公开(公告)号：US20130067931A1

公开(公告)日：2013-03-21

申请号：US13239115

申请日：2011-09-21

Applicant: Timothy Hindle ,  Brian Cottrell ,  Torey Davis

Inventor： Timothy Hindle ,  Brian Cottrell ,  Torey Davis

IPC: F02C7/20 ,  B23P17/00

CPC classification number: F01D25/04 ,  F02C7/20 ,  F05B2260/966 ,  Y02T50/671 ,  Y10T29/49229

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20130051981A1

公开(公告)日：2013-02-28

申请号：US13219287

申请日：2011-08-26

Applicant: Timothy Hindle ,  Steven Hadden ,  Torey Davis

Inventor： Timothy Hindle ,  Steven Hadden ,  Torey Davis

IPC: F01D25/04 ,  B23P11/00

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

Abstract: 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.

Abstract translation: 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：US08678323B2

公开(公告)日：2014-03-25

申请号：US13406647

申请日：2012-02-28

Applicant: Tim Daniel Barber ,  Timothy Hindle ,  Ken Young ,  Torey Davis

Inventor： Tim Daniel Barber ,  Timothy Hindle ,  Ken Young ,  Torey Davis

IPC: B64G1/00

CPC classification number: B64G1/641 ,  B64G1/286 ,  B64G2001/228

Abstract: 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.

Abstract translation: 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：US08992161B2

公开(公告)日：2015-03-31

申请号：US13219287

申请日：2011-08-26

Applicant: Timothy Hindle ,  Steven Hadden ,  Torey Davis

Inventor： Timothy Hindle ,  Steven Hadden ,  Torey Davis

IPC: F01D25/06 ,  F01D25/04

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

Abstract: 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.

Abstract translation: 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：US20130221163A1

公开(公告)日：2013-08-29

申请号：US13406647

申请日：2012-02-28

Applicant: Tim Daniel Barber ,  Timothy Hindle ,  Ken Young ,  Torey Davis

Inventor： Tim Daniel Barber ,  Timothy Hindle ,  Ken Young ,  Torey Davis

IPC: B64G1/64

CPC classification number: B64G1/641 ,  B64G1/286 ,  B64G2001/228

Abstract: 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.

Abstract translation: 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：US20090235765A1

公开(公告)日：2009-09-24

申请号：US12051585

申请日：2008-03-19

Applicant: Paul Buchele ,  Torey Davis

Inventor： Paul Buchele ,  Torey Davis

IPC: G01C19/30

CPC classification number: B64G1/286 ,  F16H1/46 ,  Y10T74/1254 ,  Y10T74/1282

Abstract: A signal torque module assembly (STMA) is provided for use within a control moment gyroscope of the type that includes a rotor assembly. The STMA comprises a torque module assembly (TMA), which includes: (i) a TMA housing, (ii) a torque motor coupled to the TMA housing, and (iii) a gear train coupled to the TMA housing and mechanically coupling the torque motor to the rotor assembly. A signal module assembly is coupled to the TMA housing, and an elongated connector electrically couples the signal module assembly and the rotor assembly. The elongated connector extends through the gear train.

Abstract translation: 提供信号扭矩模块组件（STMA）以在包括转子组件的类型的控制力矩陀螺仪内使用。 STMA包括扭矩模块组件（TMA），其包括：（i）TMA壳体，（ii）联接到TMA壳体的扭矩电动机，和（iii）联接到TMA壳体的齿轮系，并机械地联接扭矩 电机到转子总成。 信号模块组件耦合到TMA壳体，并且细长连接器将信号模块组件和转子组件电耦合。 细长连接器延伸穿过齿轮系。

公开(公告)号：US07985162B2

公开(公告)日：2011-07-26

申请号：US12051585

申请日：2008-03-19

Applicant: Paul Buchele ,  Torey Davis

Inventor： Paul Buchele ,  Torey Davis

IPC: F16H37/06 ,  F16H38/40 ,  G01C19/06

CPC classification number: B64G1/286 ,  F16H1/46 ,  Y10T74/1254 ,  Y10T74/1282

Abstract: A signal torque module assembly (STMA) is provided for use within a control moment gyroscope of the type that includes a rotor assembly. The STMA comprises a torque module assembly (TMA), which includes: (i) a TMA housing, (ii) a torque motor coupled to the TMA housing, and (iii) a gear train coupled to the TMA housing and mechanically coupling the torque motor to the rotor assembly. A signal module assembly is coupled to the TMA housing, and an elongated connector electrically couples the signal module assembly and the rotor assembly. The elongated connector extends through the gear train.

Abstract translation: 提供信号扭矩模块组件（STMA）以在包括转子组件的类型的控制力矩陀螺仪内使用。 STMA包括扭矩模块组件（TMA），其包括：（i）TMA壳体，（ii）联接到TMA壳体的扭矩电动机，和（iii）联接到TMA壳体的齿轮系，并机械地联接扭矩 电机到转子总成。 信号模块组件耦合到TMA壳体，并且细长连接器将信号模块组件和转子组件电耦合。 细长连接器延伸穿过齿轮系。