公开(公告)号：US09073627B2

公开(公告)日：2015-07-07

申请号：US12971026

申请日：2010-12-17

Applicant: Mark R. Jolly ,  Andrew D. Meyers ,  Daniel Mellinger ,  Douglas E. Ivers ,  Askari Badre-Alam ,  Douglas A. Swanson ,  Russell E. Altieri

Inventor： Mark R. Jolly ,  Andrew D. Meyers ,  Daniel Mellinger ,  Douglas E. Ivers ,  Askari Badre-Alam ,  Douglas A. Swanson ,  Russell E. Altieri

IPC: G06F19/00 ,  G05D15/00 ,  G05D19/00 ,  B64C27/00 ,  F16F15/22

CPC classification number: B64C27/001 ,  B64C2027/003 ,  F16F15/22 ,  G05D19/02 ,  Y10S416/50

Abstract: A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.

Abstract translation: 一种包括车辆振动控制系统的旋翼飞机。 车辆振动控制系统包括旋转翼飞行器构件传感器，用于输出与旋转的旋翼轮毂构件相对于非旋转体相对旋转相关的旋转翼飞行器构件数据，至少第一非旋转体振动传感器，至少 至少第一非旋转体圆周力产生器，至少第一非旋转体圆周力产生器，其与所述非旋转体固定连接，所述至少第一非旋转体振动传感器，至少第一非旋转体振动传感器，至少第一非旋转体振动传感器， 主体圆形力发生器被控制以产生具有可控旋转力量级和可控旋转力相位的旋转力，可控旋转力量值从最小力量控制到最大力量值，并且可控旋转力相位被控制在 参考旋转 翼型飞行器构件传感器数据与旋转的旋转翼型轮毂相对于非旋转体相对旋转，其中由至少第一非旋转体振动传感器感测的振动减小。

公开(公告)号：US08894353B2

公开(公告)日：2014-11-25

申请号：US13146964

申请日：2010-01-12

Applicant: James McCracken ,  Christoph Hermann Richter

Inventor： James McCracken ,  Christoph Hermann Richter

IPC: F01D5/22 ,  F01D5/26

CPC classification number: F01D5/22 ,  F01D5/225 ,  F05D2220/31 ,  F05D2250/231 ,  F05D2250/314 ,  F05D2260/96 ,  Y10S416/50

Abstract: A turbine blade system including a first turbine blade and a second turbine blade being arranged adjacent to each other shall be suited to allow a particularly secure and reliable operation of a turbine. To this end, the turbine blades are in contact in a first surface area and separated from each other in a second surface area, wherein the first turbine blade includes a pocket containing a damping piece in the second surface area.

Abstract translation: 包括彼此相邻布置的第一涡轮叶片和第二涡轮叶片的涡轮机叶片系统应适合于允许涡轮机特别安全和可靠的操作。 为此，涡轮机叶片在第一表面区域中接触并且在第二表面区域彼此分离，其中第一涡轮机叶片包括在第二表面区域中包含阻尼件的口袋。

公开(公告)号：US08876472B2

公开(公告)日：2014-11-04

申请号：US13262512

申请日：2010-03-31

Applicant: Marc Dijoud ,  Jean-Philippe Ousty

Inventor： Marc Dijoud ,  Jean-Philippe Ousty

IPC: F01D5/14 ,  F04D29/38 ,  F04D29/34 ,  F01D5/22 ,  F01D5/16 ,  F01D21/04

CPC classification number: F01D5/16 ,  F01D5/141 ,  F01D5/22 ,  F01D21/045 ,  F05D2220/40 ,  Y10S416/50

Abstract: A turbine wheel including: a plurality of first and second blades, at least one of the first blades being adjacent to at least one of the second blades; a disk presenting an axis of rotation and a periphery having the blades mounted thereat, each of the blades including a head solid with a root engaged in a housing that opens to the periphery of the disk, each of the blades including a keying mechanism including a respective shelf arranged between the head and the root of the blade, the shelves of the first blades presenting an azimuth length different from the azimuth length of the shelves of the second blades; and a damper device arranged at least between the adjacent blades, the damper device being arranged between the shelves of the blades and the periphery of the disk.

