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71. 发明授权

US09945244B2 Turbine shroud assembly and method for loading 有权
公开(公告)号：US09945244B2
公开(公告)日：2018-04-17
申请号：US14825636
申请日：2015-08-13
申请人： GENERAL ELECTRIC COMPANY
发明人： Frederic Woodrow Roberts , Victor John Morgan , Matthew Troy Hafner
IPC分类号： F01D11/22 , F01D25/04
CPC分类号： F01D11/22 , F05D2240/11 , F05D2260/50 , F05D2300/6033
摘要： A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, and a biasing apparatus. The biasing apparatus is arranged and disposed to bias the inner shroud in a direction away from the hot gas path, loading the inner shroud to the outer shroud. In another embodiment, the biasing apparatus is a springless biasing apparatus including at least one bellows, at least one thrust piston, or a combination of at least one bellows and at least one thrust piston. A method for loading the turbine shroud assembly is disclosed including biasing the inner shroud having a surface adjacent to a hot gas path in a direction away from the hot gas path toward the outer shroud, wherein biasing the inner shroud includes a biasing force exerted by the biasing apparatus.

72. 发明申请

US20180010475A1 BLADE TRACK ASSEMBLY WITH TURBINE TIP CLEARANCE CONTROL 审中-公开
公开(公告)号：US20180010475A1
公开(公告)日：2018-01-11
申请号：US15425247
申请日：2017-02-06
申请人： Rolls-Royce Corporation
发明人： Richard C. Uskert , Joseph P. Lamusga , Aaron D. Sippel
IPC分类号： F01D11/24 , F01D11/22 , F01D25/24
CPC分类号： F01D11/24 , F01D11/22 , F01D25/246 , F05D2240/11 , Y02T50/672
摘要： A turbine shroud or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.

73. 发明授权

US09845700B2 Active seal system 有权
公开(公告)号：US09845700B2
公开(公告)日：2017-12-19
申请号：US14096726
申请日：2013-12-04
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Douglas D. Dierksmeier
IPC分类号： F01D11/20 , F01D11/00 , F01D15/10 , F01D11/22
CPC分类号： F01D11/20 , F01D11/001 , F01D11/22 , F01D15/10 , F05D2220/76 , F05D2260/407 , F05D2300/6033 , F05D2300/614 , Y02T50/672
摘要： One embodiment of the present disclosure is a unique active seal system. The active seal system includes a rotor and a stationary seal component disposed adjacent to the rotor. The rotor has a rotating seal component and a first electrical generator element. The stationary seal component has a second electrical generator element and a piezoelectric portion in electrical communication with the second electrical generator element.

74. 发明授权

US09784117B2 Turbine engine tip clearance control system with rocker arms 有权
公开(公告)号：US09784117B2
公开(公告)日：2017-10-10
申请号：US14731140
申请日：2015-06-04
申请人： United Technologies Corporation
发明人： Brian Duguay , Timothy M. Davis
IPC分类号： F01D11/22 , F01D11/14 , F01D11/20
CPC分类号： F01D11/22 , F01D11/14 , F01D11/20
摘要： An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly includes a blade outer air seal segment, a linkage, a rocker arm and an actuation device. The linkage is attached to the blade outer air seal segment. The rocker arm includes a first arm and a second arm engaged with the linkage. The actuation device is engaged with the first arm. The actuation device is configured to pivot the rocker arm and thereby radially move the blade outer air seal segment.

75. 发明申请

US20170226886A1 METHOD FOR CLEARANCE CONTROL IN A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20170226886A1
公开(公告)日：2017-08-10
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 , F04D29/52 , F04D29/052 , F04D29/32 , F01D25/24 , F01D5/12
CPC分类号： F01D11/22 , F01D3/04 , F01D5/12 , F01D25/24 , F04D29/052 , F04D29/164 , F04D29/321 , F04D29/526 , F05D2220/32 , F05D2240/52 , F05D2260/30
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.

