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    STATOR VANE SYSTEM USABLE WITHIN A GAS TURBINE ENGINE
    42.
    发明公开
    STATOR VANE SYSTEM USABLE WITHIN A GAS TURBINE ENGINE 有权
    定子叶片系统可在燃气涡轮发动机内使用

    公开(公告)号：EP3172410A1

    公开(公告)日：2017-05-31

    申请号：EP14753353.3

    申请日：2014-07-24

    申请人： Siemens Aktiengesellschaft

    发明人： GRIFFIN, Elliot

    IPC分类号： F01D9/04 ,  F01D25/24 ,  F01D11/00 ,  F01D11/12

    CPC分类号： F04D29/644 ,  F01D9/042 ,  F01D11/001 ,  F01D11/127 ,  F01D25/246 ,  F04D29/083 ,  F04D29/542 ,  F05D2230/64 ,  F05D2260/30 ,  F05D2300/505

    摘要： A stator assembly (10) usable in a gas turbine engine (12) and configured to restrain inner and outer endwalls (14, 16) to limit deflection and prevent clearance loss relative to adjacent blade rotor disks (18) is disclosed. The stator assembly (10) may be formed from a plurality of stator vanes (20) with inner and outer endwalls (14, 16) that are coupled together with a first radially outer tie bar (22). In at least one embodiment, first and second radially outer tie bars (22, 24) may form first and second stator vane segments (26, 28) that together form the circumferentially extending stator assembly (10). The inner and outer endwalls (14, 16) may be coupled together with one or more circumferentially extending alignment pins (30) that limit deflection. The stator assembly (10) may include one more deformable seals (52) extending radially inward from the inner endwall (14).

    摘要翻译： 1。一种用于燃气涡轮发动机（12）的定子组件（10），包括：多个定子叶片（20），每个定子叶片由具有前缘（36​​），后缘（38）的大体细长的翼面（34） ，压力侧（40），吸力侧（42），联接到第一端（44）的内端壁（14）和联接到与第一端（44）相对的第二端（46）的外端壁（16） ）; 连接到所述定子叶片（20）的一部分的每个外端壁（16）的第一径向外部连杆（22）; 至少一个内部对齐销（48），其在相邻的内部端壁（14）之间延伸以将相邻的内部端壁（14）连接在一起; 至少一个附接到内端壁（14）的前部内密封环（50）; 和至少一个可变形密封件（52），所述至少一个可变形密封件（52）联接至所述前部内部密封环（50）的至少一个径向内表面（54），其中所述至少一个可变形密封件（52）包括面向上游的接触表面（110） 径向面向内的接触表面（112）。

    SHAPE MEMORY ALLOY-ACTUATED PROPELLER BLADES AND SHAPE MEMORY ALLOY-ACTUATED PROPELLER ASSEMBLIES
    44.
    发明公开
    SHAPE MEMORY ALLOY-ACTUATED PROPELLER BLADES AND SHAPE MEMORY ALLOY-ACTUATED PROPELLER ASSEMBLIES 审中-公开
    FORMGEDÄCHTNISLEGIERUNGSBETÄTIGTEPROPELLERBLÄTTERFORFORMGEDÄCHTNISLEGIERUNGSBETÄTIGTEPROPELLERANORDNUNGEN

    公开(公告)号：EP3127804A1

    公开(公告)日：2017-02-08

    申请号：EP16171216.1

    申请日：2016-05-25

    申请人： The Boeing Company

    发明人： Bigbee-Bansen, William J. ,  Clingman, Dan J. ,  Mabe, James H.

    IPC分类号： B64C11/30 ,  B64C11/44

    CPC分类号： B64C11/06 ,  B64C11/20 ,  B64C11/30 ,  B64C11/44 ,  B64C2027/7288 ,  F05D2300/505 ,  Y02T50/34

    摘要： Shape memory alloy-actuated propeller blades and shape memory alloy-actuated propeller assemblies are disclosed. An example propeller blade includes a propeller body (212), a plate (222) coupled to the propeller body (212), a torque transfer member (220), and a shape memory alloy (SMA) actuator (218). The torque transfer member (220) has a distal end attached to the plate (222) such that the torque transfer member (220) applies to the plate (222) at least a portion of a torque applied to the torque transfer member (220) at a proximal end ofthe torque transfer member (220). The SMA actuator (218) has a distal end and a proximal end. The distal end of the SMA actuator (218) is attached to the torque transfer member. (220) The proximal end ofthe SMA actuator (218) is coupled to the propeller body (212) such that the distal end is mated to the propeller body. (212) The SMA actuator (218)is configured to apply the torque to the proximal end of the torque transfer member (220) in response to an application of heat to the SMA actuator (218).

