公开(公告)号：EP2711300B1

公开(公告)日：2018-07-04

申请号：EP13176380.7

申请日：2013-07-12

申请人： Honeywell International Inc.

发明人： Barber, Tim Daniel ,  Young, Ken ,  Hindle, Timothy

IPC分类号： B64G1/64 ,  B64G1/22 ,  B64G1/28

CPC分类号： B64G1/641 ,  B64G1/283 ,  B64G1/285 ,  B64G1/286 ,  B64G2001/228

摘要： Launch lock assemblies (42) with reduced preload are provided. The launch lock assembly comprises first and second mount pieces (44, 46), a releasable clamp device (64), and a pair of retracting assemblies (66). Each retracting assembly comprises a pair of toothed members having interacting toothed surfaces. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement. When the releasable clamp device is actuated, the first and second mount pieces are released from clamped engagement and one toothed member of each retracting assembly moves in an opposite direction relative to the other one toothed member of the other retracting assembly to define an axial gap on each side of the first mount piece.

公开(公告)号：EP2565394A2

公开(公告)日：2013-03-06

申请号：EP12181901.5

申请日：2012-08-27

申请人： Honeywell International Inc.

发明人： Hindle, Timothy ,  Barber, Tim D. ,  Buchele, Paul

IPC分类号： F01D25/16 ,  F02C7/06 ,  F16F15/02

CPC分类号： F01D25/164 ,  F02C7/06 ,  F16C27/04 ,  F16C2360/23 ,  F16F15/023 ,  Y02T50/671

摘要： Embodiments of a gas turbine engine (20) are provided, as are embodiments of an annular bearing support damper (60, 160) and embodiments of a method for manufacturing an annular bearing support damper. In one embodiment, the gas turbine engine (20) includes an engine housing (140) and a rotor assembly disposed within the engine housing (140). A rotor bearing (56) supports the rotor assembly within the engine housing (140), and an annular bearing support damper (60, 160) is positioned between the rotor bearing (56) and the engine housing (14). The support damper (60, 160) includes an annular housing assembly (62, 168) having a damping fluid annulus (94, 182). An array of circumferentially-spaced damper pistons (90, 172) is movably coupled to the annular housing assembly (62, 168) and fluidly communicates with the damping fluid annulus (94, 182). The damper pistons (90, 172) are fixedly coupled to the rotor bearing (56) and move in conjunction therewith to force the flow of damping fluid around the annulus (94, 182) during engine operation to reduce the transmissions of vibrations to the engine housing (140).

摘要翻译： 与环形轴承支撑阻尼器（60,160）的实施例以及用于制造环形轴承支撑阻尼器的方法的实施例一样，提供燃气涡轮发动机（20）的实施例。 在一个实施例中，燃气涡轮发动机（20）包括发动机壳体（140）和设置在发动机壳体（140）内的转子组件。 转子轴承（56）支撑在发动机壳体（140）内的转子组件，并且环形轴承支撑阻尼器（60,160）定位在转子轴承（56）和发动机壳体（14）之间。 支撑阻尼器（60,160）包括具有阻尼流体环（94,182）的环形壳体组件（62,168）。 周向间隔的阻尼活塞（90,172）的阵列可移动地联接到环形壳体组件（62,168）并且与阻尼流体环（94,182）流体连通。 阻尼器活塞（90,172）固定地联接到转子轴承（56）并与其一起运动，以在发动机操作期间迫使阻尼流体在环空（94,182）周围的流动，以减少对发动机的振动传递 住房（140）。

公开(公告)号：EP2180203A2

公开(公告)日：2010-04-28

申请号：EP09173459.0

申请日：2009-10-19

申请人： Honeywell International Inc.

发明人： Boyd, James R. ,  Ruebsamen, Dale Thomas ,  Hindle, Timothy

IPC分类号： F16F1/38 ,  F16F3/093

CPC分类号： F16F3/0935 ,  F16F1/38

摘要： Vibration isolators (100) are provided that include a shaft (102), a first bushing (124), a second bushing (164), a first outer annular member (126), a second outer angular member (166), a first elastomeric member (128), a second elastomeric member (168), and a shim (107). The first elastomeric member (128) is adapted to provide a first stiffness for damping a first vibration, and the second elastomeric member (168) is adapted to provide a second stiffness for damping a second vibration, the second stiffness being greater than the first stiffness.

公开(公告)号：EP2565394B1

公开(公告)日：2019-04-03

申请号：EP12181901.5

申请日：2012-08-27

申请人： Honeywell International Inc.

发明人： Hindle, Timothy ,  Barber, Tim D. ,  Buchele, Paul

IPC分类号： F01D25/16 ,  F02C7/06 ,  F16F15/02 ,  F16C27/04 ,  F16F15/023

公开(公告)号：EP2180203B1

公开(公告)日：2018-04-11

申请号：EP09173459.0

申请日：2009-10-19

申请人： Honeywell International Inc.

