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    CARRIER INTERLOCK
    1.
    发明申请
    CARRIER INTERLOCK 审中-公开

    公开(公告)号：WO2014116342A3

    公开(公告)日：2014-10-16

    申请号：PCT/US2013069523

    申请日：2013-11-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MCCAFFREY MICHAEL G ,  ROUSE BRANDON T

    IPC: F01D11/08 ,  F02C7/28

    CPC classification number: F01D11/08 ,  F01D9/04

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an engine case, a rotor stage including a plurality of rotor blades, a plurality of carriers for supporting a plurality of blade outer air seals and an interlock formed between circumferential ends of a first adjacent carrier and a second adjacent carrier of the plurality of carriers.

    Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括发动机壳体，包括多个转子叶片的转子级，用于支撑多个叶片外部空气密封件的多个载体和形成的互锁件 在第一相邻载体的圆周端和多个载体的第二相邻载体之间。

    RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE WITH AXIAL REACTION MEMBER
    2.
    发明申请
    RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE WITH AXIAL REACTION MEMBER 审中-公开
    轴向反力构件箱体支承结构的径向位置控制

    公开(公告)号：WO2015023321A2

    公开(公告)日：2015-02-19

    申请号：PCT/US2014033149

    申请日：2014-04-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MCCAFFREY MICHAEL G ,  ROUSE BRANDON T ,  BORJA MARK ,  GARCIA IGOR S ,  FARRIS JOHN R ,  ALMY THOMAS ,  PELLETIER BRIAN R

    IPC: F01D11/22 ,  F02C7/28

    CPC classification number: F01D11/08 ,  F01D9/04 ,  F01D11/12 ,  F01D11/14 ,  F01D11/20 ,  F01D11/22 ,  F01D11/24 ,  F01D25/24 ,  Y02T50/672

    Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.

    Abstract translation: 用于燃气轮机发动机级的径向位置控制组件包括壳体结构。 受支持的结构由壳体结构可操作地支撑。 支撑环可操作地支撑被支撑的结构。 支撑结构和支撑环具有不同的热膨胀系数。 密封结构与支撑结构相邻。 支撑环基于相邻支撑结构之间的周向间隙并且基于支撑环与支撑结构之间的径向间隙，在热瞬变期间在间隙处相对于密封结构保持支撑结构。 销相对于壳体结构支撑被支撑的结构，并被配置为将支撑环与被支撑结构上的载荷隔离。

    BLADE OUTER AIR SEAL SYSTEM FOR CONTROLLED TIP CLEARANCE
    4.
    发明申请
    BLADE OUTER AIR SEAL SYSTEM FOR CONTROLLED TIP CLEARANCE 审中-公开
    用于控制喷嘴间隙的叶片外部空气密封系统

    公开(公告)号：WO2014133644A3

    公开(公告)日：2014-11-27

    申请号：PCT/US2013075273

    申请日：2013-12-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MCCAFFREY MICHAEL G ,  ROUSE BRANDON T ,  ALMY THOMAS ,  GARCIA IGOR S ,  FARRIS JOHN R ,  BORJA MARK

    IPC: F01D11/18 ,  F02C7/28 ,  F04D29/08

    CPC classification number: F01D11/18 ,  F05D2240/11 ,  F05D2300/50212 ,  Y02T50/671

    Abstract: A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75 -175% of the second coefficient of thermal expansion.

    Abstract translation: 用于燃气涡轮发动机的叶片外部空气密封系统包括由具有第一热膨胀系数的第一材料制成的多个环载体。 多个密封段分别承载在多个环形托架上。 环形部件被承载在多个环形托架中。 环构件由与构成中的第一材料不同的第二材料构成。 第二材料具有第二热膨胀系数，使得第一热膨胀系数是第二热膨胀系数的75-175％。

    CARRIER INTERLOCK
    7.
    发明公开
    CARRIER INTERLOCK 审中-公开
    载波锁定

    公开(公告)号：EP2920428A4

    公开(公告)日：2016-01-06

    申请号：EP13872958

    申请日：2013-11-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MCCAFFREY MICHAEL G ,  ROUSE BRANDON T

    IPC: F01D11/08 ,  F01D9/04 ,  F02C7/28

    CPC classification number: F01D11/08 ,  F01D9/04

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an engine case, a rotor stage including a plurality of rotor blades, a plurality of carriers for supporting a plurality of blade outer air seals and an interlock formed between circumferential ends of a first adjacent carrier and a second adjacent carrier of the plurality of carriers.

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