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285 条记录 (耗时 0.02 秒)

    Rotor blade with electrical interconnects
    72.
    发明公开
    Rotor blade with electrical interconnects 审中-公开
    Rotorblatt mit elektrischenAnschlüssen

    公开(公告)号：EP2868575A1

    公开(公告)日：2015-05-06

    申请号：EP14190152.0

    申请日：2014-10-23

    申请人： Goodrich Corporation

    发明人： Miller, Lindsay ,  Mullen, James

    IPC分类号： B64C27/46 ,  B64C27/467 ,  B64D15/12

    摘要： A rotary blade (28) includes a blade tip assembly (34) with a first bus bar segment (46) and a main blade assembly (32) with second bus bar segment (48). The first bus bar segment is connected to the blade tip assembly and the second bus bar segment is connected to the main blade assembly. The blade tip assembly is connected to the main blade assembly such that the first and second bus bar segments are longitudinally offset from one another. A low-profile interconnect (100; 200) spans the first and second bus bar segments for resistively generating less heat than the bus bar segments for a predetermined current flow.

    摘要翻译： 旋转刀片（28）包括具有第一母线段（46）的叶片末端组件（34）和具有第二母线段（48）的主叶片组件（32）。 第一母线段连接到叶片尖端组件，第二母线段连接到主叶片组件。 叶片尖端组件连接到主叶片组件，使得第一和第二母线段彼此纵向偏移。 低调互连（100; 200）跨越第一和第二母线段，用于为预定的电流电阻产生比母线段更少的热量。

    Rotary wing aircraft blade tracking
    73.
    发明公开
    Rotary wing aircraft blade tracking 审中-公开
    Drehflügelflugzeug-Blattverfolgung

    公开(公告)号：EP2738090A2

    公开(公告)日：2014-06-04

    申请号：EP13194455.5

    申请日：2013-11-26

    申请人： Sikorsky Aircraft Corporation

    发明人： Fang, Austin ,  Lozano, Steven P.

    IPC分类号： B64C27/00 ,  B64C27/46

    CPC分类号： B64D45/00 ,  B64C27/008

    摘要： A blade tracking system for a rotary wing aircraft (10) includes a blade sensor (30) mounted on a blade (24) of the rotary wing aircraft (10), the blade sensor (30) wirelessly transmitting blade data; a reference sensor (32) mounted to the rotary wing aircraft, the blade (24) driven by the rotor hub (26), the reference sensor (32) transmitting reference data; and a processor (36) receiving the blade data and the reference data, the processor (36) determining at least one of lead-lag, flap and pitch of the blade in response to the blade data and the reference data.

    摘要翻译： 用于旋转翼飞行器（10）的叶片跟踪系统包括安装在旋转翼飞行器（10）的叶片（24）上的叶片传感器（30），叶片传感器（30）无线地传送叶片数据; 参考传感器（32），其安装到所述旋翼飞行器，所述叶片（24）由所述转子毂（26）驱动，所述参考传感器（32）传输参考数据; 以及接收刀片数据和参考数据的处理器（36），处理器（36）响应于刀片数据和参考数据确定刀片的超前滞后，挡板和间距中的至少一个。

    RETRACTABLE LIFTING BLADES FOR AIRCRAFT
    74.
    发明公开
    RETRACTABLE LIFTING BLADES FOR AIRCRAFT 审中-公开
    伸缩升降飞机

    公开(公告)号：EP1968852A4

    公开(公告)日：2014-05-07

    申请号：EP06847843

    申请日：2006-12-20

    申请人： ALLEN J GERBINO LIVING TRUST DATED MAY 9 2015

    发明人： GERBINO ALLEN J

    IPC分类号： B64C27/02 ,  B64C27/26 ,  B64C27/30 ,  B64C27/32 ,  B64C27/46 ,  B64C27/50 ,  B64C27/605

    CPC分类号： B64C27/022 ,  B64C27/26 ,  B64C27/30 ,  B64C27/32 ,  B64C27/46 ,  B64C27/605

    摘要： A rotor blade assembly for providing vertical lift to an aircraft, having a rotor head and a plurality of blades, with each blade attached to a mechanism such as a cam surface, whereby movement of the mechanism causes the radial distance between the distal tip of the attached blade and the center of the rotor head to alter, decreasing or increasing the length of the lifting surface. The blades are moved from a fully extended position providing maximum lift, to a retracted position in which the blades are removed from the airstream. The pitch of the blades may be controlled by a pitch controller to achieve full helicopter responsiveness. A plurality of bladeletts may be positioned near the outer periphery of the rotor head. When they are moved into the airstream, passing air impacts the bladeletts exerting a pressure, causing rotational movement of the rotor blade assembly.

