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    ROTOR WITH BLADES SECURED BY WOVEN FIBER ATTACHMENT SYSTEM
    14.
    发明授权
    ROTOR WITH BLADES SECURED BY WOVEN FIBER ATTACHMENT SYSTEM 有权
    带刀片的刀片通过机织纤维附着系统保护

    公开(公告)号：EP3029271B1

    公开(公告)日：2018-02-28

    申请号：EP15196128.1

    申请日：2015-11-24

    Applicant: United Technologies Corporation

    Inventor： BIFULCO, Anthony R. ,  BROWN, Damon ,  AIELLO, Nicholas

    IPC: F01D5/30 ,  F01D5/28

    CPC classification number: B23P15/006 ,  F01D5/282 ,  F01D5/34 ,  F05D2300/6033 ,  Y02T50/673

    Abstract: A propulsive engine rotor (110) configured for operation within a gas turbine includes a plurality of spaced airfoil blades (120) circumferentially affixed to an outer hoop-style rim (122). At least two of the airfoil blades (120) have an integral root (140) configured to extend either through or at least radially inwardly from the rim (122). A woven fiber system provides that the blade roots (140) are interdigitally wrapped by a plurality of woven fibers (132) before impregnation and/or encapsulation of the fibers (132) and wrapped roots (140) within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor (110), includes a bore (116) through which passes the rotational axis of the rotor (110), and has a lower mass than the rotor rim (122). The woven fiber interface between the roots (140) increases the tensile load capacity of the airfoil blades (120) relative to the composite ring, and increases the self-sustaining radius of the rotor (110).

    ROTOR WITH BLADES SECURED BY WOVEN FIBER ATTACHMENT SYSTEM
    17.
    发明公开
    ROTOR WITH BLADES SECURED BY WOVEN FIBER ATTACHMENT SYSTEM 有权
    转子叶片通过连接系统由编织纤维是受保护

    公开(公告)号：EP3029271A1

    公开(公告)日：2016-06-08

    申请号：EP15196128.1

    申请日：2015-11-24

    Applicant: United Technologies Corporation

    Inventor： BIFULCO, Anthony R. ,  BROWN, Damon ,  AIELLO, Nicholas

    IPC: F01D5/30 ,  F01D5/28

    CPC classification number: B23P15/006 ,  F01D5/282 ,  F01D5/34 ,  F05D2300/6033

    Abstract: A propulsive engine rotor (110) configured for operation within a gas turbine includes a plurality of spaced airfoil blades (120) circumferentially affixed to an outer hoop-style rim (122). At least two of the airfoil blades (120) have an integral root (140) configured to extend either through or at least radially inwardly from the rim (122). A woven fiber system provides that the blade roots (140) are interdigitally wrapped by a plurality of woven fibers (132) before impregnation and/or encapsulation of the fibers (132) and wrapped roots (140) within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor (110), includes a bore (116) through which passes the rotational axis of the rotor (110), and has a lower mass than the rotor rim (122). The woven fiber interface between the roots (140) increases the tensile load capacity of the airfoil blades (120) relative to the composite ring, and increases the self-sustaining radius of the rotor (110).

    Abstract translation: 燃气涡轮机内配置用于操作的推进发动机转子（110）包括间隔开的翼型叶片（120）在外侧箍式边缘（122）沿周向贴在复数。 中的至少两个的翼型叶片（120）的具有一体地配置的根（140）无论是通过或至少径向地从轮辋（122）向内延伸。 一种编织纤维系统提供做的叶片根部（140）叉指由陶瓷或其它复合基质材料内的纤维（132）和缠绕的根（140）的浸渍和/或封装之前编织纤维（132）的多元性包裹 以形成复合材料环。 该复合环定义转子（110）的内部主体包括孔（116），通过它经过所述转子（110）的旋转轴线，并具有比转子轮缘（122）一个较低的质量。 根部（140）之间的织造纤维界面增加了翼型叶片的拉伸负荷能力（120）相对于所述复合材料环，并增大了转子（110）的自持半径。

    REINFORCED GAS TURBINE ENGINE ROTOR DISK
    18.
    发明公开
    REINFORCED GAS TURBINE ENGINE ROTOR DISK 有权
    VERSTÄRKTEGASTURBINENMOTORROTORSCHEIBE

    公开(公告)号：EP3020918A1

    公开(公告)日：2016-05-18

    申请号：EP15195023.5

    申请日：2015-11-17

    Applicant: United Technologies Corporation

    Inventor： BIFULCO, Anthony R. ,  BROWN, Damon K. ,  AIELLO, Nicholas

    IPC: F01D5/02 ,  F01D5/06

    CPC classification number: F01D5/02 ,  F01D5/06 ,  F01D5/34 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/60 ,  F05D2240/20 ,  F05D2240/35 ,  F05D2300/224 ,  F05D2300/48 ,  F05D2300/603 ,  F05D2300/6032 ,  F05D2300/614 ,  Y02T50/672

    Abstract: A structurally-reinforced rotor disk (56) for a gas turbine engine (10) is disclosed. The rotor disk (56) may comprise a body (57) including a rim (58) configured to support airfoils (54) (which may be separate or integral with the airfoils), an axially-extending bore (60) disposed radially inward of the rim (58), and a radially-extending web (64) connecting the rim (58) and the bore (60). The bore (60) may include an axial outer edge (76) and at least one circumferentially-extending annular recess (70) formed axially between the outer edge (76) and the web (64). The rotor disk (56) may further comprise an annular ring (68) retained in the annular recess (70), and the annular ring (68) may be formed from a different material than the body (57) of the rotor disk (56) so as to increase a self-sustaining radius (SSR) of the rotor disk (56).

    Abstract translation: 公开了一种用于燃气涡轮发动机（10）的结构增强转子盘（56）。 转子盘（56）可以包括主体（57），其包括构造成支撑翼型件（54）（其可以与翼型件分离或一体的）的边缘（58），轴向延伸的孔（60） 边缘（58）和连接边缘（58）和孔（60）的径向延伸的腹板（64）。 孔（60）可以包括轴向外边缘（76）和至少一个在外缘（76）和腹板（64）之间轴向形成的周向延伸的环形凹部（70）。 转子盘（56）还可以包括保持在环形凹部（70）中的环形环（68），并且环形环（68）可以由与转子盘（56）的主体（57）不同的材料形成 ）以增加转子盘（56）的自持半径（SSR）。

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