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1.发明授权Gas turbine air intake manifold controllably changing a mechnical rigidity of the walls of said intake manifold 有权燃气轮机进气歧管可控制地改变所述进气歧管的壁的机械刚度公开(公告)号：US09181875B2
公开(公告)日：2015-11-10
申请号：US13434809
申请日：2012-03-29
CPC分类号： F02C7/045 , F04D29/663 , F05D2260/96
摘要： An intake manifold is provided for inducting combustion air for a compressor of a gas turbine. The intake manifold includes a plurality of walls that delimit against the environment. Devices are provided for controllable change of the mechanical rigidity of the walls to reduce noise which is generated or is emitted in an air intake region during operation of the gas turbine. A gas turbine is also provided and includes an air intake to which air to be compressed is fed via an intake manifold. The intake manifold having a plurality of walls that delimit against the environment. Devices are provided to controllably change a mechanical rigidity of the walls to reduce noise which is generated or emitted in an air intake region during operation of the gas turbine.
摘要翻译： 设有进气歧管，用于引入燃气轮机的压缩机的燃烧空气。 进气歧管包括限定在环境中的多个壁。 提供了用于可控地改变壁的机械刚度的装置，以减少在燃气轮机的运行期间在进气区域中产生或发射的噪声。 还设置燃气轮机，并且包括进气口，待进行压缩的空气经由进气歧管供给到该进气口。 进气歧管具有限定于环境的多个壁。 提供设备以可控地改变壁的机械刚度，以减少在燃气轮机运行期间在进气区域中产生或发射的噪声。
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公开(公告)号：US20120247109A1
公开(公告)日：2012-10-04
申请号：US13434809
申请日：2012-03-29
IPC分类号： F02C7/045
CPC分类号： F02C7/045 , F04D29/663 , F05D2260/96
摘要： An intake manifold is provided for inducting combustion air for a compressor of a gas turbine. The intake manifold includes a plurality of walls that delimit against the environment. Devices are provided for controllable change of the mechanical rigidity of the walls to reduce noise which is generated or is emitted in an air intake region during operation of the gas turbine. A gas turbine is also provided and includes an air intake to which air to be compressed is fed via an intake manifold. The intake manifold having a plurality of walls that delimit against the environment. Devices are provided to controllably change a mechanical rigidity of the walls to reduce noise which is generated or emitted in an air intake region during operation of the gas turbine.
摘要翻译： 设有进气歧管，用于引入燃气轮机的压缩机的燃烧空气。 进气歧管包括限定在环境中的多个壁。 提供了用于可控地改变壁的机械刚度的装置，以减少在燃气轮机的运行期间在进气区域中产生或发射的噪声。 还设置燃气轮机，并且包括进气口，待进行压缩的空气经由进气歧管供给到该进气口。 进气歧管具有限定于环境的多个壁。 提供设备以可控地改变壁的机械刚度，以减少在燃气轮机运行期间在进气区域中产生或发射的噪声。
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公开(公告)号：US06672831B2
公开(公告)日：2004-01-06
申请号：US09995583
申请日：2001-11-29
IPC分类号： F01D1122
CPC分类号： F01D11/22
摘要： A device for setting the gap dimension for a turbomachine, in particular a gas turbine, with heat accumulation segments which are arranged on the guide-vane carrier of the rotor arrangement. At least one drive device projects radially through the turbine casing and the guide-vane carrier and is operatively connected kinematically to at least one heat accumulation segment and which, when actuated, causes a radial spacing of the heat accumulation segment. The heat accumulation segment has, in the flow direction of the turbomachine, a conical contour facing the rotor arrangement and is arranged so as to be displaceable parallel to the flow direction, and in that the drive device is connected to the heat accumulation segment directly or via an eccentric unit, in such a way that, when the drive device is actuated, the heat accumulation segment is displaced, with the result that a radial spacing between the heat accumulation segment and the moving-blade tips can be set.
