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71. 发明授权

US10247029B2 Method for clearance control in a gas turbine engine 有权
公开(公告)号：US10247029B2
公开(公告)日：2019-04-02
申请号：US15015667
申请日：2016-02-04
申请人： United Technologies Corporation
发明人： Graham Ryan Philbrick , Allison Zywiak
IPC分类号： F01D11/22 , F01D5/12 , F01D25/24 , F04D29/052 , F04D29/32 , F04D29/52 , F01D3/04 , F04D29/16
摘要： A gas turbine engine, system, and method with clearance control are provided. For example, the gas turbine engine includes a static component, and a rotating component that shifts axially in one of an aft direction and a forward direction in relation to the static component during a first operating condition of the gas turbine engine, and shifts axially in the other of the aft direction and the forward direction in relation to the static component during a second operating condition of the gas turbine engine. The first operating condition is when a rotating component growth and a static component growth change at different rates. The second operating condition is when the rotating component growth and static component growth normalize.

72. 发明授权

US10132186B2 System and method for supporting a turbine shroud 有权
公开(公告)号：US10132186B2
公开(公告)日：2018-11-20
申请号：US14825201
申请日：2015-08-13
申请人： General Electric Company
发明人： Jason David Shapiro
IPC分类号： F01D11/16 , F01D11/22 , F01D5/12 , F01D9/04
摘要： In one aspect the present subject matter is directed to a system for supporting a turbine shroud. The system includes a shroud support at least partially defining a first piston sleeve and a piston assembly having a first piston head disposed within the first piston sleeve and a second piston head coupled to the first piston head. The first piston head is slideably engaged with an inner surface of the first piston sleeve. The second piston head is slideably engaged with an inner surface of a second piston sleeve. The system also includes a turbine shroud that is fixedly connected to the piston assembly and that extends radially inwardly from the shroud support. The piston assembly provides for radially inward and radially outward movement of the turbine shroud in response to a change in a radial force applied to a hot side surface of the turbine shroud.

73. 发明申请

US20180291749A1 SHROUD ASSEMBLY FOR TURBINE SYSTEMS 审中-公开
公开(公告)号：US20180291749A1
公开(公告)日：2018-10-11
申请号：US15481674
申请日：2017-04-07
申请人： General Electric Company
发明人： Neelesh Nandkumar SARAWATE
IPC分类号： F01D5/22 , F01D5/14 , F01D11/00 , F01D11/22
CPC分类号： F01D5/225 , F01D5/34 , F01D11/006 , F01D11/008 , F05D2240/81 , F05D2260/201 , Y02T50/672 , Y02T50/676
摘要： A shroud assembly of a turbine system is presented. The shroud assembly includes a plurality of outer shroud segments disposed annularly and defining a first gap between a pair of outer shroud segments of the plurality of outer shroud segments; a plurality of inner shroud segments disposed annularly and radially inward of the plurality of outer shroud segments, and defining a second gap between a pair of inner shroud segments of the plurality of inner shroud segments, wherein the plurality of inner shroud segments is same in number to the plurality of outer shroud segments, and wherein the first gap and the second gap are offset; and an impingement plate coupled to an outer shroud segment of the pair of outer shroud segments and interposed between the outer shroud segment and the pair of inner shroud segments.

74. 发明授权

US09951643B2 Rapid response clearance control system with spring assist for gas turbine engine 有权
公开(公告)号：US09951643B2
公开(公告)日：2018-04-24
申请号：US14781168
申请日：2014-02-06
申请人： United Technologies Corporation
发明人： Brian Duguay
IPC分类号： F01D11/22 , F01D11/14 , F01D11/16 , F01D11/20 , F01D25/24 , F02C7/28
CPC分类号： F01D11/22 , F01D11/14 , F01D11/16 , F01D11/20 , F01D25/24 , F02C7/28 , F05D2220/32 , F05D2240/55 , F05D2270/01
摘要： An active clearance control system of a gas turbine engine includes an actuation cylinder, a puller engaged with an air seal segment and damped with respect to the actuation cylinder, and a full-hoop thermal control ring that at least partially supports the air seal segment. The puller may move the air seal segment between an extended radially contracted BOAS position and a retracted radially expanded BOAS position.

