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101.发明授权Method for adjusting the radial gaps which exist between blade airfoil tips or rotor blades and a passage wall 有权用于调节叶片翼型尖端或转子叶片之间存在的径向间隙的通道壁的方法公开(公告)号：US09200529B2
公开(公告)日：2015-12-01
申请号：US13703956
申请日：2011-06-09
Applicant: Tobias Buchal , Björn Buchholz , Thomas Hille , Anna Kapustina , Mirko Milazar , Eric Schwerin
Inventor： Tobias Buchal , Björn Buchholz , Thomas Hille , Anna Kapustina , Mirko Milazar , Eric Schwerin
CPC classification number: F01D11/14 , F01D21/003 , F01D21/04 , F05D2260/80 , G01B7/14 , G01B2210/58 , Y10T29/49004
Abstract: A method for measuring and adjusting gaps between a rotor and a stator of a machine using a sensor is provided. The measuring is conducted when the rotor is operated at a rotational speed below a nominal rotational speed of the machine and without the machine being in operation. The adjusting of the gap is carried out as a function of at least one gap dimension of the gap. The sensor is not resistant to an operating temperature of the machine occurring in a region where the sensor is located. After completion of the measuring the machine is operated with the sensor.
Abstract translation: 提供了使用传感器来测量和调整机器的转子和定子之间的间隙的方法。 当转子以低于机器额定转速的转速操作且没有机器运行时进行测量。 间隙的调整作为间隙的至少一个间隙尺寸的函数进行。 传感器不能抵抗传感器所在区域发生的机器的工作温度。 测量完成后，机器用传感器操作。
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公开(公告)号：US20150098807A1
公开(公告)日：2015-04-09
申请号：US14047513
申请日：2013-10-07
Applicant: General Electric Company
Inventor： Fred Thomas Willett, JR.
IPC: F01D11/14
CPC classification number: F01D11/14 , F01D11/16 , F01D11/22 , F05D2260/30 , Y10T29/49229
Abstract: A system for providing sealing in a turbine is provided. The sealing system includes a retaining channel oriented within a housing structure proximate a moving turbine component. A seal member is coupled within the retaining channel. A first end of the seal member is secured to the housing structure. A second end of the seal member is movable relative to the retaining channel between first and second positions corresponding to a transient operational mode and a steady state operational mode, respectively. The transient operational mode defines a first clearance between the seal member and the moving turbine component. The steady state configuration defines a second clearance that is smaller than the first clearance. A take-up device coupled to the second end of the seal member moves the second end between the first and second positions.
Abstract translation: 提供了一种用于在涡轮机中提供密封的系统。 密封系统包括定位在靠近移动涡轮机部件的壳体结构内的保持通道。 密封构件联接在保持通道内。 密封构件的第一端固定到壳体结构。 密封构件的第二端可分别相对于保持通道在对应于瞬态操作模式和稳态操作模式的第一和第二位置之间移动。 瞬态操作模式限定了密封构件和移动涡轮机部件之间的第一间隙。 稳态构造限定了小于第一间隙的第二间隙。 耦合到密封构件的第二端的卷取装置在第一和第二位置之间移动第二端。
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公开(公告)号：US08984895B2
公开(公告)日：2015-03-24
申请号：US13180275
申请日：2011-07-11
Applicant: James B. Kesseli , Matthew Stephen Baldwin
Inventor： James B. Kesseli , Matthew Stephen Baldwin
Abstract: A method and apparatus are disclosed for a gas turbine spool design combining metallic and ceramic components in a way that controls clearances between critical components over a range of engine operating temperatures and pressures. In a first embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud and separated by a small clearance gap. The ceramic rotor is connected to a metallic volute. In order to accommodate the differential rates of thermal expansion between the ceramic rotor and metallic volute, an active clearance control system is used to maintain the desired axial clearance between ceramic rotor and the ceramic shroud over the range of engine operating temperatures. In a second embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud which is part of a single piece ceramic volute/shroud assembly. As temperature increases, the ceramic volute expands at approximately the same rate as ceramic shroud and tends to increase the axial clearance gap between the ceramic rotor and ceramic shroud, but only by a small amount compared to a metallic volute attached to the shroud in the same way.