    摘要翻译： 公开了形状记忆合金致动的螺旋桨叶片和形状记忆合金致动的螺旋桨组件。 示例性螺旋桨叶片包括螺旋桨体（212），联接到螺旋桨体（212）的板（222），扭矩传递构件（220）和形状记忆合金（SMA）致动器（218）。 转矩传递构件（220）具有附接到板（222）的远端，使得扭矩传递构件（220）向施加到扭矩传递构件（220）的扭矩的至少一部分施加到板（222） 在扭矩传递构件（220）的近端处。 SMA致动器（218）具有远端和近端。 SMA致动器（218）的远端附接到扭矩传递构件。 （220）SMA致动器（218）的近端联接到螺旋桨体（212），使得远端与螺旋桨体配合。 （212）SMA致动器（218）被配置为响应于向SMA致动器（218）施加热量而将扭矩施加到转矩传递构件（220）的近端。

    Shape memory alloy actuation system for variable area fan nozzle
    47.
    发明公开
    Shape memory alloy actuation system for variable area fan nozzle 有权
    BetätigungssystemmitFormgedächtnislegierungfürFandüsemit variablem Querschnitt

    公开(公告)号：EP2803844A1

    公开(公告)日：2014-11-19

    申请号：EP14157118.2

    申请日：2014-02-28

    申请人： The Boeing Company

    发明人： Jasklowski, Christopher T.

    IPC分类号： F02K1/12 ,  F02K1/18

    CPC分类号： F03G7/065 ,  F02K1/1207 ,  F02K1/805 ,  F05D2300/505 ,  Y02T50/672

    摘要： A variable area fan nozzle comprising an array of hinged rigid petals and a petal actuation system in which the principle of actuation is realized by changes in shape (i.e., deformation) of the actuators rather than by movement of cooperating mechanical parts. Because these actuators have no rotating or sliding mechanical components, wear and associated maintenance are reduced. Each deformable actuator has a portion made of shape memory alloy that has been trained to change shape in a specific manner when heated to a temperature above a transition temperature. In addition, each shape memory alloy actuator is shaped to act as a fairing to reduce aerodynamic drag.

    摘要翻译： 一种可变区域风扇喷嘴，其包括铰接的刚性花瓣和花瓣致动系统的阵列，其中致动原理通过致动器的形状（即变形）的变化而不是由协作的机械部件的移动来实现。 因为这些致动器没有旋转或滑动的机械部件，因此减少了磨损和相关的维护。 每个可变形的致动器具有由形状记忆合金制成的部分，当被加热到高于转变温度的温度时，其已被训练成以特定方式改变形状。 此外，每个形状记忆合金致动器成形为用作整流罩以减小气动阻力。

    Exhaust strut with leading edge formed of shape memory alloy
    49.
    发明公开
    Exhaust strut with leading edge formed of shape memory alloy 审中-公开
    形状记忆合金的排气气体支柱前缘

    公开(公告)号：EP2623715A3

    公开(公告)日：2014-06-11

    申请号：EP12198399.3

    申请日：2012-12-20

    申请人： General Electric Company

    发明人： Keny, Mayur Abhay ,  Subbareddyar, Thangaraj ,  Sundaram, Hariharan

    IPC分类号： F01D5/14 ,  F01D5/28

    CPC分类号： F01D5/148 ,  F01D5/28 ,  F05D2300/505

    摘要： An exhaust strut (20) is provided and includes a body (30) having an airfoil-shaped cross-section (31) defining a lead edge portion (32) and a trailing edge portion (33) opposite the lead edge portion (32), the lead edge portion (32) and the trailing edge portion (33) being connected by a pressure side (34) and a suction side (35) opposite the pressure side (34), at least the lead edge portion (32) and respective sections of the pressure side (34) and the suction side (35) proximate to the lead edge portion (32) being formed of shape memory alloy, and a temperature control system (40) operably disposed at the lead edge portion (32) and the respective sections of the pressure side (34) and the suction side (35) proximate to the lead edge portion (32) to modify a temperature of the shape memory alloy.