 辅助密封件的远侧边缘的垫片相对于彼此沿着弦向方向被切开并交错，以提供与喷嘴支撑环的柔性和有效的密封接合。
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公开(公告)号：US06599089B2
公开(公告)日：2003-07-29
申请号：US10029227
申请日：2001-12-28
IPC分类号： F01D904
CPC分类号： F02C7/28 , F01D11/005 , F16J15/0812
摘要： In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a pair of sheet metal shims overlaid by a woven metallic cloth supported by a bracket secured to a back side surface of the inner rail. The radially inner end of the cloth seal bears against the annular sealing surface of the nozzle support ring. The shims of the legs of the supplemental seal are slit along their distal margin and staggered in a chord-wise direction relative to one another to provide flexibility and effective sealing engagement with the nozzle support ring.
摘要翻译： 在具有在每个喷嘴段的内轨道和喷嘴支撑环的环形轴向相对的密封表面之间具有弦状铰链密封件的燃气轮机中，在高压下在喷嘴段的支撑环和内轨道之间设置补充密封 侧面铰链密封。 补充密封件包括一对金属垫片，该金属垫片由被固定到内轨道的后侧表面的支架支撑的编织金属布覆盖。 布密封件的径向内端靠在喷嘴支撑环的环形密封表面上。 补充密封件的腿的垫片沿着它们的远侧边缘被切开，并且相对于彼此以和弦方向交错，以提供与喷嘴支撑环的柔性和有效的密封接合。
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公开(公告)号：US06637753B2
公开(公告)日：2003-10-28
申请号：US10028930
申请日：2001-12-28
申请人： Abdul-Azeez Mohammed-Fakir , Ahmad Safi , Iain Robertson Kellock , Gary Michael Itzel , Brian Peter Arness
发明人： Abdul-Azeez Mohammed-Fakir , Ahmad Safi , Iain Robertson Kellock , Gary Michael Itzel , Brian Peter Arness
IPC分类号： F16J1508
CPC分类号： F16J15/0887 , F01D11/005
摘要： In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of each nozzle segment radially inwardly of the chordal hinge seal. To minimize or prevent leakage flow across the chordal hinge seal, the seal is formed of flexible sheet metal which extends between the inner rail and a seat projecting from the annular sealing surface of the support ring radially inwardly of the chordal hinge seal. A first margin of the flexible seal engages in an arcuate groove carried by the inner rail. The opposite margin extends arcuately in sealing engagement along the seat carried by the nozzle support ring.
摘要翻译： 在具有每个喷嘴段的内轨道和喷嘴支撑环的环形轴向相对的密封表面之间具有弦向铰链密封的燃气轮机中，补充密封件设置在每个喷嘴段的支撑环和内轨道之间， 弦铰链密封。 为了最小化或防止跨弦铰链密封件的泄漏流动，密封件由柔性金属板形成，该金属板在内轨道和从支撑环的环形密封表面伸出的位于弦杆铰链密封件的径向内侧的座位之间延伸。 柔性密封件的第一边缘接合由内轨道承载的弓形凹槽。 相反的边缘沿着由喷嘴支撑环承载的座椅的密封接合弓形地延伸。
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公开(公告)号：US20100061848A1
公开(公告)日：2010-03-11
申请号：US12206333
申请日：2008-09-08
CPC分类号： F01D11/24 , F05D2240/11
摘要： Disclosed is a shroud for a turbomachine including at least one support structure and at least one inner shroud disposed at a gas path of a turbomachine. The at least one inner shroud and the at least one support structure have at least one gap therebetween. The at least one gap alternates between at least one restrictive gap and at least one unrestrictive gap and is capable of creating at least one pressure loss mechanism to reduce a hot gas flow in the at least one gap. Further disclosed is a turbomachine and a method for reducing ingestion of hot gas in a turbomachine.