Abstract translation: 一种涡轮机叶轮，包括：多个第一和第二叶片，所述第一叶片中的至少一个与所述第二叶片中的至少一个相邻; 呈现旋转轴线的圆盘和安装有叶片的边缘，每个叶片包括具有根部的根部的头部实心，所述根部与通向盘的周边的壳体接合，每个叶片包括键合机构， 相应的搁架布置在头部和叶片的根部之间，第一叶片的搁架具有不同于第二叶片的搁架的方位角长度的方位角长度; 以及至少在相邻叶片之间布置的阻尼器装置，所述阻尼装置布置在所述叶片的搁架和所述盘的周边之间。

公开(公告)号：US08870547B2

公开(公告)日：2014-10-28

申请号：US13208861

申请日：2011-08-12

Applicant: Karim Grase ,  Ichwan Zuardy ,  Marianne Jacoba Reijerkerk

Inventor： Karim Grase ,  Ichwan Zuardy ,  Marianne Jacoba Reijerkerk

IPC: B64C11/20 ,  B64C3/18 ,  B64C1/06

CPC classification number: B64C1/06 ,  B64C3/18 ,  Y02E10/721 ,  Y10S416/50 ,  Y10T29/49764 ,  Y10T428/23 ,  Y10T428/24182 ,  Y10T428/31504

Abstract: The present invention provides a structural element, in particular for an aircraft and spacecraft, comprising a core, the rigidity of which varies at least in portions for optimising the aeroelastic characteristics of the structural element The present invention also provides a method for producing a structural element, in particular for an aircraft and spacecraft, which comprises the following steps: provision of a structural element comprising a core; determination of the aeroelastic behavior of the structural element; and variation, at least in portions, of the rigidity of the core of the structural element such that the aeroelastic behavior of the structural element is optimised. The present invention further provides an aircraft and spacecraft comprising a structural element of this type, and a rotor blade, in particular for a wind turbine, comprising a structural element of this type.

Abstract translation: 本发明提供了一种特别是飞机和航天器的结构元件，其包括芯，其刚度至少部分变化以优化结构元件的气动弹性特征本发明还提供了一种用于制造结构元件的方法 特别是对于飞机和航天器，其包括以下步骤：提供包括核心的结构元件; 确定结构元件的气动弹性行为; 并且至少部分地改变结构元件的芯的刚性，使得优化结构元件的气动弹性行为。 本发明还提供了一种包括这种结构元件的飞行器和航天器，特别是用于风力涡轮机的转子叶片，其包括这种类型的结构元件。

公开(公告)号：US20140112792A1

公开(公告)日：2014-04-24

申请号：US14143828

申请日：2013-12-30

Applicant: United Technologies Corporation

Inventor： Seth J. Thomen ,  Christopher Corcoran

IPC: F01D5/22 ,  F01D11/00

CPC classification number: F01D5/22 ,  F01D11/006 ,  F01D11/008 ,  F05D2250/25 ,  Y10S416/50

Abstract: A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.

Abstract translation: 用于联接相邻涡轮机叶片的平台的减震器销包括第一平坦纵向端部区域，第二平坦纵向端部区域和减小的横截面面积。 减小的横截面积由第一主体区域与第一平坦纵向端部区域分离，并且减小的横截面面积与第二平坦纵向端部区域通过第二主体区域分离。 横截面积减小的截面积小于第一和第二主体区域的横截面面积。

公开(公告)号：US20130309097A1

公开(公告)日：2013-11-21

申请号：US13952181

申请日：2013-07-26

Applicant: Rolls-Royce PLC

Inventor： David MILLER

IPC: F01D5/16

CPC classification number: F01D5/16 ,  F01D5/26 ,  F05D2260/96 ,  F16F7/08 ,  F16F2230/36 ,  Y10S416/50 ,  Y10T29/49336 ,  Y10T29/49337 ,  Y10T29/49938 ,  Y10T29/4994 ,  Y10T74/213 ,  Y10T74/2131