摘要翻译： 用于设置涡轮机械，特别是燃气轮机的间隙尺寸的装置，其具有设置在转子装置的导向叶片载体上的热积聚段。 至少一个驱动装置径向突出通过涡轮壳体和导向叶片承载件，并且可运动地连接到至少一个热积聚段上，并且当被致动时，其将导致热积聚段的径向间隔。 热积聚段在涡轮机的流动方向上具有面向转子装置的锥形轮廓，并且被布置成可平行于流动方向移动，并且驱动装置直接连接到热积累段 通过偏心单元，使得当驱动装置被致动时，热积累段被移位，结果可以设置热积聚段和活动叶片尖端之间的径向间隔。
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公开(公告)号：US08028967B2
公开(公告)日：2011-10-04
申请号：US12211454
申请日：2008-09-16
申请人： Armin Busekros , Olatunde Omisore , Thomas Wilhelm
发明人： Armin Busekros , Olatunde Omisore , Thomas Wilhelm
IPC分类号： F16M3/00
摘要： A device and a method for mounting a turbine engine, e.g., a gas turbine system, are described, in which a rotor unit is mounted to rotate inside a stationary external housing, having at least two supports for taking up the weight of the turbine engine, these supports being arranged at a spacing from one another in an axial longitudinal direction in relation to the external housing and at one side being articulated directly or indirectly on the external housing and at the other being supported directly or indirectly on a base frame. At least one support provides at least one support face which is supported exclusively in partial regions on at least two support plate elements. The at least one support face of the support is in operational engagement with the base frame by way of the support plate elements.
摘要翻译： 描述了一种用于安装诸如燃气轮机系统的涡轮发动机的装置和方法，其中安装转子单元以在固定外壳内旋转，具有至少两个用于承受涡轮发动机重量的支撑件 ，这些支撑件相对于外壳在轴向纵向方向上彼此间隔开，并且在一侧被直接或间接地铰接在外壳上，另一侧被直接或间接地支撑在基架上。 至少一个支撑件提供至少一个支撑面，其仅在至少两个支撑板元件的部分区域中被支撑。 支撑件的至少一个支撑面通过支撑板元件与基座框架操作接合。
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公开(公告)号：US20100237221A1
公开(公告)日：2010-09-23
申请号：US12720168
申请日：2010-03-09
申请人： Armin Busekros , Pascal Prehm , Miroslav Cindric , Dominic BÜRGI
发明人： Armin Busekros , Pascal Prehm , Miroslav Cindric , Dominic BÜRGI
IPC分类号： F16M1/04
CPC分类号： F01D25/28 , F01D25/243 , F01D25/26 , F05B2260/301
摘要： In a support for a turbine, which turbine has an outer casing which is split into an upper section (11) and a lower section (12) in a horizontal parting plane, in which upper section (11) and lower section (12) are screwed to each other on a horizontal flange (13; 13a, 13b) which lies in the parting plane, the support includes a multiplicity of essentially vertical supports (31) which by an upper end act on the outer casing (18) and by the lower end are supported on a foundation. With such a support, optimum points of application on the outer casing are achieved with the threaded flange connection without limitations by one or more of the supports (31) acting by the upper end on the horizontal flange (13; 13a, 13b) and being part of the horizontal threaded flange connection.
摘要翻译： 在涡轮机的支撑件中，哪个涡轮机具有外壳，该外壳分成上部（11）和下部（12）的水平分离平面中的上部（11）和下部（12） 在位于分型平面中的水平凸缘（13; 13a，13b）上彼此螺纹连接，支撑件包括多个基本上垂直的支撑件（31），其通过上端作用在外壳（18）上，并且由 底端支撑在基础上。 通过这样的支撑，通过螺纹法兰连接实现了外壳上的最佳施加点，而不受由水平凸缘（13; 13a，13b）上端作用的一个或多个支撑件（31）的限制，并且是 水平螺纹法兰连接的一部分。
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公开(公告)号：US07766610B2
公开(公告)日：2010-08-03
申请号：US11245062
申请日：2005-10-07
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F05D2260/601
摘要： Annular or ring-segment-shaped cavities (2, 7) which are formed in particular in multi-shell (11; 12, 13) casings of turbomachines are preferably provided with suitable means for compensating for forming temperature stratifications. According to the invention, an overflow passage (14) connects two points of the cavity to one another which are situated in different circumferential positions. Arranged in the overflow passage (14) is an ejector (17) which can be operated with a motive fluid and which serves to drive a flow through the overflow passage from an upstream end (15) to a downstream end (16).