75. 发明申请

US20180030846A1 GAS TURBINE ENGINE ACTIVE CLEARANCE CONTROL SYSTEM 审中-公开
公开(公告)号：US20180030846A1
公开(公告)日：2018-02-01
申请号：US15221061
申请日：2016-07-27
申请人： United Technologies Corporation
发明人： Michael G. McCaffrey
IPC分类号： F01D11/22 , F01D25/24
CPC分类号： F01D11/22 , F01D11/20 , F01D25/24 , F05D2260/97
摘要： A gas turbine engine includes a blade having a tip, a blade outer air seal operatively connected to a case assembly, and an active clearance control system disposed on the case assembly. The active control system includes an actuator assembly. The actuator assembly includes a motor assembly and a shaft. The shaft has a shaft body that extends between a first end that is operatively connected to the motor assembly and a second end that is operatively connected to the blade outer air seal.

76. 发明授权

US09121302B2 Radial compressor blade clearance control system 有权
标题翻译：径向压缩机叶片间隙控制系统
公开(公告)号：US09121302B2
公开(公告)日：2015-09-01
申请号：US13547155
申请日：2012-07-12
申请人： Loc Quang Duong , Xiaolan Hu
发明人： Loc Quang Duong , Xiaolan Hu
IPC分类号： F01D11/22 , F01D9/04
CPC分类号： F01D11/22 , F01D9/045
摘要： A diaphragm assembly includes a cylinder, a circular flange, and a diaphragm. The cylinder defines an axis and includes a first end and a second end opposite the first end. The circular flange is coaxial with the cylinder and at a greater radial distance from the axis than the cylinder. The diaphragm extends from the second end of the cylinder to the flange.
摘要翻译：隔膜组件包括气缸，圆形凸缘和隔膜。圆柱体限定了一个轴线，并包括第一端和与第一端相对的第二端。圆形法兰与圆柱体同轴并且距离轴线比圆柱体更大的径向距离。隔膜从气缸的第二端延伸到凸缘。

77. 发明申请

US20150167487A1 TURBOMACHINE COLD CLEARANCE ADJUSTMENT 有权
标题翻译：涡轮冷清除调整
公开(公告)号：US20150167487A1
公开(公告)日：2015-06-18
申请号：US14105834
申请日：2013-12-13
申请人： General Electric Company
发明人： Fred Thomas Willett, JR. , Kenneth Michael Koza
IPC分类号： F01D11/22
CPC分类号： F01D21/003 , F01D25/24 , F05D2230/644 , F05D2260/80 , F05D2270/804 , F05D2270/821 , G01B7/14 , G01B11/14 , Y10T29/49323
摘要： A system and method for measuring and adjusting rotor to stator clearances is disclosed, as well as a turbomachine embodying the system and method. In an embodiment, a turbomachine is assembled, including a stator having an upper and a lower stator shell, and a rotor disposed within the stator. A cold clearance between the rotor and the stator is determined at each of a plurality of clearance measurement points using an in situ clearance sensor system. Each of the clearance measurement points is axially spaced from each other clearance measurement point. The cold clearance between the rotor and the stator is adjusted based on the determined cold clearances, by displacing one of the upper stator shell or the lower stator shell relative to a foundation, thereby changing a shape of the upper stator shell or the lower stator shell to accommodate a position of the rotor within the stator.
摘要翻译：公开了一种用于测量和调整转子到定子间隙的系统和方法，以及体现该系统和方法的涡轮机。在一个实施例中，组装涡轮机，包括具有上和下定子壳的定子和设置在定子内的转子。使用原位间隙传感器系统，在多个间隙测量点的每一个处确定转子和定子之间的冷空隙。每个间隙测量点与彼此的间隙测量点轴向间隔开。基于所确定的冷间隙，通过使上定子壳或下定子壳中的一个相对于基座移位，从而改变上定子壳或下定子壳的形状来调节转子和定子之间的冷空隙以容纳转子在定子内的位置。

