公开(公告)号：EP2674360A1

公开(公告)日：2013-12-18

申请号：EP12171794.6

申请日：2012-06-13

申请人： Claverham Limited

发明人： Brewer,Paul R. ,  Raval, Reg R. ,  Bekircan, Suat

IPC分类号： B64C27/72 ,  F16H25/20 ,  F16H57/04

CPC分类号： B64C27/615 ,  B64C27/00 ,  B64C27/72 ,  B64C2027/7272 ,  F16H2025/249 ,  Y02T50/34

摘要： A rotor blade assembly includes a rotor blade (20) and a rotatable flap portion (34) located along a span of the rotor blade (20). A linear actuator (46) located inside the rotor blade (20) is operably connected to the flap portion (34) to rotate the flap portion (34) about a flap axis (44) and is absent oil, grease or other fluid lubricant. A rotary-winged aircraft (10) includes an airframe (14) and a main rotor assembly (12) operably connected to the airframe (14). The main rotor assembly includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis (22). At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade (20) and a rotatable flap portion (34) located along a span of the rotor blade (20). A linear actuator (46) positioned inside the rotor blade (20) is operably connected to the flap portion (34) to rotate the flap portion (34) about a flap axis (44) and is absent oil, grease or other fluid lubricant.

摘要翻译： 转子叶片组件包括沿着转子叶片（20）的跨度定位的转子叶片（20）和可旋转翼片部分（34）。 位于转子叶片（20）内部的线性致动器（46）可操作地连接到翼片部分（34），以使翼片部分（34）围绕翼片轴线（44）旋转，并且不存在油，油脂或其它流体润滑剂。 旋转飞机（10）包括机身（14）和可操作地连接到机身（14）的主转子组件（12）。 主转子组件包括可围绕转子组件轴线（22）旋转的多个转子叶片组件。 多个转子叶片组件中的至少一个转子叶片组件包括转子叶片（20）和沿转子叶片（20）的跨度定位的可旋转翼片部分（34）。 定位在转子叶片（20）内部的线性致动器（46）可操作地连接到翼片部分（34），以使翼片部分（34）围绕翼片轴线（44）旋转，并且不存在油，油脂或其它流体润滑剂。

公开(公告)号：EP3409962A1

公开(公告)日：2018-12-05

申请号：EP17174351.1

申请日：2017-06-02

申请人： Claverham Limited

发明人： Bekircan, Suat

IPC分类号： F16C19/26 ,  F16C23/08 ,  F16C33/36 ,  F16C33/58

CPC分类号： F16C33/366 ,  F16C19/26 ,  F16C19/364 ,  F16C23/086 ,  F16C33/36 ,  F16C33/541 ,  F16C33/585

摘要： A roller bearing comprises inner and outer rings (20,30) defining a toroidal inner raceway rotatable about a bearing axis (A). A plurality of concave rolling elements (10) is arranged in a single row between the outer and inner rings (20,30). Each of the plurality of concave rolling elements (10) is a symmetrical cylindrical roller having circular ends, a roller axis passing through the centre of the circular ends, and a concave side profile (12) that extends continuously between the circular ends. The toroidal inner and outer raceways each have a convex race surface that continuously engages the concave side profile (12) between the circular ends of each concave rolling element (10) with a first radius and extends axially beyond the circular ends of each concave rolling element with a second radius that is less than the first radius.

公开(公告)号：EP2703288B1

公开(公告)日：2018-03-14

申请号：EP12250147.1

申请日：2012-08-31

申请人： Claverham Limited

发明人： Brewer, Paul R. ,  Bekircan, Suat

IPC分类号： B64C27/72

CPC分类号： B64C27/615 ,  B64C27/72 ,  B64C2027/7266 ,  Y02T50/34

摘要： A rotor blade assembly includes a rotor blade (20) and a movable trim tab (34) located along a span of the rotor blade (20). A linear positioner (46) is located inside the rotor blade (20) and operably connected to the trim tab (34) to move the trim tab (34) thereby reducing rotor blade vibration. A method for reducing vibration of a rotor assembly includes energizing a linear positioner (46) located inside a rotor blade (20) of the rotor assembly and moving an output piston (52) of the linear positioner (46). A trim tab (34) located at the rotor blade (20) is moved to a selected trim tab angle relative to the rotor blade (20) by the output piston (52), and the linear positioner (46) is deenergized thereby locking the trim tab (34) at the selected trim tab angle.

