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公开(公告)号：US08840114B2
公开(公告)日：2014-09-23
申请号：US13420100
申请日：2012-03-14
IPC分类号： F16J15/447 , F01D25/18 , F01D11/04
CPC分类号： F01D25/183 , F01D11/04 , F05D2240/55
摘要： An assembly, for example in a gas turbine engine, includes a rotatable component supported by a bearing in a support structure. A sealing arrangement includes a non-rotating sealing ring which makes sealing contact with sealing features on the rotatable component. The non-rotating sealing ring is radially displaceable with respect to the support structure by means of ribs which engage axially facing support faces of the support structure. The non-rotating sealing ring is radially located by an outer, non-rotating, race of the bearing, by means of a locating surface on a locating body of the non-rotating sealing ring. As a result of this arrangement, the running clearance at the sealing arrangement can be maintained, despite radial displacement of the rotatable component with respect to the support structure, and despite thermal and mechanical deflections of the support structure.
摘要翻译： 例如在燃气涡轮发动机中的组件包括由支撑结构中的轴承支撑的可旋转部件。 密封装置包括不可旋转的密封环，其与可旋转部件上的密封特征密封接触。 非旋转密封环通过与支承结构的轴向面对的支撑面接合的肋而可相对于支撑结构径向移动。 非旋转密封环通过非旋转密封环的定位体上的定位表面径向定位在轴承的外部非旋转轴承座上。 作为这种布置的结果，尽管可旋转部件相对于支撑结构的径向位移，并且尽管支撑结构的热和机械偏转，也可以保持密封装置处的运行间隙。
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公开(公告)号：US08511974B2
公开(公告)日：2013-08-20
申请号：US12760001
申请日：2010-04-14
申请人： Ian A. Hood , Kenneth F. Udall
发明人： Ian A. Hood , Kenneth F. Udall
IPC分类号： F01D17/16
摘要： A control mechanism is provided for moving at least two components of a gas turbine engine. The control mechanism comprises a movable actuation rod and a first linkage arrangement which includes a first bell crank connecting the actuation rod to a first component. Movement of the actuation rod produces an output motion of the first bell crank which in turn drives movement of the first component. The control mechanism further comprises a second linkage arrangement which includes a second bell crank connecting the actuation rod to a second component. Movement of the actuation rod produces an output motion of the second bell crank which in turn drives movement of the second component. The first and the second linkage arrangements are configure so that over a predetermined range of movement of the actuation rod the first component is moved which the second component is not moved.
摘要翻译： 提供了用于移动燃气涡轮发动机的至少两个部件的控制机构。 控制机构包括可动致动杆和第一连杆装置，该第一联动装置包括将致动杆连接到第一部件的第一曲柄曲柄。 致动杆的移动产生第一钟形曲柄的输出运动，而后者又驱动第一部件的运动。 控制机构还包括第二连杆装置，其包括将致动杆连接到第二部件的第二钟形曲柄。 致动杆的移动产生第二钟形曲柄的输出运动，其又驱动第二部件的运动。 第一和第二连杆装置被构造成使得在致动杆的预定移动范围内移动第一部件，而第二部件不移动。
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公开(公告)号：US08303187B2
公开(公告)日：2012-11-06
申请号：US12588441
申请日：2009-10-15
申请人： Kenneth F. Udall , Alan R. Maguire
发明人： Kenneth F. Udall , Alan R. Maguire
CPC分类号： F01D25/164 , F16C19/54 , F16C27/04 , F16C33/58 , F16C41/02 , F16C2360/23
摘要： In order to accommodate loading in a number of situations such as with regard to thrusts in a gas turbine engine it is known to provide thrust bearings. These thrust bearings can be large and may be difficult to accommodate. By providing a duplex or multiplex thrust bearing which may be of increased axial length but reduced radial width easier accommodation may be achieved. By providing a thrust element 27 which compromises a balance beam from which extend elastic hinges to a mounting to a fixed bearing frame and ends of bearing races 21, 22 an appropriate thrust response can be achieved dependent upon bearing loads presented through bearing elements 23, 24. By rotation of the balance beam and flexing of the elastic hinges 30, 31, 32 an appropriate bearing load share is achieved.