Abstract translation: 公开了一种用于燃料涡轮阀芯设计的方法和装置，该设计以在发动机工作温度和压力的范围内控制关键部件之间的间隙的方式组合金属和陶瓷部件。 在第一实施例中，陶瓷涡轮机转子刚好在陶瓷罩内部旋转并由小间隙间隔开。 陶瓷转子与金属蜗壳连接。 为了适应陶瓷转子和金属蜗壳之间的不同的热膨胀率，使用主动间隙控制系统在发动机工作温度的范围内保持陶瓷转子和陶瓷套管之间所需的轴向间隙。 在第二实施例中，陶瓷涡轮转子刚好在作为单件陶瓷蜗壳/护罩组件的一部分的陶瓷罩内旋转。 随着温度升高，陶瓷蜗壳以与陶瓷护罩大致相同的速度膨胀，并且倾向于增加陶瓷转子和陶瓷护罩之间的轴向间隙，但是与附接到其上的护罩的金属蜗壳相比仅仅少量 办法。
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104.发明申请METHOD FOR ADJUSTING THE RADIAL GAPS WHICH EXIST BETWEEN BLADE AIRFOIL TIPS OR ROTOR BLADES AND A PASSAGE WALL 有权调整叶片飞行器叶片或转子叶片和通风壁之间存在的径向叶片的方法公开(公告)号：US20130312249A1
公开(公告)日：2013-11-28
申请号：US13703956
申请日：2011-06-09
Applicant: Tobias Buchal , Björn Buchholz , Thomas Hille , Anna Kapustina , Mirko Milazar , Eric Schwerin
Inventor： Tobias Buchal , Björn Buchholz , Thomas Hille , Anna Kapustina , Mirko Milazar , Eric Schwerin
IPC: F01D11/14
CPC classification number: F01D11/14 , F01D21/003 , F01D21/04 , F05D2260/80 , G01B7/14 , G01B2210/58 , Y10T29/49004
Abstract: A method for measuring and adjusting gaps between a rotor and a stator of a machine using a sensor is provided. The measuring is conducted when the rotor is operated at a rotational speed below a nominal rotational speed of the machine and without the machine being in operation. The adjusting of the gap is carried out as a function of at least one gap dimension of the gap. The sensor is not resistant to an operating temperature of the machine occurring in a region where the sensor is located. After completion of the measuring the machine is operated with the sensor.
Abstract translation: 提供了使用传感器来测量和调整机器的转子和定子之间的间隙的方法。 当转子以低于机器额定转速的转速操作且没有机器运行时进行测量。 间隙的调整作为间隙的至少一个间隙尺寸的函数进行。 传感器不能抵抗传感器所在区域发生的机器的工作温度。 测量完成后，机器用传感器操作。
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公开(公告)号：US20120243976A1
公开(公告)日：2012-09-27
申请号：US13491332
申请日：2012-06-07
Applicant: Henry Grady Ballard, JR. , Fred Thomas Willett, JR.
Inventor： Henry Grady Ballard, JR. , Fred Thomas Willett, JR.
IPC: F01D11/14
CPC classification number: F01D25/26 , F01D25/28 , F05D2230/642 , F05D2230/644 , F05D2240/40 , F05D2260/36
Abstract: A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.
Abstract translation: 提供涡轮机并且包括涡轮机壳体，其包括在其多个阶段的护罩，以及约束元件，其设置成围绕涡轮机壳体至少第一至第四基本上规则间隔的围绕涡轮机壳体的周边位置，所述约束元件构造成同心地约束涡轮机壳体的护罩。
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Patent Agency Ranking
公开(公告)号：US20110070072A1
公开(公告)日：2011-03-24
申请号：US12565108
申请日：2009-09-23
Applicant: Moorthi Subramaniyan
Inventor： Moorthi Subramaniyan
CPC classification number: F01D11/08 , F01D5/225 , F05D2220/30 , F05D2240/80 , Y10T29/4932
Abstract: A tip clearance control mechanism for a rotary machine adapted for reducing leakage flows, and minimizing tip vortex size and penetration into main flow that will improve turbine efficiency. The tip clearance control mechanism includes inventive arrangements of a rotating shroud and a shape of the shroud, teeth of various shapes and locations on the rotating shroud, and one or more stator teeth of various shapes and locations on a stationary shroud or casing wall configurations providing comparable tip clearance control. The reduction in leakage flow is a function of how these components are assembled together, which defines a clearance passage between the rotating shroud and the stationary shroud.
