公开(公告)号：US09046001B2

公开(公告)日：2015-06-02

申请号：US13220081

申请日：2011-08-29

申请人： Timothy Hindle ,  Tim Daniel Barber ,  Paul Buchele

发明人： Timothy Hindle ,  Tim Daniel Barber ,  Paul Buchele

IPC分类号： F01D25/16 ,  F02C7/06 ,  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 are provided, as are embodiments of an annular bearing support damper and embodiments of a method for manufacturing an annular bearing support damper. In one embodiment, the gas turbine engine includes engine housing and a rotor assembly disposed within the engine housing. A rotor bearing supports the rotor assembly within the engine housing, and an annular bearing support damper is positioned between the rotor bearing and the engine housing. The support damper includes an annular housing assembly having a damping fluid annulus. An array of circumferentially-spaced damper pistons is movably coupled to the annular housing assembly and fluidly communicates with the damping fluid annulus. The damper pistons are fixedly coupled to the rotor bearing and moves in conjunction therewith to force the flow of damping fluid around the annulus during engine operation to reduce the transmissions of vibrations to the engine housing.

摘要翻译： 提供燃气涡轮发动机的实施例，如环形轴承支撑阻尼器的实施例和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，燃气涡轮发动机包括发动机壳体和设置在发动机壳体内的转子组件。 转子轴承支撑发动机壳体内的转子组件，并且环形轴承支撑阻尼器定位在转子轴承和发动机壳体之间。 支撑阻尼器包括具有阻尼流体环的环形壳体组件。 周向间隔的阻尼活塞的阵列可移动地联接到环形壳体组件并且与阻尼流体环空间流体连通。 减震器活塞固定地联接到转子轴承并与其一起运动，以在发动机操作期间迫使阻尼流体在环空周围流动，以减少发动机壳体的振动传递。

公开(公告)号：US08708322B2

公开(公告)日：2014-04-29

申请号：US12940771

申请日：2010-11-05

申请人： Ken Young ,  Timothy Hindle

发明人： Ken Young ,  Timothy Hindle

IPC分类号： B25B1/00

CPC分类号： B64G1/641

摘要： A payload launch lock mechanism includes a base, a preload clamp, a fastener, and a shape memory alloy (SMA) actuator. The preload clamp is configured to releasibly restrain a payload. The fastener extends, along an axis, through the preload clamp and into the base, and supplies a force to the preload clamp sufficient to restrain the payload. The SMA actuator is disposed between the base and the clamp. The SMA actuator is adapted to receive electrical current and is configured, upon receipt of the electrical current, to supply a force that causes the fastener to elongate without fracturing. The preload clamp, in response to the fastener elongation, either rotates or pivots to thereby release the payload.

摘要翻译： 有效载荷发射锁定机构包括基座，预载夹具，紧固件和形状记忆合金（SMA）致动器。 预载夹具被配置为可释放地约束有效载荷。 紧固件沿着轴线延伸穿过预压夹具并进入基座，并且向预载夹具提供足以约束有效载荷的力。 SMA致动器设置在基座和夹具之间。 SMA致动器适于接收电流，并且在接收到电流时被配置为提供使紧固件伸长而不断裂的力。 响应于紧固件伸长，预紧夹具旋转或枢转，从而释放有效载荷。

公开(公告)号：US20130112843A1

公开(公告)日：2013-05-09

申请号：US13289815

申请日：2011-11-04

申请人： Ken Young ,  Timothy Hindle ,  Tim Daniel Barber

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

IPC分类号： F16F15/00 ,  F16C11/06 ,  F16M13/00

CPC分类号： F16F15/04 ,  F16C11/106 ,  F16C2326/43 ,  F16C2361/00 ,  F16F9/54 ,  F16M11/121 ,  F16M11/14 ,  F16M11/18 ,  F16M11/2078 ,  Y10T403/32598

摘要： Mounting systems for structural members, fastening assemblies thereof, and vibration isolation systems including the same are provided. Mounting systems comprise a pair of mounting brackets, each clamped against a fastening assembly forming a mounting assembly. Fastening assemblies comprise a spherical rod end comprising a spherical member having a through opening and an integrally threaded shaft, first and second seating members on opposite sides of the spherical member and each having a through opening that is substantially coaxial with the spherical member through opening, and a partially threaded fastener that threadably engages each mounting bracket forming the mounting assembly. Structural members have axial end portions, each releasably coupled to a mounting bracket by the integrally threaded shaft. Axial end portions are threaded in opposite directions for permitting structural member rotation to adjust a length thereof to a substantially zero strain position. Structural members may be vibration isolator struts in vibration isolation systems.