摘要翻译： 为了适应诸如关于燃气涡轮发动机中的推力的若干情况的负载，已知提供止推轴承。 这些推力轴承可能很大，可能难以适应。 通过提供可以增加轴向长度但减小径向宽度的双工或多重推力轴承，可以实现更容易的调节。 通过提供推力元件27，其抵消平衡梁，平衡梁从其延伸弹性铰链到安装件到固定的轴承架和轴承座圈21,22的端部，可以根据通过轴承元件23,24呈现的轴承负载来实现适当的推力响应 通过平衡梁的旋转和弹性铰链30,31,32的弯曲，实现了适当的轴承负载份额。
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公开(公告)号：US20100284788A1
公开(公告)日：2010-11-11
申请号：US12768041
申请日：2010-04-27
IPC分类号： F02C7/24
CPC分类号： F01D21/045 , F01D5/16 , F01D25/06
摘要： A duct wall of a fan casing of a gas turbine engine comprises an intake section and a containment casing, which are interconnected by bolts at flanges. An acoustic flutter damper is provided between the flanges to reduce or eliminate flutter arising in blades of the fan at certain important operating conditions. The damper provides flexibility at the connection between the intake section and the containment casing so that, in the event of detachment of a blade or a bladed fragment, the resulting deflection wave in the containment casing can be accommodated by displacement and/or deformation of the acoustic flutter damper, reducing the risk that the bolts will shear to allow the intake section and the containment casing to become detached from each other. The acoustic flutter damper may comprise a circumferential array of separate segments.
摘要翻译： 燃气涡轮发动机的风扇壳体的导管壁包括通过螺栓在凸缘处互连的进气部分和容纳壳体。 在凸缘之间提供声波阻尼器以减少或消除在某些重要操作条件下风扇叶片中产生的颤动。 阻尼器在进气部分和收容壳体之间的连接处提供了灵活性，使得在叶片或叶片碎片脱离的情况下，容纳壳体中产生的偏转波可以通过位移和/或变形 声波阻尼器，减少了螺栓剪切的风险，使进气段和密封套彼此脱离。 声波阻尼器可以包括分开的段的圆周阵列。
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公开(公告)号：US20100278639A1
公开(公告)日：2010-11-04
申请号：US12760001
申请日：2010-04-14
申请人： Ian A. HOOD , Kenneth F. Udall
发明人： Ian A. HOOD , Kenneth F. Udall
IPC分类号： F01D17/16
摘要： A control mechanism is provided for moving at least two components of a gas turbine engine. The control mechanism comprises a moveable actuation rod. The control mechanism further comprises a first linkage arrangement which includes a first bell crank and which operatively connects the actuation rod to a first component of the gas turbine engine. Movement of the actuation rod produces an output motion of the first bell crank which in turn drives movement of the first component. The control mechanism further comprises a second linkage arrangement which includes a second bell crank and which operatively connects the actuation rod to a second component of the gas turbine engine. Movement of the actuation rod produces an output motion of the second bell crank which in turn drives movement of the second component. The first linkage arrangement and the second linkage arrangement are configured so that over a predetermined range of movement of the actuation rod the first component is moved by the first bell crank while the second component is not moved by the second bell crank.
