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    Device for the blind coupling of fluidic, electrical or similar supplies, to a receiving control mechanism
    4.
    发明授权
    Device for the blind coupling of fluidic, electrical or similar supplies, to a receiving control mechanism 有权
    用于将流体，电气或类似用品盲接的装置连接到接收控制机构

    公开(公告)号：US09518687B2

    公开(公告)日：2016-12-13

    申请号：US13940772

    申请日：2013-07-12

    申请人： SNECMA

    发明人： Augustin Curlier ,  Gilles Alain Charier ,  Olivier Belmonte

    IPC分类号： B64C11/38 ,  F16L21/00 ,  F01D7/02

    CPC分类号： F16L21/00 ,  B33Y80/00 ,  B64C11/385 ,  F01D7/02 ,  Y02T50/66

    摘要： A device can be housed coaxially inside a sleeve in which the supplies are situated, and includes: a hollow cylindrical body that fits inside the sleeve and accepts the mechanism in the housing of the hollow body, with passages for respectively connecting the supplies to said mechanism; and a cover which is integrated or fixed, removably, on the front side of the cylindrical body and connects the hidden supplies to the respective passages of the body.

    摘要翻译： 装置可以同轴地容纳在供应物所在的套筒内，并且包括：中空圆柱体，其配合在套筒内部并且接纳中空本体的壳体中的机构，具有用于将供给物分别连接到所述机构的通道 ; 以及可拆卸地一体地或固定在圆筒体的前侧上并将隐藏的物品连接到身体的各个通道的盖子。

    Aircraft gas turbine with adjustable fan
    5.
    发明授权
    Aircraft gas turbine with adjustable fan 有权
    飞机燃气轮机带可调风扇

    公开(公告)号：US09194397B2

    公开(公告)日：2015-11-24

    申请号：US13739722

    申请日：2013-01-11

    申请人： Rolls-Royce Deutschland Ltd & Co KG

    发明人： Predrag Todorovic

    IPC分类号： F04D19/00 ,  F01D5/30 ,  F01D7/02 ,  F02K3/06

    CPC分类号： F04D19/00 ,  F01D5/3007 ,  F01D7/02 ,  F02K3/06 ,  F05D2220/36 ,  F05D2260/74 ,  F05D2260/79 ,  Y02T50/671

    摘要： The present invention relates to an aircraft gas turbine having a fan rotatable about an engine axis in the inflow region of the aircraft gas turbine, with the fan having several fan blades, with each fan blade being moveably mounted on a hub rotatable about the engine axis by means of its blade root on an area which is at the front in the flow direction, and with each fan blade being moveably mounted on an area at the rear in the flow direction, on an adjusting disk axially displaceable relative to the engine axis and non-rotatable with the hub, with the pitch angle of the fan blades being variable by the axial movement of the adjusting disk.

    摘要翻译： 本发明涉及一种飞机燃气轮机，其具有可在飞机燃气轮机的流入区域中围绕发动机轴线旋转的风扇，风扇具有多个风扇叶片，每个风扇叶片可移动地安装在可围绕发动机轴线旋转的轮毂 通过其叶片根部在位于流动方向前方的区域上，并且每个风扇叶片可移动地安装在沿流动方向的后部的区域上，在相对于发动机轴线可轴向移动的调节盘上，以及 与轮毂不可旋转，风扇叶片的俯仰角可通过调节盘的轴向运动而变化。

    Air driven turbine including a blade pitch control system
    7.
    发明授权
    Air driven turbine including a blade pitch control system 失效
    包括叶片桨距控制系统的空气驱动涡轮

    公开(公告)号：US5779446A

    公开(公告)日：1998-07-14

    申请号：US553180

    申请日：1995-11-07

    申请人： Jon B. Althof ,  Shan-Chin Tsai ,  Teddy L. Jones

    发明人： Jon B. Althof ,  Shan-Chin Tsai ,  Teddy L. Jones

    IPC分类号： F01D7/00 ,  F01D7/02

    CPC分类号： F01D7/02 ,  F01D7/00 ,  Y02T50/671 ,  Y02T50/673

    摘要： An air driven turbine having variable pitched blades is provided that includes a pitch change mechanism and associated control circuits for automatically adjusting the pitch of the blades during either rotating or non-rotating operational modes of the air driven turbine. The pitch control mechanism includes a resettable overspeed protection device which is directly actuated by an overspeed condition of the turbine and operates independently from the pitch change mechanism to move the blades to a failsafe, feathered, or coarse pitch, low speed position. The pitch control mechanism utilizes a linear actuator in the form of an acme screw drive. The air driven turbine includes a ball ramp thrust bearing for attaching the blades to a hub of the turbine in such a manner that during rotation of the turbine actuation loads on the pitch change mechanism are reduced. The control circuits utilize simple on-off switching circuits for controlling blade pitch, thereby eliminating the need for more complex PID type control functions.

    摘要翻译： 提供了具有可变倾斜叶片的空气驱动涡轮机，其包括桨距改变机构和相关联的控制回路，用于在空气驱动涡轮机的旋转或非旋转操作模式期间自动调节桨叶的桨距。 俯仰控制机构包括可重置的超速保护装置，其直接由涡轮机的超速状态致动，并且独立于桨距变化机构操作以将叶片移动到故障保护，羽化或粗桨距低速位置。 俯仰控制机构采用直角螺丝传动形式的线性致动器。 空气驱动涡轮机包括用于将叶片附接到涡轮机的轮毂的滚珠斜坡推力轴承，使得在叶轮变化机构上的涡轮致动负载的旋转减小时。 控制电路利用简单的开 - 关切换电路来控制叶片间距，从而无需更复杂的PID控制功能。

    Propeller pitch control
    8.
    发明授权
    Propeller pitch control 失效
    螺旋桨桨距控制

    公开(公告)号：US5213471A

    公开(公告)日：1993-05-25

    申请号：US576884

    申请日：1990-09-04

    申请人： Edwin K. Miller ,  Robert L. Roberts ,  Petr Hora ,  David L. Joyce ,  John S. Mears

    发明人： Edwin K. Miller ,  Robert L. Roberts ,  Petr Hora ,  David L. Joyce ,  John S. Mears

    IPC分类号： B64C11/32 ,  F01D7/02

    CPC分类号： F01D7/02 ,  B64C11/325 ,  B64D2027/005 ,  Y02T50/66 ,  Y02T50/673

    摘要： The invention concerns a system for controlling an aircraft propeller. A hydraulic motor controls pitch of the propeller blades. The propeller blades are characterized by the absence of feather-inducing counterweights. An overspeed governor senses when propeller speed exceeds a limit, and, in response, assumes control of the hydraulic motor and drives the blades toward a coarsened pitch position, which reduces the propeller speed. In another form of the invention, a mechanical brake can override the hydraulic motor and mechanically retard a rotating gear, which causes the propeller blades to move toward a coarsened pitch.

    摘要翻译： 本发明涉及一种用于控制飞行器螺旋桨的系统。 液压马达控制螺旋桨叶片的间距。 螺旋桨叶片的特征在于没有羽毛诱导配重。 超速调速器检测螺旋桨速度是否超过极限，并且作为响应，控制液压马达并驱动叶片朝向粗化桨距位置，这降低了螺旋桨速度。 在本发明的另一种形式中，机械式制动器可以超越液压马达并且机械地延迟旋转的齿轮，这使得螺旋桨叶片朝着粗化间距移动。