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    BLADE TIP CLEARANCE SYSTEMS
    1.
    发明申请
    BLADE TIP CLEARANCE SYSTEMS 审中-公开
    刀尖间隙系统

    公开(公告)号：WO2015130355A3

    公开(公告)日：2015-10-22

    申请号：PCT/US2014066304

    申请日：2014-11-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DAVIS TIMOTHY M ,  PAULINO JOSE R ,  DUGUAY BRIAN

    IPC: F01D11/08 ,  F01D11/18

    CPC classification number: F01D11/18 ,  F01D5/02 ,  F01D5/12 ,  F01D11/24 ,  F05D2220/32 ,  F05D2260/22141 ,  F05D2300/5021 ,  F05D2300/50212 ,  Y02T50/676

    Abstract: A blade tip clearance system includes first and second control rings. The first control ring has a first coefficient of thermal expansion (CTE) and a first thermal response rate. The second control ring is located radially outward of and operatively connected to the first control ring and has a second CTE that is different from the first CTE and a second thermal response rate that is different from the first thermal response rate. Thermal expansion and contraction of the first and the second control rings controls a radial position of the blade tip clearance system relative to a rotating blade component.

    Abstract translation: 叶片顶端间隙系统包括第一和第二控制环。 第一控制环具有第一热膨胀系数（CTE）和第一热响应速率。 第二控制环位于第一控制环的径向外部并且可操作地连接到第一控制环，并且具有不同于第一CTE的第二CTE和与第一热响应速率不同的第二热响应速率。 第一和第二控制环的热膨胀和收缩控制叶片顶端间隙系统相对于旋转叶片部件的径向位置。

    GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM
    2.
    发明申请
    GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM 审中-公开
    燃气轮机发动机快速响应间隙控制系统

    公开(公告)号：WO2015069328A3

    公开(公告)日：2015-07-23

    申请号：PCT/US2014047836

    申请日：2014-07-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DAVIS TIMOTHY M ,  DUGUAY BRIAN

    IPC: F01D11/22 ,  F02C7/28

    CPC classification number: F01D11/22 ,  F01D11/08 ,  F01D11/14 ,  F04D29/164 ,  F05D2220/32 ,  F05D2260/50 ,  F05D2270/60

    Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a sync ring with a multiple of graduation sets. Each of the graduation sets is associated with one of the multiple of blade outer air seal assemblies. An active clearance control system of a gas turbine engine includes a sync ring with a multiple of graduation sets. Each of the graduation sets includes a multiple of graduations to define an associated radial position for each of a respective multiple of blade outer air seal assemblies.

    Abstract translation: 燃气涡轮发动机的主动间隙控制系统包括多个叶片外部气密封组件和具有多个分度组的同步环。 每个分度组与多个叶片外部气密封组件中的一个相关联。 燃气涡轮发动机的主动间隙控制系统包括具有多个分度组的同步环。 每个刻度组包括多个刻度，以为叶片外部气封组件的相应多个中的每一个限定相关联的径向位置。

    RADIAL POSITION CONTROL OF CASE SUPPORT STRUCTURE WITH SPLINED CONNECTION
    3.
    发明申请
    RADIAL POSITION CONTROL OF CASE SUPPORT STRUCTURE WITH SPLINED CONNECTION 审中-公开
    采用分层连接的箱体支撑结构的径向位置控制

    公开(公告)号：WO2015047478A3

    公开(公告)日：2015-06-11

    申请号：PCT/US2014042840

    申请日：2014-06-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ROMANOV DMITRIY A ,  DUGUAY BRIAN

    IPC: F02C7/20 ,  F01D25/28

    CPC classification number: F01D11/18 ,  F01D11/12 ,  F01D25/246 ,  F01D25/28 ,  F02C7/20 ,  F05D2240/14 ,  F05D2240/55 ,  F05D2240/80 ,  Y02T50/672

    Abstract: A radial position control assembly for a gas turbine engine includes a case structure. A support structure is operatively supported by the case structure respectively with first and second splines in engagement with one another. The support structure includes an annular recess, and a support ring is received in the recess. The support structure and the support ring having different coefficients of thermal expansion. An axial biasing member urges the first and second splines into engagement with one another.

    Abstract translation: 用于燃气涡轮发动机的径向位置控制组件包括壳体结构。 支撑结构分别通过第一花键和第二花键彼此接合而被壳体结构可操作地支撑。 支撑结构包括环形凹槽，并且支撑环容纳在凹槽中。 支撑结构和支撑环具有不同的热膨胀系数。 轴向偏置构件推动第一花键和第二花键彼此接合。

    ACTUATOR FOR GAS TURBINE ENGINE BLADE OUTER AIR SEAL
    8.
    发明申请
    ACTUATOR FOR GAS TURBINE ENGINE BLADE OUTER AIR SEAL 审中-公开
    气动涡轮发动机叶片外空气密封件执行器

    公开(公告)号：WO2014186015A2

    公开(公告)日：2014-11-20

    申请号：PCT/US2014016768

    申请日：2014-02-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DUGUAY BRIAN

    CPC classification number: F01D11/20 ,  F01D11/08 ,  F01D11/22 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2260/57

    Abstract: A blade outer air seal (BOAS) actuator assembly, according to an exemplary aspect of the present disclosure includes, among other things, an actuator member; and a retractor configured to move with the actuator member to move a BOAS segment from a first position to a second position that is radially outside the first position, the BOAS segment seated against a support structure when in the first position and spaced from the support structure when in the second position.

    Abstract translation: 根据本公开的示例性方面的叶片外部空气密封（BOAS）致动器组件尤其包括致动器构件; 以及牵开器，其构造成与所述致动器构件一起移动以将BOAS段从第一位置移动到径向位于所述第一位置的第二位置，所述BOAS段在处于所述第一位置时抵靠支撑结构抵靠并与所述支撑结构间隔开 当在第二个位置。

    ACTUATOR FOR GAS TURBINE ENGINE BLADE OUTER AIR SEAL
    10.
    发明公开
    ACTUATOR FOR GAS TURBINE ENGINE BLADE OUTER AIR SEAL 审中-公开
    燃气轮机叶片外部密封组件可调

    公开(公告)号：EP2971592A4

    公开(公告)日：2016-11-09

    申请号：EP14797409

    申请日：2014-02-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DUGUAY BRIAN

    IPC: F01D11/20 ,  F01D11/08 ,  F01D11/22 ,  F02C7/28 ,  F04D29/08

    CPC classification number: F01D11/20 ,  F01D11/08 ,  F01D11/22 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2260/57

    Abstract: A blade outer air seal (BOAS) actuator assembly, according to an exemplary aspect of the present disclosure includes, among other things, an actuator member; and a retractor configured to move with the actuator member to move a BOAS segment from a first position to a second position that is radially outside the first position, the BOAS segment seated against a support structure when in the first position and spaced from the support structure when in the second position.

    Abstract translation: 根据本公开的示例性方面的叶片外部空气密封（BOAS）致动器组件包括致动器构件; 以及牵开器，其构造成与所述致动器构件一起移动以将BOAS段从第一位置移动到位于所述第一位置的径向外侧的第二位置，所述BOAS段在处于所述第一位置时与所述支撑结构抵靠并与所述支撑结构间隔开 当处于第二位置时。

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