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    BLADE
    21.
    发明申请
    BLADE 有权
    刀

    公开(公告)号：US20100054937A1

    公开(公告)日：2010-03-04

    申请号：US12547573

    申请日：2009-08-26

    Applicant: Peter Rowland Beckford ,  Simon Read ,  Ian Colin Deuchar Care

    Inventor： Peter Rowland Beckford ,  Simon Read ,  Ian Colin Deuchar Care

    IPC: F01D5/14

    CPC classification number: F01D5/147 ,  F01D5/14 ,  F01D21/045 ,  F05D2300/612

    Abstract: A fan blade for a gas turbine engine has an aerofoil part and a root part. The root part includes a root former; the root former 18 includes a zone of weakness, which reduces the ability of the root part to withstand an impact force. Thus, in an impact situation in which the fan blade has separated from the fan rotor and the fan blade has itself separated into fragments, the root part will fracture or buckle more easily than would be the case with conventional arrangements. This will lower the impact force of the root part upon the fan casing, thus permitting the fan casing to be designed to withstand lower impact forces. The fan casing can therefore be made lighter, and cheaper, than in conventional arrangements.

    Abstract translation: 用于燃气涡轮发动机的风扇叶片具有机翼部分和根部部分。 根部包括根部; 根部18包括弱点区域，这降低了根部部分承受冲击力的能力。 因此，在风扇叶片与风扇转子分离并且风扇叶片本身分离成碎片的冲击情况下，根部将比常规布置的情况更容易断裂或弯曲。 这将降低根部对风扇壳体的冲击力，从而允许风扇壳体设计成承受较低的冲击力。 因此，风扇壳体可以比常规布置更轻，更便宜。

    Test apparatus and method of testing
    22.
    发明申请
    Test apparatus and method of testing 有权
    测试仪器和测试方法

    公开(公告)号：US20090126455A1

    公开(公告)日：2009-05-21

    申请号：US12292108

    申请日：2008-11-12

    Applicant: Simon Read

    Inventor： Simon Read

    IPC: G01N3/30

    CPC classification number: G01M7/08 ,  G01N3/30 ,  G01N3/313

    Abstract: With regard to components it is necessary to test specimens of materials in order to determine acceptability for objective component performance. Previously such testing generally involved fixing and clamping of the test specimen which produced artificial stressing conditions. By providing a specimen component typically in the form of an elongate member 2 which is suspended between mounting ends 3 a combination is provided which has inertia. In such circumstances when a projectile impacts upon the elongate member that elongate member flexes and deforms and this deformation can be monitored for testing purposes. The projectile 4 is arranged to have a relatively facile compliant nature upon impact with the component 2 such that there is no local stressing of the component whilst suspending the mounting ends substantially avoids clamp resilience distorting objective or realistic stressing conditions.

    Abstract translation: 关于部件，为了确定客观部件性能的可接受性，必须对材料样品进行测试。 以前，这种测试通常涉及产生人为应力条件的测试样品的固定和夹紧。 通过提供通常为细长构件2的形式的试样部件，悬挂在安装端3之间，提供具有惯性的组合。 在这种情况下，当弹丸撞击细长构件时，细长构件弯曲并变形，并且该变形可以被监测用于测试目的。 抛射体4被布置成在与部件2碰撞时具有相对容易的顺应性，使得在悬挂安装端的情况下，部件不存在局部应力，而基本上避免了夹紧弹性变形的目标或现实的应力条件。

    Blades
    23.
    发明申请
    Blades 有权
    叶片

    公开(公告)号：US20080019838A1

    公开(公告)日：2008-01-24

    申请号：US11826487

    申请日：2007-07-16

    Applicant: Simon Read ,  Sivasubramaniam K. Sathianathan

    Inventor： Simon Read ,  Sivasubramaniam K. Sathianathan

    IPC: F01D5/14 ,  B21D53/78

    CPC classification number: F04D29/388 ,  F01D5/147 ,  F01D5/3007 ,  F05D2230/23 ,  F05D2230/236 ,  F05D2230/25 ,  Y10T29/49337 ,  Y10T29/49339

    Abstract: A blade (10, FIG. 1) for a gas turbine engine includes an aerofoil portion (12, FIG. 1) and a root portion 14 defined by concave and convex walls 16, 18 having opposing inner surfaces 16a, 18a. A reinforcing member 20 is located between the concave and convex walls 16, 18 and is bonded to the inner surfaces 16a, 18a thereof, and the root portion 14 includes an unbonded region 24a, 24b in which the reinforcing member 20 contacts an inner surface 16a, 18a of one of the concave and convex walls 16, 18 but is not bonded thereto.