发明人： Boyd, James R. ,  Ruebsamen, Dale Thomas ,  Hindle, Timothy

IPC分类号： F16F1/38 ,  F16F3/093

CPC分类号： F16F3/0935 ,  F16F1/38

摘要： Vibration isolators (100) are provided that include a shaft (102), a first bushing (124), a second bushing (164), a first outer annular member (126), a second outer angular member (166), a first elastomeric member (128), a second elastomeric member (168), and a shim (107). The first elastomeric member (128) is adapted to provide a first stiffness for damping a first vibration, and the second elastomeric member (168) is adapted to provide a second stiffness for damping a second vibration, the second stiffness being greater than the first stiffness.

公开(公告)号：EP2565394A3

公开(公告)日：2018-01-10

申请号：EP12181901.5

申请日：2012-08-27

申请人： Honeywell International Inc.

发明人： Hindle, Timothy ,  Barber, Tim D. ,  Buchele, Paul

IPC分类号： F01D25/16 ,  F02C7/06 ,  F16F15/02 ,  F16C27/04 ,  F16F15/023

CPC分类号： F01D25/164 ,  F02C7/06 ,  F16C27/04 ,  F16C2360/23 ,  F16F15/023 ,  Y02T50/671

摘要： Embodiments of a gas turbine engine (20) are provided, as are embodiments of an annular bearing support damper (60, 160) and embodiments of a method for manufacturing an annular bearing support damper. In one embodiment, the gas turbine engine (20) includes an engine housing (140) and a rotor assembly disposed within the engine housing (140). A rotor bearing (56) supports the rotor assembly within the engine housing (140), and an annular bearing support damper (60, 160) is positioned between the rotor bearing (56) and the engine housing (14). The support damper (60, 160) includes an annular housing assembly (62, 168) having a damping fluid annulus (94, 182). An array of circumferentially-spaced damper pistons (90, 172) is movably coupled to the annular housing assembly (62, 168) and fluidly communicates with the damping fluid annulus (94, 182). The damper pistons (90, 172) are fixedly coupled to the rotor bearing (56) and move in conjunction therewith to force the flow of damping fluid around the annulus (94, 182) during engine operation to reduce the transmissions of vibrations to the engine housing (140).

摘要翻译： 提供了燃气涡轮发动机（20）的实施例，环形轴承支撑阻尼器（60,160）的实施例以及用于制造环形轴承支撑阻尼器的方法的实施例。 在一个实施例中，燃气涡轮发动机（20）包括发动机壳体（140）和布置在发动机壳体（140）内的转子组件。 转子轴承（56）将转子组件支撑在发动机壳体（140）内，并且环形轴承支撑阻尼器（60,160）定位在转子轴承（56）和发动机壳体（14）之间。 支撑阻尼器（60,160）包括具有阻尼流体环（94,182）的环形壳体组件（62,168）。 一组周向间隔的阻尼器活塞（90,172）可移动地联接到环形壳体组件（62,168）并且与阻尼流体环形空间（94,182）流体连通。 阻尼活塞（90,172）固定地联接到转子轴承（56）并且与其一起移动以在发动机操作期间迫使阻尼流体围绕环空（94,182）流动以减少振动传递到发动机 住房（140）。

公开(公告)号：EP2589834B1

公开(公告)日：2020-01-01

申请号：EP12182279.5

申请日：2012-08-29

申请人： Honeywell International Inc.

发明人： Young, Ken ,  Hindle, Timothy ,  Barber, Tim Daniel

IPC分类号： F16M11/20 ,  F16M11/18 ,  F16M11/14 ,  F16M11/12 ,  F16C11/10 ,  F16F9/54 ,  F16F15/04

公开(公告)号：EP2905504A2

公开(公告)日：2015-08-12

申请号：EP15152949.2

申请日：2015-01-28

申请人： Honeywell International Inc.

发明人： Hindle, Timothy ,  Barber, Tim Daniel ,  Young, Ken

IPC分类号： F16F9/36 ,  F16F9/48 ,  F16F9/18

CPC分类号： F16F9/361 ,  F16F1/028 ,  F16F9/061 ,  F16F9/18 ,  F16F9/19 ,  F16F9/3221 ,  F16F9/3235 ,  F16F9/54

摘要： Embodiments of an isolator (10) are provided. In one embodiment, the isolator includes a damper housing (22) having a radially-extending partition wall (38) through which a central opening (30) is formed. First and second hydraulic chambers (56, 58) are located on opposing sides of the radially-extending partition wall and may be filled with a damping fluid. At least one restricted orifice (60) is formed through the damper housing and fluidly couples the first and second hydraulic chambers. The isolator further includes a damper piston (20), which extends through the central opening, which is exposed to the damping fluid when the first and second hydraulic chambers are filled therewith, and which is configured to translate along a working axis (12) with respect to the damper housing during operation of the isolator.