摘要翻译： 提供了用于结构构件的安装系统，其紧固组件以及包括其的隔振系统。 安装系统包括一对安装支架，每个安装支架夹紧在形成安装组件的紧固组件上。 紧固组件包括球形杆端部，其包括具有通孔和一体螺纹轴的球形构件，在球形构件的相对侧上的第一和第二座构件，并且每个具有通孔，该通孔与球形构件通过开口基本上同轴， 以及与形成安装组件的每个安装支架螺纹接合的部分螺纹紧固件。 结构构件具有轴向端部，每个端部通过一体的螺纹轴可释放地联接到安装支架。 轴向端部沿相反的方向旋拧，以允许结构构件旋转以将其长度调节到基本上为零的应变位置。 结构构件可以是隔振系统中的隔振支柱。

公开(公告)号：US08327985B2

公开(公告)日：2012-12-11

申请号：US12489128

申请日：2009-06-22

申请人： James Boyd ,  Timothy Hindle ,  Dale Thomas Ruebsamen

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

IPC分类号： F16F7/10

CPC分类号： F16F13/005 ,  F16F9/16 ,  F16F9/22 ,  F16F15/022 ,  F16F15/023 ,  F16F2230/105

摘要： A vibration isolating system is disclosed. The vibration isolating system comprises a passive mechanical system comprising a damping assembly, a first resilient member coupled in series with the damping assembly, and a second resilient member coupled in parallel with the series combination of the damping assembly and the first resilient member. The vibration isolating system further comprises a support member coupled in series with the passive mechanical system, a viscoelastic mount coupled to the support member, and a motion limiter coupled to the support member such that the passive mechanical system transmits a force to the support member when the passive mechanical undergoes longitudinal displacement greater than a predetermined displacement.

摘要翻译： 公开了一种隔振系统。 隔振系统包括被动机械系统，该被动机械系统包括阻尼组件，与阻尼组件串联联接的第一弹性构件以及与阻尼组件和第一弹性构件的串联组合并联的第二弹性构件。 隔振系统还包括与被动机械系统串联联接的支撑构件，耦合到支撑构件的粘弹性安装件，以及耦合到支撑构件的运动限制器，使得被动机械系统当向 被动机械经历大于预定位移的纵向位移。

公开(公告)号：US20100101903A1

公开(公告)日：2010-04-29

申请号：US12256909

申请日：2008-10-23

申请人： James R. Boyd ,  Dale Thomas Ruebsamen ,  Timothy Hindle

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

IPC分类号： F16F9/30

CPC分类号： F16F3/0935 ,  F16F1/38

摘要： Vibration isolators are provided that include a shaft, a first bushing, a second bushing, a first outer annular member, a second outer annular member, a first elastomeric member, a second elastomeric member, and a shim. The first elastomeric member is adapted to provide a first stiffness for damping a first vibration, and the second elastomeric member is adapted to provide a second stiffness for damping a second vibration, the second stiffness being greater than the first stiffness.

摘要翻译： 提供了隔振器，其包括轴，第一衬套，第二衬套，第一外部环形构件，第二外部环形构件，第一弹性构件，第二弹性体构件和垫片。 第一弹性体构件适于提供用于阻尼第一振动的第一刚度，并且第二弹性构件适于提供用于阻尼第二振动的第二刚度，第二刚度大于第一刚度。

公开(公告)号：US20130051981A1

公开(公告)日：2013-02-28

申请号：US13219287

申请日：2011-08-26

申请人： Timothy Hindle ,  Steven Hadden ,  Torey Davis

发明人： Timothy Hindle ,  Steven Hadden ,  Torey Davis

IPC分类号： F01D25/04 ,  B23P11/00

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

摘要翻译： 提供燃气涡轮发动机，宽带阻尼系统以及生产宽带阻尼式燃气轮机的方法。 在一个实施例中，燃气涡轮发动机包括发动机壳体，安装在发动机壳体内用于围绕旋转轴线旋转的转子组件以及设置在转子组件和发动机壳体之间的宽带阻尼系统。 宽带阻尼系统包括围绕旋转轴线成角度地间隔开的第一组三个参数轴向阻尼器，以及第二组三个参数轴向阻尼器，其围绕旋转轴线成角度地间隔开并与第一组三个参数轴向阻尼器并联。 第一组和第二组三参数轴向阻尼器被调谐以在不同的旋转频率处提供峰值阻尼，以增加燃气涡轮发动机运行期间宽带阻尼系统的阻尼带宽。

公开(公告)号：US07967282B2

公开(公告)日：2011-06-28

申请号：US12256909

申请日：2008-10-23

申请人： James R. Boyd ,  Dale Thomas Ruebsamen ,  Timothy Hindle

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

IPC分类号： F16F1/38

CPC分类号： F16F3/0935 ,  F16F1/38

摘要： Vibration isolators are provided that include a shaft, a first bushing, a second bushing, a first outer annular member, a second outer annular member, a first elastomeric member, a second elastomeric member, and a shim. The first elastomeric member is adapted to provide a first stiffness for damping a first vibration, and the second elastomeric member is adapted to provide a second stiffness for damping a second vibration, the second stiffness being greater than the first stiffness.

