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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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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：US08118548B2
公开(公告)日：2012-02-21
申请号：US12210439
申请日：2008-09-15
IPC分类号： F01D5/20
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：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：US08002515B2
公开(公告)日：2011-08-23
申请号：US12206333
申请日：2008-09-08
IPC分类号： F03B11/02
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：US20090058013A1
公开(公告)日：2009-03-05
申请号：US11896533
申请日：2007-09-04
IPC分类号： F16J15/447 , F01D11/08
CPC分类号： F01D11/02 , F01D11/001
摘要： A uniquely configured rotating seal tooth is used in conjunction with commonly used labyrinth-type seals that provide a seal between a rotating component and a stationary component. The uniquely configured rotating seal tooth produces a compression mechanism to counter leakage flow through the labyrinth of seal teeth, thereby lessening the pressure gradient that drives leakage and reversing the direction of some of the leakage flow.
摘要翻译： 结合常用的迷宫型密封件与旋转部件和固定部件之间提供密封的独特结构的旋转密封齿。 独特构造的旋转密封齿产生压缩机构以抵抗通过密封齿的迷宫的泄漏流，从而减小驱动泄漏并扭转一些泄漏流的方向的压力梯度。
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公开(公告)号：US08083475B2
公开(公告)日：2011-12-27
申请号：US12352664
申请日：2009-01-13
IPC分类号： F01D5/30 , F01D11/00 , F01D25/24 , F01D11/02 , B63H1/16 , B64C11/00 , B64C11/04 , F03B3/12 , F04D29/34 , F04D3/00 , F04D19/00
CPC分类号： F01D11/001 , F05D2250/184
摘要： The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon.
摘要翻译： 本申请为涡轮机桶提供天使翼密封件。 天使翼密封件可以包括具有正弦形外缘的第一翼和定位在其上的多个翼齿。
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公开(公告)号：US08066475B2
公开(公告)日：2011-11-29
申请号：US11896533
申请日：2007-09-04
IPC分类号： F01D11/02
CPC分类号： F01D11/02 , F01D11/001
摘要： A uniquely configured rotating seal tooth is used in conjunction with commonly used labyrinth-type seals that provide a seal between a rotating component and a stationary component. The uniquely configured rotating seal tooth produces a compression mechanism to counter leakage flow through the labyrinth of seal teeth, thereby lessening the pressure gradient that drives leakage and reversing the direction of some of the leakage flow.
摘要翻译： 结合常用的迷宫型密封件与旋转部件和固定部件之间提供密封的独特结构的旋转密封齿。 独特构造的旋转密封齿产生压缩机构以抵抗通过密封齿的迷宫的泄漏流，从而减小驱动泄漏并扭转一些泄漏流的方向的压力梯度。
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公开(公告)号：US20100178159A1
公开(公告)日：2010-07-15
申请号：US12352664
申请日：2009-01-13
CPC分类号： F01D11/001 , F05D2250/184
摘要： The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon.
摘要翻译： 本申请为涡轮机桶提供天使翼密封件。 天使翼密封件可以包括具有正弦形外缘的第一翼和定位在其上的多个翼齿。
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