摘要翻译： 提供了用于移动燃气涡轮发动机的至少两个部件的控制机构。 控制机构包括可移动致动杆。 控制机构还包括第一联动装置，其包括第一钟形曲柄并将致动杆可操作地连接到燃气涡轮发动机的第一部件。 致动杆的移动产生第一钟形曲柄的输出运动，而后者又驱动第一部件的运动。 控制机构还包括第二联动装置，其包括第二钟形曲柄并将致动杆可操作地连接到燃气涡轮发动机的第二部件。 致动杆的移动产生第二钟形曲柄的输出运动，其又驱动第二部件的运动。 第一联动装置和第二联动装置构造成使得在致动杆的预定的运动范围内，第一部件通过第一钟形曲柄移动，而第二部件不被第二曲柄运动。
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公开(公告)号：US20100251688A1
公开(公告)日：2010-10-07
申请号：US11651553
申请日：2007-01-10
申请人： Kenneth F. Udall
发明人： Kenneth F. Udall
CPC分类号： F01D21/045 , F05D2250/61 , F05D2300/433 , F05D2300/603
摘要： A containment system for a gas turbine engine comprises a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine. The force absorbing arrangement circumferentially surrounds a major proportion of the axial length of the engine.
摘要翻译： 用于燃气涡轮发动机的容纳系统包括用于吸收由发动机的故障部件的喷射部分施加在其上的力的力吸收装置。 力吸收装置周向地围绕发动机轴向长度的主要部分。
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公开(公告)号：US07654075B2
公开(公告)日：2010-02-02
申请号：US11520671
申请日：2006-09-14
申请人： Kenneth F. Udall
发明人： Kenneth F. Udall
IPC分类号： F02K3/04
CPC分类号： F01D25/246 , F01D9/041 , F01D9/042 , F01D25/162 , F01D25/28 , F04D29/526 , F04D29/542 , F04D29/644 , F05D2240/12 , Y02T50/673
摘要： A static structure is provided such as that used as an engine structure 30 within a gas turbine engine. A structure 30 comprises a hub or core 33 with a concentric ring or casing 32. The hub 33 and casing 32 are secured together through spoke or vane elements 31 which are sloped axially and tangentially relative to a principal axis X-X. In such circumstances any roll torque reaction caused by differentially rotating hub and ring motions is retained by the tangential inclination of the spokes or vanes whilst axial sloping of these spokes or vanes 31 and axially sloping of the struts 34 creates bracing in the direction of the principal axis X-X. In such circumstances essentially robust triangles are formed radially and longitudinally respectively each comprising spokes or vanes 31 and struts 34 secured at axially spaced locations on the hub or core 33.
摘要翻译： 提供了诸如在燃气涡轮发动机内用作发动机结构30的静态结构。 结构30包括具有同心环或壳体32的毂或芯33.毂33和壳体32通过相对于主轴线X-X轴向和切向倾斜的轮辐或叶片元件31固定在一起。 在这种情况下，通过轮毂和环运动的差异转动引起的任何滚动扭矩反作用力由轮辐或叶片的切向倾斜保持，同时这些轮辐或叶片31的轴向倾斜和支柱34的轴向倾斜在主体的方向上产生支撑 轴XX。 在这种情况下，基本上坚固的三角形分别径向和纵向地形成，每个包括辐条或叶片31和固定在轮毂或芯33上轴向间隔开的位置的支柱34。
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8.发明授权Mounting for coupling a turbofan gas turbine engine to an aircraft structure 失效用于将涡轮风扇燃气涡轮发动机耦合到飞行器结构的安装
公开(公告)号：US5746391A
公开(公告)日：1998-05-05
申请号：US625356
申请日：1996-04-01
CPC分类号： B64D27/18 , B64D2027/264 , Y02T50/44
摘要： A mounting for connecting a turbofan gas turbine engine to an aircraft structure comprises three mounting points at the vertices of a triangle on the aircraft structure and three mounting points on the fan casing of the turbofan gas turbine engine. The first mounting point on the aircraft structure is connected to all of the three mounting points on the fan casing by three links. The second mounting point on the aircraft structure is connected to the second mounting point and the third mounting point on the fan casing by two links. The third mounting point on the aircraft structure is connected to the second mounting point and the third mounting point by two links. The links provide an open spaceframe which defines the structure of a pylon. The mounting has reduced weight compared to conventional mountings and is cheaper to manufacture.