公开(公告)号：EP2703288A1

公开(公告)日：2014-03-05

申请号：EP12250147.1

申请日：2012-08-31

申请人： Claverham Limited

发明人： Brewer, Paul R. ,  Bekircan, Suat

IPC分类号： B64C27/72

CPC分类号： B64C27/615 ,  B64C27/72 ,  B64C2027/7266 ,  Y02T50/34

摘要： A rotor blade assembly includes a rotor blade (20) and a movable trim tab (34) located along a span of the rotor blade (20). A linear positioner (46) is located inside the rotor blade (20) and operably connected to the trim tab (34) to move the trim tab (34) thereby reducing rotor blade vibration. A method for reducing vibration of a rotor assembly includes energizing a linear positioner (46) located inside a rotor blade (20) of the rotor assembly and moving an output piston (52) of the linear positioner (46). A trim tab (34) located at the rotor blade (20) is moved to a selected trim tab angle relative to the rotor blade (20) by the output piston (52), and the linear positioner (46) is deenergized thereby locking the trim tab (34) at the selected trim tab angle.

摘要翻译： 转子叶片组件包括沿着转子叶片（20）的跨度定位的转子叶片（20）和可移动的装饰片（34）。 线性定位器（46）位于转子叶片（20）内并且可操作地连接到修剪突片（34）以移动修剪突片（34），从而减少转子叶片的振动。 一种用于减小转子组件的振动的方法包括对位于转子组件的转子叶片（20）内部的线性定位器（46）进行激励，并移动线性定位器（46）的输出活塞（52）。 位于转子叶片（20）处的修剪突片（34）通过输出活塞（52）相对于转子叶片（20）移动到选定的修剪翼片角度，并且线性定位器（46）被断电，从而锁定 修剪片（34）处于选定的修剪片角度。

公开(公告)号：EP2674359A1

公开(公告)日：2013-12-18

申请号：EP12171792.0

申请日：2012-06-13

申请人： Claverham Limited

发明人： Brewer, Paul R. ,  Bekircan, Suat ,  Raval, Reg R.

IPC分类号： B64C27/615

CPC分类号： B64C27/615 ,  B64C2027/7266 ,  F16H21/40 ,  Y02T50/34 ,  Y10T74/18056

摘要： A rotor blade assembly includes a rotor blade (20), a rotatable flap portion (34) disposed along a span of the rotor blade (20). A rotary actuator (46) is located inside the rotor blade (20) and is operably connected to the flap portion (34) to rotate the flap portion (34) about a flap axis. A rotary-winged aircraft (10) includes an airframe (14) and a main rotor assembly (12) operably connected to the airframe (14). The main rotor assembly (12) includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis (22). At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade (20) and a rotatable flap portion (34) disposed along a span of the rotor blade (20). A rotary actuator (46) is located inside the rotor blade (20) and is operably connected to the flap portion (34) to rotate the flap portion (34) about a flap axis. The rotary actuator (46) is absent oil, grease or other fluid lubricant.

摘要翻译： 转子叶片组件包括转子叶片（20），沿着转子叶片（20）的跨度设置的可旋转翼片部分（34）。 旋转致动器（46）位于转子叶片（20）内部并且可操作地连接到翼片部分（34）以使翼片部分（34）围绕翼片轴线旋转。 旋转飞机（10）包括机身（14）和可操作地连接到机身（14）的主转子组件（12）。 主转子组件（12）包括可围绕转子组件轴线（22）旋转的多个转子叶片组件。 多个转子叶片组件中的至少一个转子叶片组件包括转子叶片（20）和沿着转子叶片（20）的跨度设置的可旋转翼片部分（34）。 旋转致动器（46）位于转子叶片（20）内部并且可操作地连接到翼片部分（34）以使翼片部分（34）围绕翼片轴线旋转。 旋转致动器（46）不存在油，油脂或其它流体润滑剂。