78. 发明授权

US08939715B2 Active tip clearance control for shrouded gas turbine blades and related method 有权
标题翻译：罩式燃气轮机叶片的主动顶盖间隙控制及相关方法
公开(公告)号：US08939715B2
公开(公告)日：2015-01-27
申请号：US12728870
申请日：2010-03-22
申请人： Harold Edward Miller
发明人： Harold Edward Miller
IPC分类号： F01D5/02 , F01D11/22 , F01D11/24
CPC分类号： F01D11/22 , F01D11/24
摘要： A turbine bucket tip clearance control system includes a rotor assembly having a rotor supporting a plurality of axially spaced wheels, each wheel mounting an annular row of buckets, the annular row of buckets on at least one of the plurality of axially-spaced wheels having a radially outer tip shroud provided with at least one seal tooth. A stator assembly includes a radially inwardly facing, axially-stepped surface, formed with radially inner and outer seal surfaces connected by a shoulder. The stator assembly and rotor assembly are moveable axially relative to each other, enabling selective positioning of the at least one seal tooth radially opposite one of the radially inner and outer seal surfaces to thereby selectively alter a clearance gap between the at least one seal tooth and the radially inward facing axially-stepped surface.
摘要翻译：涡轮机铲斗顶部间隙控制系统包括转子组件，该转子组件具有支撑多个轴向间隔开的轮的转子，每个轮安装环形的一排铲斗，所述多个轴向隔开的轮中的至少一个上的环形排桶具有具有至少一个密封齿的径向外部尖端护罩。定子组件包括径向向内的轴向台阶表面，其形成有由肩部连接的径向内部和外部密封表面。定子组件和转子组件可相对于彼此轴向运动，使得至少一个密封齿能够与径向内部和外部密封表面之一径向相对地选择性地定位，从而选择性地改变至少一个密封齿与径向向内的轴向台阶表面。

79. 发明授权

US08864443B2 Sealing device for steam turbines and method for controlling sealing device 有权
标题翻译：蒸汽轮机密封装置及密封装置控制方法
公开(公告)号：US08864443B2
公开(公告)日：2014-10-21
申请号：US13181970
申请日：2011-07-13
申请人： Kenjiro Narita , Haruyuki Yamazaki , Takeshi Kudo , Kenichi Murata
发明人： Kenjiro Narita , Haruyuki Yamazaki , Takeshi Kudo , Kenichi Murata
IPC分类号： F01D11/00 , F01D11/22 , F16J15/44 , F01D11/06
CPC分类号： F01D11/22 , F01D11/06 , F05D2220/31 , F16J15/442 , F16J15/445
摘要： A sealing structure in which free-cutting spacers on a sealing base plate and sealing fins on a rotor are opposed to each other is provided. The sealing base plate is disposed so as to be movable in an axial direction of the rotor. When a steam turbine increases in load, a pressure head moves in an axial steam-pressure loading direction of the rotor and the sealing base plate connected to the pressure head moves in the axial steam-pressure loading direction. Since the free-cutting spacers at positions opposed to those of the sealing fins existing after the movement of the sealing base plate are maintained in a non-contact state, clearances between the sealing fins and the free-cutting spacers are dimensionally minimized.
摘要翻译：提供密封基板上的自由切割间隔件和转子上的密封翅片彼此相对的密封结构。密封基板被设置成能够沿着转子的轴向移动。当蒸汽轮机的负载增加时，压头在转子的轴向蒸汽加压方向移动，与压头连接的密封基板在轴向蒸汽加压方向移动。由于在与密封基板移动之后存在的密封翅片的位置相对的位置处的自由切割间隔件保持非接触状态，所以密封翅片和自由切割间隔件之间的间隙在尺寸上最小化。

80. 发明授权

US08608435B2 Turbo engine 失效
标题翻译：涡轮发动机
公开(公告)号：US08608435B2
公开(公告)日：2013-12-17
申请号：US12514283
申请日：2007-10-30
申请人： Alexander Böck
发明人： Alexander Böck
IPC分类号： F01D17/12 , F01D17/26 , F01D11/22
CPC分类号： F01D11/22 , F05D2250/61 , F05D2250/611
摘要： A turbomachine, especially a gas turbine, includes a rotor having rotating blades and a stator having a housing and guide blades. The rotating blades form at least one rotating blade ring, which at one radially outward lying end adjoins an inner ring or casing ring of the housing, thereby defining a gap therebetween. The casing ring is connected to a support ring via curved walls, which together with the casing ring and the support ring bound a cavity and form a bellowslike structure. By changing the pressure prevailing in the cavity of the respective bellowslike structure, the gap between the casing ring and the radially outward lying ends of the respective rotating blade ring can be pneumatically adjusted.
摘要翻译：涡轮机，特别是燃气轮机，包括具有旋转叶片的转子和具有壳体和引导叶片的定子。旋转叶片形成至少一个旋转叶片环，其在一个径向向外的一端邻接壳体的内环或壳环，由此在其间限定间隙。套管环通过弯曲的壁连接到支撑环，弯曲壁与套管环和支撑环一起形成一个空腔并形成一个波纹管状结构。通过改变相应的波纹管状结构的空腔中的压力，可以气动地调整套管环与相应旋转叶片环的径向向外的端部之间的间隙。

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