76. 发明申请

US20170159483A1 HIGH RESPONSE TURBINE TIP CLEARANCE CONTROL SYSTEM 审中-公开
公开(公告)号：US20170159483A1
公开(公告)日：2017-06-08
申请号：US15359066
申请日：2016-11-22
申请人： United Technologies Corporation
发明人： Eric A. Hudson , Stephen K. Kramer
IPC分类号： F01D11/22
CPC分类号： F01D11/22 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2260/53 , F05D2260/56 , F05D2260/57 , F05D2270/20 , Y02T50/671
摘要： An actuation system according to various embodiments can include an actuation ring having a first end and a second end separated by a gap, the actuation ring being configured to be coupled to a blade outer air seal (BOAS). The actuation system can also include an actuator coupled to at least one of the first end or the second end and configured to adjust a size of the gap such that a tip clearance between the BOAS and a blade tip is reduced in response to the size of the gap being reduced.

77. 发明申请

US20170096907A1 GAS TURBINE TIP CLEARANCE CONTROL ASSEMBLY 审中-公开
公开(公告)号：US20170096907A1
公开(公告)日：2017-04-06
申请号：US15205781
申请日：2016-07-08
申请人： DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.
发明人： Sungchul JUNG
IPC分类号： F01D11/22 , F01D25/24 , F01D5/02 , F01D9/02 , F01D11/02 , F01D11/12
CPC分类号： F01D11/22 , F01D5/02 , F01D5/225 , F01D9/02 , F01D11/02 , F01D11/127 , F01D25/24 , F05D2220/32 , F05D2240/11 , F05D2240/20
摘要： The present disclosure relates to a tip clearance control assembly of a gas turbine including a casing, a plurality of blades, a labyrinth seal, and a shroud. The casing guides a flow of combustion gas. The plurality of blades is located inside the casing in such a manner as to be coupled to a rotary shaft of the gas turbine. The labyrinth seal is located at the front end portion of each blade. The shroud surrounds the front end portion of each blade. The casing includes an outer casing having dove tail slots and an inner ring segment having dove tail coupling portions, so that the dove tail coupling portions moves in an axial direction and a radial direction with respect to the gas turbine.

78. 发明授权

US09593589B2 System and method for thrust bearing actuation to actively control clearance in a turbo machine 有权
标题翻译：用于推力轴承致动的系统和方法，以主动地控制涡轮机中的间隙
公开(公告)号：US09593589B2
公开(公告)日：2017-03-14
申请号：US14193077
申请日：2014-02-28
申请人： General Electric Company
发明人： Deepak Trivedi , Norman Arnold Turnquist , Xiaoqing Zheng , Murat Inalpolat
IPC分类号： F01D11/22 , F01D25/16 , F16C41/00 , F01D21/08 , F16C17/04
CPC分类号： F01D11/22 , F01D3/00 , F01D17/26 , F01D21/08 , F01D25/16 , F16C17/04 , F16C41/004 , F16C2360/23
摘要： An actuation system to control clearance in a turbomachine including a shaft bearing including at least one axially displaceable thrust bearing. The axially displaceable thrust bearing configured to axially displace a rotating component relative to a stationary component to control the clearance therebetween. The system further including a plurality of actuators coupled to the at least one axially displaceable thrust bearing and configured to actuate the at least one axially displaceable thrust bearing to control the clearance. The plurality of actuators is configured to deactivate a diametrically opposed actuator in the event of an actuator failure to maintain zero moment. In a topography network, each diametrically opposed actuator pair is coupled to a single control line. In an alternate topography network, alternating actuators are coupled to a single control line. In addition, a method of actuating a thrust bearing to control clearance in a turbomachine is disclosed.
摘要翻译：一种用于控制涡轮机中的间隙的致动系统，包括具有至少一个可轴向移动的推力轴承的轴承座。轴向移动推力轴承构造成相对于静止部件轴向移动旋转部件以控制它们之间的间隙。所述系统还包括耦合到所述至少一个可轴向移动的推力轴承并被构造成致动所述至少一个可轴向移动的止推轴承以控制所述间隙的多个致动器。多个致动器构造成在执行器失效以保持零时刻的情况下停用直径相对的致动器。在地形网络中，每个直径相对的致动器对耦合到单个控制线。在替代的地形网络中，交替的致动器耦合到单个控制线。此外，公开了一种致动推力轴承以控制涡轮机中的间隙的方法。