摘要翻译： 提供了隔振器，其包括轴，第一衬套，第二衬套，第一外部环形构件，第二外部环形构件，第一弹性构件，第二弹性体构件和垫片。 第一弹性体构件适于提供用于阻尼第一振动的第一刚度，并且第二弹性构件适于提供用于阻尼第二振动的第二刚度，第二刚度大于第一刚度。

公开(公告)号：US08770513B2

公开(公告)日：2014-07-08

申请号：US13308178

申请日：2011-11-30

申请人： Tim Daniel Barber ,  Timothy Hindle ,  Steven Hadden

发明人： Tim Daniel Barber ,  Timothy Hindle ,  Steven Hadden

IPC分类号： B64D27/00

CPC分类号： B64D27/26 ,  B64D2027/266 ,  F16F1/10 ,  F16F3/02

摘要： Resilient aircraft engine mounts and mounting systems including the same are provided. A resilient aircraft engine mount comprises a base and a pair of opposed spiral springs in parallel forming a clevis with the base. A first spiral spring of the pair of opposed spiral springs has a first center opening extending therethrough. A second spiral spring of the pair of opposed spiral springs has a second center opening extending therethrough that is concentric with the first center opening for accepting a clevis pin. First and second spiral springs are each comprised of a rectangular cross section beam. The resilient aircraft engine mount is tunable in three translational axes to support three degrees of freedom vibration isolation. Two or more resilient aircraft engine mounts provide six degrees of freedom vibration isolation. Resilient aircraft engine mounts attach the aircraft engine to a pylon structure and help isolate vibratory forces.

摘要翻译： 提供弹性飞机发动机支架和包括其的安装系统。 弹性飞机发动机支架包括基座和一对相对的螺旋弹簧，平行地形成与基座的U形夹。 一对相对的螺旋弹簧的第一螺旋弹簧具有延伸穿过其中的第一中心开口。 一对相对的螺旋弹簧的第二螺旋弹簧具有延伸穿过其中的第二中心开口，该第二中心开口与第一中心开口同心，用于接受U形夹销。 第一和第二螺旋弹簧各自由矩形截面梁组成。 弹性飞机发动机支架可以在三个平移轴上调节，以支持三个自由度的隔振。 两个或多个弹性飞机发动机支架提供六个自由度的隔振。 弹性飞机发动机支架将飞机发动机连接到塔架结构，并有助于隔离振动力。

公开(公告)号：US08678323B2

公开(公告)日：2014-03-25

申请号：US13406647

申请日：2012-02-28

申请人： Tim Daniel Barber ,  Timothy Hindle ,  Ken Young ,  Torey Davis

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

IPC分类号： B64G1/00

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

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

摘要翻译： 提供发射锁组件的实施例，如包括一个或多个发射锁组件的航天器隔离系统的实施例。 在一个实施例中，发射锁组件包括第一和第二安装件，可释放夹紧装置和轴向间隙放大装置。 可释放的夹紧装置通常将第一和第二安装件保持在夹紧接合状态; 并且当被致动时，将第一和第二安装件从夹紧的接合件释放以允许它们之间的相对轴向运动。 轴向间隙放大装置通常位于阻挡位置，其中间隙放大装置阻碍第一和第二安装件之间的相对轴向运动。 当第一和第二安装件从夹紧接合松开时，轴向间隙放大装置移动到非阻挡位置，以增加第一和第二安装件之间的轴向运动范围。

公开(公告)号：US20130067931A1

公开(公告)日：2013-03-21

申请号：US13239115

申请日：2011-09-21

申请人： Timothy Hindle ,  Brian Cottrell ,  Torey Davis

发明人： Timothy Hindle ,  Brian Cottrell ,  Torey Davis

IPC分类号： F02C7/20 ,  B23P17/00

CPC分类号： F01D25/04 ,  F02C7/20 ,  F05B2260/966 ,  Y02T50/671 ,  Y10T29/49229

摘要： Embodiments of a gas turbine engine assembly including a strut-based vibration isolation mount are provided, as are embodiments of a method for producing such a gas turbine engine assembly. In one embodiment, the gas turbine engine assembly includes a gas turbine engine and a vibration isolation mount. The vibration isolation mount includes, in turn, at least one three parameter axial strut having a first end attached to the gas turbine engine and having a second, opposing end configured to be attached to the airframe. The three parameter axial strut is tuned to minimize the transmission of vibrations from the gas turbine engine to the airframe during operation of the gas turbine engine.

摘要翻译： 提供了包括基于支柱的隔振安装件的燃气涡轮发动机组件的实施例，如用于生产这种燃气涡轮发动机组件的方法的实施例。 在一个实施例中，燃气涡轮发动机组件包括燃气涡轮发动机和隔振支架。 隔振安装座又包括至少一个三参数轴向支柱，其具有附接到燃气涡轮发动机的第一端，并且具有构造成附接到机身的第二相对端。 调整三参数轴向支柱以最小化在燃气涡轮发动机运行期间从燃气涡轮发动机到机身的振动的传递。