摘要翻译： 提供的绝缘体（10）的实施例。 在一个中，实施例绝缘体包括具有穿过其中的中央开口（30）形成一径向延伸的分隔壁（38）的阻尼器壳体（22）。 第一和第二液压室（56，58）位于相对的径向延伸的分隔壁的两侧，并且可填充有阻尼流体。 至少一个限流孔（60）通过阻尼器壳体和流体地耦合所述第一和第二液压腔形成。 所述绝缘体还包括阻尼器活塞（20），通过中央开口延伸，所有这一切都被暴露于阻尼流体。当第一和第二液压室被填充在那里，所有这一切都被配置为沿着一个工作轴线（12）与翻译 隔离的手术过程中尊重减震器壳体。

公开(公告)号：EP2562367A3

公开(公告)日：2015-06-17

申请号：EP12181431.3

申请日：2012-08-22

申请人： Honeywell International Inc.

发明人： Hindle, Timothy ,  Hadden, Steven ,  Davis, Torey

IPC分类号： F01D25/04 ,  F16F15/02 ,  F16F15/023 ,  F01D5/10

CPC分类号： F01D25/04 ,  F01D5/10 ,  F05D2250/41 ,  F05D2260/96 ,  F16F15/022 ,  F16F15/023 ,  Y02T50/671 ,  Y10T29/4932

摘要： Gas turbine engine (18), broadband damping systems (20), and methods for producing broadband-damped gas turbine engine are provided. In one embodiment, the gas turbine engine (18) includes an engine case (38), a rotor assembly (66) mounted within the engine case (38) for rotation about a rotational axis, and a broadband damping system (20) disposed between the rotor assembly (66) and the engine case (38). The broadband damping system (20) includes a first set of three parameter axial dampers (60, 61, 62) angularly spaced around the rotational axis, and a second set of three parameter axial dampers (63, 64, 65) angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers (60, 61, 62). The first and second sets of three parameter axial dampers (60, 61, 62, 63, 64, 65) are tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system (20) during operation of the gas turbine engine (18).

公开(公告)号：EP2634095A2

公开(公告)日：2013-09-04

申请号：EP12198245.8

申请日：2012-12-19

申请人： Honeywell International Inc.

发明人： Barber, Tim Daniel ,  Hindle, Timothy ,  Young, Ken ,  Davis, Torey

IPC分类号： B64G1/00 ,  B64F1/04

CPC分类号： B64G1/641 ,  B64G1/286 ,  B64G2001/228

摘要： Embodiments of a launch lock assembly (34, 42) are provided, as are embodiments of a spacecraft isolation system (20) including one or more launch lock assemblies (34, 42). In one embodiment, the launch lock assembly (34, 42) includes first and second mount pieces (36, 38, 44, 46), a releasable clamp device (64), and an axial gap amplification device (66). The releasable clamp device (64) normally maintains the first and second mount pieces (36, 38, 44, 46) in clamped engagement; and, when actuated, releases the first and second mount pieces (36, 38, 44, 46) from clamped engagement to allow relative axial motion therebetween. The axial gap amplification device (66) normally residing in a blocking position wherein the gap amplification device (66) obstructs relative axial motion between the first and second mount pieces (36, 38, 44, 46). The axial gap amplification device (66) moves into a non-blocking position when the first and second mount pieces (36, 38, 44, 46) are released from clamped engagement to increase the range of axial motion between the first and second mount pieces (36, 38, 44, 46).

摘要翻译： 设置有推出锁组件（34，42）的实施例中，因为是一个宇宙飞船隔离系统（20）包括一个或多个发射锁组件（34，42）的实施例。 在一个中，实施例推出锁组件（34，42）包括第一和第二安装件（36，38，44，46），可释放的夹紧装置（64），并在轴向间隙放大装置（66）。 可释放的夹紧装置（64）通常保持第一和第二安装在夹紧卡合片（36，38，44，46）; 并且，当致动时，释放第一和第二安装夹紧从卡合片（36，38，44，46），以允许相对轴向运动之间存在。 所述的轴向间隙放大装置（66）通常驻留在worin的间隙放大装置（66）的阻挡位置阻碍所述第一和第二安装件（36，38，44，46）之间的相对轴向运动。 所述的轴向间隙放大装置（66）移动到非阻挡位置。当第一和第二安装件（36，38，44，46）从夹紧的接合释放，以增加轴向运动的范围内的第之间和第二安装件 （36，38，44，46）。