Abstract: Vibration damping is important with regard to such components as hollow turbine blades in gas turbine engines. Traditionally damping has occurred through damping elements secured at the root or tip of such blades. Such damping is not optimised and results in potential problems with wear in operational life. By providing a tube of deformable material which can be located within a hollow cavity it is possible to provide an element which through friction engagement can absorb vibration energy and therefore damp such vibration. The tube incorporates a number of cuts and/or grooves in an appropriate pattern in order to define a deformation profile once the tube is expanded in location. The tube is secured in position internally upon an expandable element which is typically an inflatable device. Once in position the tube is retained in its expanded deformable profile and the engagement between the tube and the hollow cavity wall surface results in energy absorption through vibration episodes. It is also possible to provide a tube formed from a shape memory alloy which will expand of its own right in location to engage the hollow cavity wall surfaces for energy absorption during vibration episodes.

Abstract translation: 振动阻尼对于诸如燃气涡轮发动机中的中空涡轮叶片的部件是重要的。 传统的阻尼是通过固定在这种叶片的根部或尖端处的阻尼元件发生的。 这种阻尼没有被优化，并且在使用寿命中导致潜在的磨损问题。 通过提供可以位于中空腔内的可变形材料管，可以提供通过摩擦接合可以吸收振动能量并因此减弱这种振动的元件。 该管以合适的图案包括多个切口和/或凹槽，以便一旦管在位置上扩展就能限定变形曲线。 管内部固定在可膨胀元件上，该可膨胀元件通常是可充气装置。 一旦就位，管被保持在其膨胀的可变形轮廓中，并且管与中空腔壁表面之间的接合导致通过振动发生的能量吸收。 还可以提供一种由形状记忆合金形成的管，其将在其位置上自身扩张以接合中空腔壁表面，以在振动发生期间吸收能量。

公开(公告)号：US08172541B2

公开(公告)日：2012-05-08

申请号：US12394260

申请日：2009-02-27

Applicant: Ronald Ralph Cairo

Inventor： Ronald Ralph Cairo

IPC: B64C11/04 ,  B64C11/16 ,  B64C27/46 ,  F03B3/12 ,  F03B7/00 ,  F04D29/34 ,  F04D29/38 ,  B63H1/26 ,  B63H7/02 ,  F01D5/14 ,  F03D11/02

CPC classification number: F04D29/023 ,  F04D29/324 ,  F05D2260/96 ,  F05D2300/43 ,  Y10S416/50

Abstract: An airfoil component and method for producing the component. The component has root and airfoil portions, the latter having an airfoil tip and oppositely-disposed concave and convex surfaces that converge at leading and trailing edges of the airfoil portion. The airfoil portion has at least one stiffener between first and second walls thereof that define the concave and convex surfaces, respectively. The stiffener defines multiple internal cavities within the airfoil portion that extend in the span-wise direction of the airfoil portion. A polymeric material fills at least one of the internal cavities and is bonded to the airfoil portion only at an extremity of the internal cavity nearer the root portion, and not to the stiffener or to the first and second walls of the airfoil portion, to define an internal damping member that provides a vibratory damping effect to the airfoil portion.

Abstract translation: 翼型部件及其制造方法。 该部件具有根部和翼面部分，后者具有翼型末端和相对设置的凹凸表面，其在翼型部分的前缘和后缘处会聚。 翼型部分在其第一和第二壁之间分别具有限定凹面和凸面的至少一个加强筋。 加强件限定在翼型部分内在翼型部分的跨度方向上延伸的多个内部空腔。 聚合物材料填充至少一个内部空腔，并且仅在靠近根部的内部空腔的末端而不是加强件或翼型部分的第一和第二壁上结合到翼型部分，以限定 内部阻尼构件，其向翼型部提供振动阻尼作用。

公开(公告)号：US08141813B2

公开(公告)日：2012-03-27

申请号：US12581560

申请日：2009-10-19

Applicant: Santino Pancotti ,  Dante Ballerio ,  Attilio Colombo

Inventor： Santino Pancotti ,  Dante Ballerio ,  Attilio Colombo

IPC: B64C27/00

CPC classification number: B64C27/001 ,  Y10S416/50

Abstract: A helicopter having a rotor, a fuselage, and a transmission connected functionally to the rotor; the helicopter has a supporting body supporting at least the transmission, and connecting means having a first connecting member and at least one second connecting member connected to the supporting body and the fuselage respectively; and the connecting means have elastic means interposed between the first and second connecting member.

