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71.发明授权公开(公告)号：US07654791B2
公开(公告)日：2010-02-02
申请号：US11477294
申请日：2006-06-29
申请人： Andre Werner
发明人： Andre Werner
IPC分类号： F01D11/20
CPC分类号： F01D11/22 , F05D2220/3216 , F05D2240/11 , F05D2270/65 , F05D2300/431 , F05D2300/437 , F05D2300/501
摘要： An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained.
摘要翻译： 公开了一种用于控制涡轮发动机，特别是飞机发动机的压缩机的叶片顶端间隙的装置和方法。 叶片顶端间隙控制装置具有转子和围绕转子的壳体，形成叶片顶端间隙，包括可移动到叶片顶端间隙中的密封元件和致动器单元，其中密封元件被设计为周向护罩 衬垫由柔性橡胶材料制成，其中至少一个也是周向的管状隔膜被布置。 隔膜通过致动器单元与液压流体作用。 这使得可以抵消由于腐蚀，老化等而在操作期间发生的劣化。结果，保持效率并保持泵的限制间隔。
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公开(公告)号：US20080131270A1
公开(公告)日：2008-06-05
申请号：US11633396
申请日：2006-12-04
IPC分类号： F01D11/20
CPC分类号： F01D11/20 , F01D11/22 , F01D11/24 , F05D2300/505
摘要： A blade gap control system configured to move a blade ring of a turbine engine relative to a blade assembly to reduce the gaps between the tips of the blades and the blade rings to increase the efficiency of the turbine engine is provided. The blade rings can be at an acute angle with respect to the rotational axis of the blade assembly. The axial movement of the blade ring can be done by a pressure differential supplied across the blade ring, the thermal expansion and/or contraction of a linkage or by a piston.
摘要翻译： 叶片间隙控制系统构造成相对于叶片组件移动涡轮发动机的叶片环，以减小叶片和叶片环之间的间隙，以提高涡轮发动机的效率。 叶片环可以相对于叶片组件的旋转轴线成锐角。 叶片环的轴向运动可以通过供应在叶片环上的压力差，连杆的热膨胀和/或收缩或活塞来实现。
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公开(公告)号：US5165845A
公开(公告)日：1992-11-24
申请号：US789557
申请日：1991-11-08
申请人： Syed J. Khalid
发明人： Syed J. Khalid
CPC分类号： F02C9/18 , F01D11/20 , F04D27/0246 , F05D2200/11
摘要： Stall margin in a gas turbine compressor is controlled during acceleration by synthesizing the thermal enlargement of critical compressor stages to synthesize the temporary increase in blade-case clearance during acceleration. The change in clearance is used to produce an augmenting stator vane deflection signal which is summed with a steady state vane deflection signal to increase deflection during acceleration until the clearance returns to a nominal level when the expansion of the compressor parts stabilize.
摘要翻译： 在加速期间通过合成关键压缩机级的热膨胀来合成在加速期间刀片间隙的临时增加来控制燃气轮机压缩机中的失速边界。 间隙的变化被用于产生增大的定子叶片偏转信号，其与稳态叶片偏转信号相加，以在加速期间增加偏转，直到当压缩机部件的膨胀稳定时，间隙返回到标称水平。
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公开(公告)号：US20230184127A1
公开(公告)日：2023-06-15
申请号：US17550722
申请日：2021-12-14
申请人： Regi U.S., Inc.
发明人： Paul Porter
IPC分类号： F01D11/20
CPC分类号： F01D11/20 , F05D2240/55
摘要： A rotary device includes a shaft, a rotor coupled to the shaft, and a stator having a cam surface. Vanes reside within slots of the rotary device and engage with the cam surface. A first seal couples to the rotor and includes first grooves that extend in a direction substantially parallel to a rotational axis of the shaft. A second seal couples to the stator and includes second grooves extending in the direction substantially parallel to the rotational axis. A third seal couples to the rotor and includes third grooves extending in the direction substantially parallel to the rotational axis. A fourth seal couples to the stator and includes fourth grooves extending in the direction substantially parallel to the rotational axis. The first grooves and the second grooves, as well as the third grooves and the fourth grooves, from labyrinth seals for the chambers of the rotary device.
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公开(公告)号：US20220341345A1
公开(公告)日：2022-10-27
申请号：US17241242
申请日：2021-04-27
摘要： A turbine containment system is provided. The turbine containment system includes a first containment member surrounding a portion of a turbine including a plurality of rotor disks and rotor blades; and a second containment member in communication with the first containment member, wherein the first containment member and the second containment member together contain each of the rotor disks and the rotor blades therein.
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公开(公告)号：US10851712B2
公开(公告)日：2020-12-01
申请号：US15634098
申请日：2017-06-27
摘要： A clearance control system includes one or more clearance control devices that include features for controlling the clearances between rotating and stationary components of an engine. In one exemplary aspect, a clearance control device utilizes a fluid to pressurize an actuation chamber defined by a compliant member of the clearance control device. The pressurization of the actuation chamber causes the actuation chamber to expand in a direction that changes the clearance between the stationary and rotating components of the engine.
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公开(公告)号：US10815814B2
公开(公告)日：2020-10-27
申请号：US15588911
申请日：2017-05-08
发明人： Mark F. Zelesky , Brian Merry , Gabriel L. Suciu
摘要： A control system for a gas turbine engine comprises a case structure, a clearance control ring mounted for movement relative to the case structure, an outer air seal mounted to the clearance control ring and facing a first engine component, and a control and valve assembly that receives flow from a flow input source. The control and valve assembly is configured to direct flow into a first cavity positioned radially between the case structure and the outer air seal, and wherein the control and valve assembly is configured to direct flow into a second cavity positioned downstream of the first cavity to interact with a second engine component. A method of controlling flow between a compressor section and turbine section is also disclosed.
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公开(公告)号：US10808562B2
公开(公告)日：2020-10-20
申请号：US16254694
申请日：2019-01-23
发明人： Michael G. McCaffrey
IPC分类号： F02C7/28 , F01D11/00 , F23R3/00 , F01D9/02 , F01D5/12 , F01D11/08 , F01D11/14 , F01D11/20 , F16J15/02 , F16J15/06
摘要： A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a housing mountable to an engine static structure, a seal carrier secured to the housing and configured to be selectively biased from the housing, and a wedge seal secured to the seal carrier. The wedge seal abuts against sealing surfaces of adjacent blade outer air seals in response to movement of the seal carrier relative to the housing. The wedge seal is separate and distinct from the seal carrier. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
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公开(公告)号：US10801354B2
公开(公告)日：2020-10-13
申请号：US15137193
申请日：2016-04-25
摘要： A gas turbine engine includes a first case, a second case, and a fastener. The first case has a first flange defining a first opening. The second case has a second flange defining a second opening. The second flange abuts the first flange. The fastener extends through the first opening and the second opening. The fastener defines a first bore that extends through a fastener head along an axis towards an outlet port defined by a fastener shank.
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公开(公告)号：US20200157965A1
公开(公告)日：2020-05-21
申请号：US16195336
申请日：2018-11-19
IPC分类号： F01D11/20
摘要： Systems and methods are provided that use a tip clearance control apparatus comprising a mechanical iris, where the tip clearance control apparatus controls a distance between a tip of a blade and a ring of abradable material positioned in an adjustable opening of the mechanical iris.
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