79. 发明授权

US09587507B2 Blade clearance control for gas turbine engine 有权
标题翻译：燃气轮机发动机叶片间隙控制
公开(公告)号：US09587507B2
公开(公告)日：2017-03-07
申请号：US14143567
申请日：2013-12-30
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Nathan W. Ottow
IPC分类号： F01D11/22 , F04D29/42 , F04D29/62 , F01D5/04
CPC分类号： F01D11/22 , F01D5/043 , F04D29/4206 , F04D29/622
摘要： An apparatus and method for controlling a clearance between the blades of a turbomachinery component and flow forming surface are disclosed herein, and includes controlling the clearance by moving the surface axially relative to the turbomachinery component. In one embodiment the apparatus includes an impeller rotatable about a first axis, a shroud encircling the impeller, and a first ring encircling the first axis. An actuator is operably engaged with the first ring to pivot the first ring about the first axis. The apparatus also includes at least one cam engaged with the first ring and at least one cam follower engaged with the shroud. Pivoting movement of the first ring about the first axis results in the at least one cam urging the at least one cam follower and the shroud along the first axis to vary a distance between the plurality of blades and the shroud.
摘要翻译：本文公开了一种用于控制涡轮机械部件和流动成形表面的叶片之间的间隙的装置和方法，并且包括通过相对于涡轮机械部件轴向移动表面来控制间隙。在一个实施例中，该装置包括可围绕第一轴线旋转的叶轮，环绕叶轮的护罩和环绕第一轴线的第一环。致动器与第一环可操作地接合以围绕第一轴线枢转第一环。该装置还包括与第一环接合的至少一个凸轮和与护罩接合的至少一个凸轮从动件。围绕第一轴的第一环的枢转运动导致至少一个凸轮沿着第一轴向至少一个凸轮从动件和护罩施力以改变多个叶片和护罩之间的距离。

80. 发明申请

US20170051627A1 TURBINE SHROUD ASSEMBLY 有权
标题翻译：涡轮SHROUD总成
公开(公告)号：US20170051627A1
公开(公告)日：2017-02-23
申请号：US14827698
申请日：2015-08-17
申请人： GENERAL ELECTRIC COMPANY
发明人： Matthew Troy HAFNER , Victor John MORGAN , Frederic Woodrow ROBERTS
IPC分类号： F01D11/22 , F01D25/00 , F01D25/08 , F01D25/04
CPC分类号： F01D11/22 , F01D11/14 , F01D11/20 , F01D25/005 , F01D25/04 , F01D25/08 , F05D2220/32 , F05D2240/11 , F05D2260/52 , F05D2260/96 , F05D2300/17 , F05D2300/171 , F05D2300/502 , F05D2300/6033
摘要： A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, a damper block disposed between the inner shroud and the outer shroud, a first biasing apparatus, and a second biasing apparatus. The first biasing apparatus provides a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud. The second biasing apparatus provides a second biasing force to the damper block, biasing the damper block a second deflection distance in a direction toward the hot gas path and away from the outer shroud. The second deflection distance is greater than the first deflection distance.
摘要翻译：公开了一种涡轮机护罩组件，其包括具有与热气体路径相邻的表面的内护罩，外护罩，设置在内护罩和外护罩之间的阻尼块，第一偏压装置和第二偏压装置。第一偏置装置向内护罩提供第一偏置力，从而朝向热气体路径并远离外护罩的方向偏压内护罩的第一偏转距离。第二偏压装置向阻尼器块提供第二偏压力，使阻尼器块沿朝向热气体路径并远离外护罩的方向偏置第二偏转距离。第二偏转距离大于第一偏转距离。

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