摘要翻译： 特别是在涡轮机的多壳（11; 12,13）壳体中形成的环形或环形的空腔（2,7）优选地设置有用于补偿成形温度分层的合适装置。 根据本发明，溢流通道（14）将空腔的两个点彼此连接，这两个点位于不同的圆周位置。 布置在溢流通道（14）中的喷射器（17）能够与运动流体一起操作并用于驱动从上游端（15）到下游端（16）的溢流通道的流动。
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公开(公告)号：US08292252B2
公开(公告)日：2012-10-23
申请号：US12720168
申请日：2010-03-09
申请人： Armin Busekros , Pascal Prehm , Miroslav Cindric , Dominic Bürgi
发明人： Armin Busekros , Pascal Prehm , Miroslav Cindric , Dominic Bürgi
IPC分类号： F16M3/00
CPC分类号： F01D25/28 , F01D25/243 , F01D25/26 , F05B2260/301
摘要： In a support for a turbine, which turbine has an outer casing which is split into an upper section (11) and a lower section (12) in a horizontal parting plane, in which upper section (11) and lower section (12) are screwed to each other on a horizontal flange (13; 13a, 13b) which lies in the parting plane, the support includes a multiplicity of essentially vertical supports (31) which by an upper end act on the outer casing (18) and by the lower end are supported on a foundation. With such a support, optimum points of application on the outer casing are achieved with the threaded flange connection without limitations by one or more of the supports (31) acting by the upper end on the horizontal flange (13; 13a, 13b) and being part of the horizontal threaded flange connection.
摘要翻译： 在涡轮机的支撑件中，哪个涡轮机具有外壳，该外壳分成上部（11）和下部（12）的水平分离平面中的上部（11）和下部（12） 在位于分型平面中的水平凸缘（13; 13a，13b）上彼此螺纹连接，支撑件包括多个基本上垂直的支撑件（31），其通过上端作用在外壳（18）上，并且由 底端支撑在基础上。 通过这样的支撑，通过螺纹法兰连接实现了外壳上的最佳施加点，而不受由水平凸缘（13; 13a，13b）上端作用的一个或多个支撑件（31）的限制，并且是 水平螺纹法兰连接的一部分。
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公开(公告)号：US20060073010A1
公开(公告)日：2006-04-06
申请号：US11245062
申请日：2005-10-07
IPC分类号： F04D29/58
CPC分类号： F01D25/12 , F05D2260/601
摘要： Annular or ring-segment-shaped cavities (2, 7) which are formed in particular in multi-shell (11; 12, 13) casings of turbomachines are preferably provided with suitable means for compensating for forming temperature stratifications. According to the invention, an overflow passage (14) connects two points of the cavity to one another which are situated in different circumferential positions. Arranged in the overflow passage (14) is an ejector (17) which can be operated with a motive fluid and which serves to drive a flow through the overflow passage from an upstream end (15) to a downstream end (16).
摘要翻译： 特别是在涡轮机的多壳（11; 12,13）壳体中形成的环形或环形的空腔（2,7）优选地设置有用于补偿成形温度分层的合适装置。 根据本发明，溢流通道（14）将空腔的两个点彼此连接，这两个点位于不同的圆周位置。 布置在溢流通道（14）中的喷射器（17）能够与运动流体一起操作并用于驱动从上游端（15）到下游端（16）的溢流通道的流动。
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