摘要翻译： 公开了一种用于涡轮机的护罩，其包括至少一个支撑结构和设置在涡轮机的气体路径处的至少一个内护罩。 所述至少一个内护罩和所述至少一个支撑结构在它们之间具有至少一个间隙。 所述至少一个间隙在至少一个限制性间隙和至少一个非限制性间隙之间交替，并且能够产生至少一个压力损失机制以减少所述至少一个间隙中的热气流。 进一步公开了一种涡轮机和减少涡轮机中的热气摄入的方法。
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公开(公告)号：US07448850B2
公开(公告)日：2008-11-11
申请号：US11278972
申请日：2006-04-07
IPC分类号： F01D5/30
CPC分类号： F01D25/12 , F05D2240/81 , F05D2260/2322 , Y02T50/67 , Y02T50/676
摘要： A closed loop inner shroud assembly for a gas turbine. The shroud assembly may include a shroud body, a cover plate, an inlet though the cover plate to the shroud body, a serpentine passageway through the shroud body, and an outlet from the shroud body to the cover plate.
摘要翻译： 一种用于燃气轮机的闭环内护罩组件。 护罩组件可以包括护罩主体，盖板，通向罩体的盖板的入口，穿过护罩主体的蛇形通道，以及从护罩主体到盖板的出口。
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6.发明授权Turbine vane segment and impingement insert configuration for fail-safe impingement insert retention 失效涡轮叶片段和冲击插入件配置，用于故障安全冲击插入件保持公开(公告)号：US06561757B2
公开(公告)日：2003-05-13
申请号：US09682195
申请日：2001-08-03
IPC分类号： F01D906
CPC分类号： F01D9/06 , F01D5/186 , F01D5/188 , F01D5/189 , F01D9/02 , F01D11/005 , F01D25/12 , F05D2240/10 , F05D2240/81 , F05D2260/201 , F05D2260/205 , F05D2260/2322
摘要： An impingement insert sleeve is provided that is adapted to be disposed in a coolant cavity defined through a stator vane. The insert has a generally open inlet end and first and second pairs of diametrically opposed side walls, and at least one fail-safe tab defined at a longitudinal end of the insert for limiting radial displacement of the insert with respect to the stator vane.
摘要翻译： 提供了一种冲击插入套管，其适于设置在通过定子叶片限定的冷却剂腔中。 插入件具有大致开口的入口端和第一和第二对直径相对的侧壁，以及限定在插入件的纵向端部处的至少一个故障安全突出部，用于限制插入件相对于定子叶片的径向位移。
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7.发明授权Support pedestals for interconnecting a cover and nozzle band wall in a gas turbine nozzle segment 失效用于连接燃气轮机喷嘴段中的盖和喷嘴带壁的支撑基座公开(公告)号：US06413040B1
公开(公告)日：2002-07-02
申请号：US09593276
申请日：2000-06-13
申请人： Yufeng Phillip Yu , Gary Michael Itzel , Waylon Willard Webbon , Radhakrishna Bagepalli , Steven Sebastian Burdgick , Iain Robertson Kellock
发明人： Yufeng Phillip Yu , Gary Michael Itzel , Waylon Willard Webbon , Radhakrishna Bagepalli , Steven Sebastian Burdgick , Iain Robertson Kellock
IPC分类号： F01D514
CPC分类号： F01D9/065 , F05D2240/81
摘要： A gas turbine nozzle segment has outer and inner band portions. Each band portion includes a nozzle wall, a cover and an impingement plate between the cover and nozzle wall defining two cavities on opposite sides of the impingement plate. Cooling steam is supplied to one cavity for flow through the apertures of the impingement plate to cool the nozzle wall. Structural pedestals interconnect the cover and nozzle wall and pass through holes in the impingement plate to reduce localized stress otherwise resulting from a difference in pressure within the chamber of the nozzle segment and the hot gas path and the fixed turbine casing surrounding the nozzle stage. The pedestals may be cast or welded to the cover and nozzle wall.