    Abstract translation: 用于燃气涡轮发动机的叶片（10，图1）包括机翼部分（12，图1）和由具有相对的内表面16a，18a的凹凸壁18,18限定的根部14。 加强构件20位于凹凸壁16,18之间并且结合到其内表面16a，18a，并且根部14包括加强构件20接触的未结合区域24a，24b 凹壁和凸壁16,18中的一个的内表面16a，18b并不与其接合。

    Aerofoil
    24.
    发明申请
    Aerofoil 有权
    翼型

    公开(公告)号：US20070041842A1

    公开(公告)日：2007-02-22

    申请号：US11484728

    申请日：2006-07-12

    Applicant: Ewan Thompson ,  Simon Read

    Inventor： Ewan Thompson ,  Simon Read

    IPC: B64C27/46

    CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2270/09 ,  F05D2300/603 ,  F05D2300/612 ,  F05D2300/614 ,  F05D2300/702

    Abstract: An aerofoil blade for a gas turbine engine, the blade having a metallic core defining a number of cavities that contain a foamed material. The cavities are shaped such that the force of an impact on one surface of the blade is dissipated through the foam and transmitted to the metallic core. A fibrous internal containment device allows the blade to fragment progressively thereby spreading the load imparted by the blade to a casing should the blade fragment upon impact.

    Abstract translation: 一种用于燃气涡轮发动机的机翼叶片，该叶片具有限定多个包含发泡材料的空腔的金属芯。 空腔成形为使得在叶片的一个表面上的冲击力通过泡沫散发并传递到金属芯。 纤维内部容纳装置允许叶片逐渐碎裂，从而当刀片在冲击时碎片被分散，从而将叶片施加的载荷扩展到壳体。

    Compressor blade
    25.
    发明申请
    Compressor blade 有权
    压缩机叶片

    公开(公告)号：US20050008493A1

    公开(公告)日：2005-01-13

    申请号：US10793907

    申请日：2004-03-08

    Applicant: Simon Read

    Inventor： Simon Read

    IPC: F01D5/16 ,  F01D5/18 ,  F01D21/04 ,  F04D29/32 ,  B63H1/26

    CPC classification number: F01D21/045 ,  F01D5/16 ,  F01D5/18 ,  F04D29/324 ,  Y10S416/50

    Abstract: A compressor blade (26) comprises an aerofoil (36) and a root (38). The aerofoil (36) comprises a concave wall (40) extending from a leading edge (44) to a trailing edge (46) and a convex wall (42) extending from the leading edge (44) to the trailing edge (46). The aerofoil (36) defines at least one internal chamber (48). The root (38) is connected to the aerofoil (36) and the root (38) has a base (50) remote from the aerofoil (38) and at least one aperture (52) extends from the base (50) to the at least one internal chamber (48) in the aerofoil (36). The dimensions, shape and position of the least one aperture (52) are selected such that the root (38) is deformable. This reduces the weight of the containment region of a fan casing (28)

    Abstract translation: 压缩机叶片（26）包括机翼（36）和根部（38）。 机翼（36）包括从前缘（44）延伸到后缘（46）的凹壁（40）和从前缘（44）延伸到后缘（46）的凸壁（42）。 机翼（36）限定至少一个内部腔室（48）。 根（38）连接到机翼（36），根（38）具有远离机翼（38）的基座（50），并且至少一个孔（52）从基座（50）延伸到 机翼（36）中的至少一个内室（48）。 选择最小孔径（52）的尺寸，形状和位置使得根部（38）可变形。 这减小了风扇壳体（28）的容纳区域的重量，

    Wind energy convertor
    26.
    发明授权
    Wind energy convertor 失效
    风能转换器

    公开(公告)号：US4857753A

    公开(公告)日：1989-08-15

    申请号：US116456

    申请日：1987-11-03

    Applicant: Anthony J. S. Mewburn-Crook ,  Peter Bullen ,  Simon Read

    Inventor： Anthony J. S. Mewburn-Crook ,  Peter Bullen ,  Simon Read

    IPC: F03D3/04 ,  F03D9/00

    CPC classification number: F03D3/0409 ,  Y02E10/74 ,  Y10S415/907

    Abstract: In a vertical axis wind generator incorporating a circular turbine supported by an uppermost part of an upstanding support, a stator surrounding and coaxial with the turbine comprises an upper annular body positioned adjacent and or above the upper end of the turbine and having an uppermost surface which over at least a part of its radial width is inclined downwardly towards the vertical axis, a lower annular body positioned adjacent and/or below the lower end of the turbine and, extending lengthwise between the annular bodies, a plurality of circumferentially spaced blades define the venturi. Preferably, the undersurface of the lower annular body over at least a part of its radial width is inclined upwardly towards the vertical axis. The wind energy convertor will convert into mechanical energy the energy of a wind blowing in any direction and is capable of self-starting, irrespective of the direction of the wind.