摘要翻译： 用于将涡轮风扇燃气涡轮发动机连接到飞行器结构的安装件包括在飞行器结构上的三角形顶点处的三个安装点和涡轮风扇燃气涡轮发动机的风扇壳体上的三个安装点。 飞机结构上的第一个安装点通过三个连杆连接到风扇外壳上的所有三个安装点。 飞机结构上的第二安装点通过两个连杆连接到风扇壳体上的第二安装点和第三安装点。 飞机结构上的第三安装点通过两个连杆连接到第二安装点和第三安装点。 连杆提供了一个定义塔架结构的开放空间框架。 与常规安装相比，安装件具有减轻的重量并且制造成本更低。
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公开(公告)号：US08985946B2
公开(公告)日：2015-03-24
申请号：US13483461
申请日：2012-05-30
CPC分类号： F01D5/30 , B64C11/306 , B64D2027/005 , F01D7/00 , F02C6/206 , F02K3/072 , Y02T50/66
摘要： A mounting system for mounting a blade to a rotor body includes a pitch control mechanism including an anchor and a pitch change rod extending radially outwardly from the anchor to join to a base of the blade. The anchor and the rod are rotatable about the longitudinal axis of the rod to vary the blade pitch. The pitch control mechanism further includes a torque-transmitting formation between the blade and the anchor such that pitch-varying torque can be transmitted to the blade through the torque-transmitting formation while allowing relative radial movement between the blade and the anchor. The system includes a primary bearing formation, which transmits blade centrifugal loads to the rotor body while accommodating variation of the blade pitch, and secondary bearing formation, which transmits pitch change mechanism centrifugal loads to the rotor body while accommodating rotation of the anchor and the rod during variation of the blade pitch.
摘要翻译： 用于将叶片安装到转子主体的安装系统包括俯仰控制机构，其包括锚固件和从锚固件径向向外延伸以连接到叶片的基部的变桨杆。 锚杆和杆可围绕杆的纵向轴线旋转以改变叶片间距。 俯仰控制机构还包括在叶片和锚之间的转矩传递结构，使得桨距变化转矩可以通过扭矩传递构件传递到叶片，同时允许叶片和锚之间的相对径向移动。 该系统包括主轴承结构，其将叶片离心载荷传递到转子本体同时容纳叶片间距的变化，以及次级轴承形成，其将桨距变化机构的离心载荷传递到转子本体，同时容纳锚和杆的旋转 在叶片间距的变化期间。
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公开(公告)号：US20100284790A1
公开(公告)日：2010-11-11
申请号：US12768316
申请日：2010-04-27
IPC分类号： F04D29/66
CPC分类号： F01D21/045 , F01D5/16 , F01D25/06
摘要： A gas turbine engine fan casing duct wall comprises an intake section and a containment casing, provided respectively with flanges. An acoustic flutter damper is secured between the flanges. The acoustic flutter damper has a skin accommodating an internal structure that dampens fan blade flutter. The skin is secured to the flanges at separate locations. In normal operation of the engine, the internal structure is sufficiently robust to support loads transmitted through the acoustic flutter damper between the intake section and the containment casing. If a blade or blade fragment detaches, the resulting deflection wave in the containment case ruptures the internal structure, and the load path between the intake section and the containment casing passes along the skin, which consequently maintains the connection between the intake duct and the containment casing, while permitting substantial radial deflection of the containment casing relative to the intake section.
摘要翻译： 燃气涡轮发动机风扇壳体管道壁包括分别设置有凸缘的进气部分和容纳壳体。 声波阻尼器固定在凸缘之间。 声波阻尼器具有容纳内部结构的皮肤，其阻尼风扇叶片的颤动。 皮肤在不同的位置固定在法兰上。 在发动机的正常操作中，内部结构足够坚固以支撑通过吸气部分和容纳壳体之间的声波阻尼器传递的载荷。 如果叶片或叶片碎片分离，则容纳壳体中产生的偏转波使内部结构破裂，并且进气部分和收容壳体之间的载荷路径沿着皮肤通过，从而保持进气管道与容纳物之间的连接 同时允许容纳壳体相对于进气部分的大量径向偏转。
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