摘要翻译： 燃气轮机喷嘴段具有外带部分和内带部分。 每个带部分包括喷嘴壁，盖和在盖和喷嘴壁之间的冲击板，其在冲击板的相对侧上限定两个空腔。 冷却蒸汽被供应到一个空腔以流过冲击板的孔以冷却喷嘴壁。 结构基座将盖和喷嘴壁互连并穿过冲击板中的孔，以减少局部应力，否则由于喷嘴段和热气路径以及围绕喷嘴级的固定涡轮壳体之间的压力差导致。 基座可以铸造或焊接到盖和喷嘴壁。
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公开(公告)号：US20100068041A1
公开(公告)日：2010-03-18
申请号：US12210439
申请日：2008-09-15
IPC分类号： F01D11/08
CPC分类号： F01D9/04 , F01D11/02 , F01D25/246
摘要： A turbomachine includes a casing defining a hot gas path, and a shroud member attached to the casing. The shroud member is spaced from the casing to define a gap. The shroud member includes a first end having a first hook member provided with a first sealing surface and a second end including a second hook member provided with a second sealing surface. At least one of the first and second sealing surfaces includes a plurality of labyrinth seal elements that reduce air leakage through the gap into the hot gas path.
摘要翻译： 涡轮机包括限定热气路径的壳体和附接到壳体的护罩构件。 护罩构件与壳体间隔开以限定间隙。 护罩构件包括具有设置有第一密封表面的第一钩构件的第一端和包括具有第二密封表面的第二钩构件的第二端。 第一和第二密封表面中的至少一个包括多个迷宫式密封元件，其减少通过间隙进入热气体路径的空气泄漏。
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公开(公告)号：US06776583B1
公开(公告)日：2004-08-17
申请号：US10373757
申请日：2003-02-27
IPC分类号： F01D526
CPC分类号： F01D5/22 , F01D5/26 , F01D11/006 , F05D2230/60 , F05D2250/291 , Y10S416/50
摘要： A damper pin for a bucket damper slot in a turbine includes slot insertion ends shaped to fit into the bucket damper slot, and at least a first scallop section formed or machined between the slot insertion ends and shaped to receive a bucket shank pocket radial contour at bucket Hi-C. A second scallop section may also be formed or machined diametrically opposed and anti-symmetrical to the first scallop section between the slot insertion ends.
摘要翻译： 用于涡轮机中的斗式减震器狭槽的减震销包括成形为装配到铲斗减震器狭槽中的狭槽插入端，以及在槽插入端之间形成或加工的至少第一扇贝部分，并且成形为接收铲斗柄袋口径向轮廓 桶Hi-C。 第二扇贝部分也可以形成或加工成在狭槽插入端之间与第一扇形部分直径相对和反对称。
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10.发明授权
公开(公告)号：US5823741A
公开(公告)日：1998-10-20
申请号：US719666
申请日：1996-09-25
申请人： Daniel Ross Predmore , Iain Robertson Kellock , Victor Hugo Correia , John Howard Starkweather , Dean Thomas Lenahan
发明人： Daniel Ross Predmore , Iain Robertson Kellock , Victor Hugo Correia , John Howard Starkweather , Dean Thomas Lenahan
CPC分类号： F01D11/005 , F05D2240/11 , F05D2240/81 , F23R2900/00012
摘要： A seal joint including a sealing member for sealing segmented components of a gas turbine engine is spaced from the gas path to provide more effective cooling. The segments include radial extension flanges spacing the seal joint from the gas path. Various cooling arrangements are adaptable to the modified segments to provide for open or closed circuit impingement or convection cooling plus film cooling. Excessive thermal gradients are avoided as the entire corner of the segment is evenly cooled. Moreover, air usage at the joint is bounded by seal leakage with no extra dedicated cooling air.
摘要翻译： 包括用于密封燃气涡轮发动机的分段部件的密封构件的密封接头与气体路径间隔开以提供更有效的冷却。 这些段包括将密封接头与气体路径间隔开的径向延伸凸缘。 各种冷却装置适用于经修改的部分，以提供开路或闭路冲击或对流冷却加膜冷却。 避免了过度的热梯度，因为片段的整个角均匀冷却。 此外，关节处的空气使用受密封泄漏限制，无需额外的专用冷却空气。
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