    Abstract translation: 在垂直轴的风力发电机中，其包括由直立支撑件的最上部支撑的圆形涡轮机，围绕并与涡轮机同轴的定子包括位于涡轮机的上端附近和/或上方的上部环形体，并且具有最上表面， 其径向宽度的至少一部分向着垂直轴向下倾斜，下环形体定位在涡轮的下端附近和/或下方，并且在环形体之间纵向延伸，多个周向间隔开的叶片限定了 文丘里 优选地，下环形体的在其径向宽度的至少一部分上的下表面向着垂直轴线向上倾斜。 风能转换器将转换成机械能，风能在任何方向吹动，并且能够自启动，而不管风的方向如何。

    Blade
    28.
    发明授权
    Blade 有权
    刀

    公开(公告)号：US08668456B2

    公开(公告)日：2014-03-11

    申请号：US13267375

    申请日：2011-10-06

    Applicant: Nicholas M. Merriman ,  Simon Read

    Inventor： Nicholas M. Merriman ,  Simon Read

    IPC: F01D5/14 ,  F01D5/28 ,  F04D29/32 ,  F04D29/38 ,  F01D5/16

    CPC classification number: F01D5/147 ,  F01D5/16 ,  F01D5/282 ,  F04D29/324 ,  F04D29/38 ,  F04D29/382 ,  F05D2240/303 ,  Y10S416/50

    Abstract: A turbomachine blade having features arranged to initiate bending of the leading edge towards the pressure surface upon impact of a foreign object on the leading edge. The features may be features weaker than the material of the leading edge located on the pressure surface side of a mid-thickness line. By causing the leading edge to bend towards the pressure surface on impact the volume of the foreign object, typically a bird, that passes over the suction surface is reduced.

    Abstract translation: 一种涡轮机叶片，其具有布置成当外来物体在前缘上撞击时引导前缘朝向压力表面弯曲的特征。 特征可以是比位于中厚线的压力表面侧的前缘的材料更弱的特征。 通过在冲击时使前缘朝向压力表面弯曲，减小了越过吸力表面的异物（通常为鸟）的体积。

    Annulus filler
    29.
    发明授权
    Annulus filler 有权
    环形填料

    公开(公告)号：US08297931B2

    公开(公告)日：2012-10-30

    申请号：US12461111

    申请日：2009-07-31

    Applicant: Simon Read ,  Ewan F Thompson ,  Christopher S Brown

    Inventor： Simon Read ,  Ewan F Thompson ,  Christopher S Brown

    IPC: F01D5/02

    CPC classification number: F01D11/008 ,  F01D5/3007 ,  F02K3/06 ,  F05D2240/80

    Abstract: An annulus filler (101) is provided for mounting to a rotor disc (102) of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc (102). The annulus filler (101) has an outer part (106) which defines an airflow surface for air being drawn through the engine, and a separate, support part (105) which is connectable to the outer part (106) and to the rotor disc (102) to support the outer part (106) on the rotor disc (102). The outer (106) and support parts (105) are configured to allow a procedure for mounting the annulus filler (101) to the rotor disc (102). In a first step the support part (105) is connected to the rotor disc (102) without the outer part (106), and in a subsequent second step the outer part (106) is connected to the support part (105).

    Abstract translation: 提供了一种环形填料（101），用于安装到燃气涡轮发动机的转子盘（102）并用于桥接附接到转子盘（102）的两个相邻叶片之间的间隙。 环形填料（101）具有外部部分（106），其限定用于空气被引导通过发动机的气流表面，以及分开的支撑部分（105），其可连接到外部部分（106）和转子盘 （102）以支撑转子盘（102）上的外部部分（106）。 外部（106）和支撑部件（105）构造成允许将环形填料（101）安装到转子盘（102）上的过程。 在第一步骤中，支撑部分（105）没有外部部分（106）连接到转子盘（102），并且在随后的第二步骤中，外部部分（106）连接到支撑部分（105）。

    Blade for a gas turbine engine
    30.
    发明授权
    Blade for a gas turbine engine 有权
    燃气轮机的叶片

    公开(公告)号：US07972116B2

    公开(公告)日：2011-07-05

    申请号：US11826487

    申请日：2007-07-16

    Applicant: Simon Read ,  Sivasubramaniam K Sathianathan

    Inventor： Simon Read ,  Sivasubramaniam K Sathianathan

    IPC: F01D5/14 ,  B21D53/78

    CPC classification number: F04D29/388 ,  F01D5/147 ,  F01D5/3007 ,  F05D2230/23 ,  F05D2230/236 ,  F05D2230/25 ,  Y10T29/49337 ,  Y10T29/49339

    Abstract: A blade for a gas turbine engine includes an aerofoil portion and a root portion defined by concave and convex walls having opposing inner surfaces. A reinforcing member is located between the concave and convex walls and is bonded to the inner surfaces of the concave and convex walls, and the root portion includes an unbonded region in which the reinforcing member contacts an inner surface of one of the concave and convex walls but is not bonded to the concave and convex walls.

    Abstract translation: 用于燃气涡轮发动机的叶片包括机翼部分和由具有相对的内表面的凹凸壁限定的根部分。 加强构件位于凹凸壁之间并且被结合到凹壁和凸壁的内表面，并且根部包括非粘合区域，加强构件中的一个凹壁和凸壁的内表面 但不粘合到凹凸壁。

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