    Aerofoil
    77.
    发明公开
    Aerofoil 有权
    Tragfläche

    公开(公告)号：EP2508423A2

    公开(公告)日：2012-10-10

    申请号：EP11190396.9

    申请日：2011-11-23

    申请人： AgustaWestland Limited

    发明人： Brocklehurst, Alan

    IPC分类号： B64C27/46

    CPC分类号： B64C27/463 ,  Y02E10/721 ,  Y10T29/49332

    摘要： An aerofoil (12a, 12b, 12c, 12d) has a main portion of aerofoil cross section, an inner spanwise root end where the aerofoil is in use secured to a supporting structure, and at an outermost spanwise end outboard of the main portion, beyond a tip station, a tip region, and the tip region including a tip edge, the planform configuration of the tip edge lying on a first Bezier curve constructed from at least four control points P1, P2, P3 and P4, the control points P1, P2, P3 and P4 each lying on the periphery of a polygon which bounds the tip region, Bezier control point P1 being located on a leading edge of the aerofoil at the tip station, which is at a spanwise position between 93.5%R and 95.9%R, where first and second sides of the polygon meet, the first side being at the tip station extending perpendicularly to a blade reference axis, which extends spanwise of the main portion of the aerofoil, and the second side being a tangent to the leading edge of the aerofoil at control point P1, which extends between control point P1 to a position where the second side meets a third side of the boundary polygon at a position outwardly of the tip edge, the third side being parallel to the first side and extending between the position where the third side meets the second side, to where the third side and a fourth side meet, control point P2 being located on the second side at a position between 30% and 80% along the second side from P1, control point P3 being located on the third side at a position between 30% and 90% along the third side from where the second and third sides meet, and control point P4 being located at the outermost tip edge point at a trailing edge of the aerofoil, where R is the effective aerofoil span.

    摘要翻译： 机翼（12a，12b，12c，12d）具有机翼横截面的主要部分，内翼展根部，其中机翼被使用固定到支撑结构，并且在主要部分的外侧的最外翼展方向端部 尖端区域，尖端区域和包括尖端边缘的尖端区域，尖端边缘的平面形状位于由至少四个控制点P1，P2，P3和P4构成的第一贝塞尔曲线上，控制点P1， P2，P3和P4各自位于限定尖端区域的多边形的周边上，贝塞尔控制点P1位于尖端站的机翼的前缘，其位于93.5％R和95.9％之间的翼展位置， R，其中所述多边形的第一和第二面相交，所述第一侧处于所述尖端站处，所述尖端站垂直于叶片参考轴线延伸，所述叶片参考轴线延伸到所述机翼的主要部分的翼展方向，并且所述第二侧面与所述前缘 在控制点P1的机翼 ，其在控制点P1之间延伸到第二侧在尖端边缘外侧的位置处与边界多边形的第三侧相交的位置，第三侧平行于第一侧并且在第三侧相遇的位置之间延伸 第二侧，第三侧和第四侧相交，控制点P2位于第二侧，沿着P1的第二侧位于30％至80％之间的位置，控制点P3位于第三侧 沿着第二和第三侧相遇的第三侧的位置在30％和90％之间，并且控制点P4位于机翼后缘处的最外侧尖端边缘处，其中R是有效机翼跨度。

    FLÜGEL FÜR EINE STRÖMUNGSMASCHINE
    78.
    发明授权
    FLÜGEL FÜR EINE STRÖMUNGSMASCHINE 有权
    翅膀叶轮机

    公开(公告)号：EP2334549B1

    公开(公告)日：2012-06-20

    申请号：EP09783256.2

    申请日：2009-09-22

    申请人： Enthammer, Walter

    发明人： Enthammer, Walter

    IPC分类号： F03D1/06 ,  B64C27/46

    CPC分类号： B64C27/463 ,  F03D1/0633 ,  F05B2260/96 ,  Y02E10/721

    摘要： The invention relates to a blade (3) for a turbomachine, in particular for a rotor (2) of a helicopter, comprising a main section (5) that is designed to create a flow in the surrounding medium and that extends from a hub section (4) to a blade tip region (7). An end piece (6) for influencing eddy formation is provided in the blade tip region (7). To achieve a substantial noise reduction, the end piece (6) is designed as a rounded flow body comprising at least one groove (13a, 13b, 13c; 13d, 13e, 13f) originating in the transition region (12) between the body and the main section (5), substantially in the direction of the blade axis (8) and curving towards the trailing edge (11) of the blade (3).