Abstract translation: 具有转子，机身和与转子功能相连的变速器的直升机; 所述直升机具有至少支撑所述变速器的支撑体，并且所述连接装置具有分别连接到所述支撑体和所述机身的第一连接构件和至少一个第二连接构件; 并且所述连接装置具有插入在所述第一和第二连接构件之间的弹性装置。

公开(公告)号：US20120051937A1

公开(公告)日：2012-03-01

申请号：US13208861

申请日：2011-08-12

Applicant: Karim Grase ,  Ichwan Zuardy ,  Marianne Jacoba Reijerkerk

Inventor： Karim Grase ,  Ichwan Zuardy ,  Marianne Jacoba Reijerkerk

IPC: F01D5/14 ,  B23Q17/00 ,  B32B7/02 ,  B32B3/08 ,  B32B9/00

CPC classification number: B64C1/06 ,  B64C3/18 ,  Y02E10/721 ,  Y10S416/50 ,  Y10T29/49764 ,  Y10T428/23 ,  Y10T428/24182 ,  Y10T428/31504

Abstract: The present invention provides a structural element, in particular for an aircraft and spacecraft, comprising a core, the rigidity of which varies at least in portions for optimising the aeroelastic characteristics of the structural element The present invention also provides a method for producing a structural element, in particular for an aircraft and spacecraft, which comprises the following steps: provision of a structural element comprising a core; determination of the aeroelastic behaviour of the structural element; and variation, at least in portions, of the rigidity of the core of the structural element such that the aeroelastic behaviour of the structural element is optimised. The present invention further provides an aircraft and spacecraft comprising a structural element of this type, and a rotor blade, in particular for a wind turbine, comprising a structural element of this type.

Abstract translation: 本发明提供了一种特别是飞机和航天器的结构元件，其包括芯，其刚度至少部分变化以优化结构元件的气动弹性特征本发明还提供了一种用于制造结构元件的方法 特别是对于飞机和航天器，其包括以下步骤：提供包括核心的结构元件; 确定结构元件的气动弹性行为; 并且至少部分地改变结构元件的芯的刚性，使得优化结构元件的气动弹性行为。 本发明还提供了一种包括这种结构元件的飞行器和航天器，特别是用于风力涡轮机的转子叶片，其包括这种类型的结构元件。

公开(公告)号：US08123483B2

公开(公告)日：2012-02-28

申请号：US11965786

申请日：2007-12-28

Applicant: Frédéric Beroul

Inventor： Frédéric Beroul

IPC: B64C27/51

CPC classification number: B64C27/51 ,  B64C27/35 ,  Y10S416/50

Abstract: The present invention relates to an improvement to rotorcraft rotors (1) fitted with inter-blade drag dampers (15) such that for each blade (4), the two joints (16) connecting said blade (4) to two inter-blade drag dampers (15) are disposed on either side of the pitch variation axis (101) of said blade, at least one of the two joints (16) being offset to above the plane P containing the pitch variation axis (101) and the vertical flapping axis (102).

Abstract translation: 本发明涉及一种装配有叶片间阻尼器（15）的旋翼航空转子（1）的改进，使得对于每个叶片（4），将所述叶片（4）连接到两个叶片间拖动的两个接头（16） 阻尼器（15）设置在所述叶片的俯仰变化轴线（101）的任一侧上，所述两个接头（16）中的至少一个偏移到包含所述俯仰变化轴线（101）的平面P的上方，并且垂直拍动 轴（102）。