Abstract translation: 一种用于减少泄漏流量的旋转机器的顶端间隙控制机构，并且使尖端涡流尺寸最小化并使其渗透到主流中，这将提高涡轮机效率。 顶端间隙控制机构包括旋转罩的形式和罩的形状，旋转罩上的各种形状和位置的齿，以及固定护罩或套管壁上的各种形状和位置的一个或多个定子齿，其配置提供 可比顶尖间隙控制。 泄漏流量的减少是这些组件如何组装在一起的功能，其限定了旋转护罩和固定护罩之间的间隙通道。
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公开(公告)号：US20110002771A1
公开(公告)日：2011-01-06
申请号：US12825493
申请日：2010-06-29
Applicant: Leo V. LEWIS , Bengt E G BLIDMARK
Inventor： Leo V. LEWIS , Bengt E G BLIDMARK
CPC classification number: F01D11/122 , F01D11/125
Abstract: A system is provided for controlling rotor blade over-tip leakage of a working fluid in rotating machine. The system has a circumferential row of rotor blades, and a circumferential row of seal segments for sealing with the radially outer tips of the rotor blades to reduce over-tip leakage of the working fluid. The seal segments have an inboard abradable layer which is adapted to be abraded by the blade tips to form a wear track for the blade tips. The system further has one or more tip wearing bodies which are adapted to wear down the blade tips. The thickness of the abradable layer and the cold build radial positions of the blade tips, seal segments and tip wearing bodies are arranged such that, during running-in of the machine, a wear track having a uniform radius is formed in the abradable layer by the blade tips, and the tip wearing bodies also wear down the blade tips to provide a uniform blade tip radius.
Abstract translation: 提供一种用于控制旋转机器中工作流体的转子叶片过尖端泄漏的系统。 该系统具有周向排的转子叶片和周向排的密封段，用于与转子叶片的径向外部末端密封以减少工作流体的过度尖端泄漏。 密封段具有内侧可磨损层，其适于被刀片尖端磨损以形成刀片尖端的磨损轨迹。 该系统还具有一个或多个尖端磨损体，其适于磨损刀片尖端。 可磨损层的厚度和叶片尖端，密封段和尖端磨损体的冷构造径向位置被布置成使得在机器进入期间，在可磨损层中形成具有均匀半径的磨损轨迹 刀片尖端和尖端磨损体也磨损刀片尖端以提供均匀的刀尖半径。
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公开(公告)号：US07651317B2
公开(公告)日：2010-01-26
申请号：US11476113
申请日：2006-06-28
Applicant: Gilles Alain Marie Charier , Franck Christian Conan , Thomas Julien Roland Earith , Marc Leandri
Inventor： Gilles Alain Marie Charier , Franck Christian Conan , Thomas Julien Roland Earith , Marc Leandri
IPC: F01D11/14
CPC classification number: F04D29/164
Abstract: A multistage compressor for a turbomachine, in particular an airplane turboprop or turbojet, the compressor comprising a double-walled casing having an inner wall made up of shrouds surrounding respective annular rows of moving blades and annular rows of straightening stator vanes, said shrouds being connected to the outer wall of the casing by independent suspension means enabling the radial clearances between the outer ends of the moving blades and the shrouds of the inner wall of the casing to be adjusted independently from one compression stage to another.
Abstract translation: 一种用于涡轮机，特别是飞机涡轮螺旋桨或涡轮喷气发动机的多级压缩机，该压缩机包括双壁壳体，该双壁壳体具有由围绕相应的环形行动叶片和环形排矫正定子叶片的护罩构成的内壁，所述护罩连接 通过独立的悬挂装置将壳体的外壁附着到壳体的外壁之间的径向间隙，从而能够独立于一个压缩级到另一个压缩级。
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109.发明申请公开(公告)号：US20090317228A1
公开(公告)日：2009-12-24
申请号：US11477294
申请日：2006-06-29
Applicant: Andre Werner
Inventor： Andre Werner
IPC: F01D11/14
CPC classification number: F01D11/22 , F05D2220/3216 , F05D2240/11 , F05D2270/65 , F05D2300/431 , F05D2300/437 , F05D2300/501
Abstract: 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.
Abstract translation: 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：US5997248A
公开(公告)日：1999-12-07
申请号：US204182
申请日：1998-12-03
Applicant: Farshad Ghasripoor , Richard K. Schmid , Mitchell R. Dorfman
Inventor： Farshad Ghasripoor , Richard K. Schmid , Mitchell R. Dorfman
CPC classification number: F01D11/12 , Y10T428/2993
Abstract: A granular composition is applied to tips of rotor blades utilized in a gas turbine engine wherein the blade tips rub against an abradable ceramic layer. Individual grains each have a core of silicon carbide and a layer of aluminum nitride on the core. A layer of a cladding metal may be bonded to the aluminum nitride. The composition also may include particles of cubic boron nitride and/or particles of metal alloy blended with the grains of silicon carbide.
Abstract translation: 将颗粒组合物应用于在燃气涡轮发动机中使用的转子叶片的尖端，其中叶片尖端摩擦耐磨陶瓷层。 单个晶粒各自具有碳化硅芯和芯上的氮化铝层。 包覆金属的层可以结合到氮化铝。 组合物还可以包括与碳化硅颗粒共混的立方氮化硼颗粒和/或金属合金颗粒。
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