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    GAS TURBINE HUB
    1.
    发明申请
    GAS TURBINE HUB 审中-公开

    公开(公告)号：WO2015020715A3

    公开(公告)日：2015-02-12

    申请号：PCT/US2014/039091

    申请日：2014-05-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： BURD, Steven W. ,  HARRIS, Meggan ,  OLS, John T. ,  ASKEY, William G.

    IPC: F01D5/02 ,  F01D5/30

    Abstract: A unitary one-piece hub has first and second rings and a midsection arranged between the first and second rings. The midsection includes a plurality of windows configured to receive a plurality of cross members. The windows include a lip configured to surround the cross members. A gas turbine engine and a method of providing a hub for a gas turbine engine are also disclosed.

    DIVERGENT FLAP
    2.
    发明申请
    DIVERGENT FLAP 审中-公开

    公开(公告)号：WO2015112554A1

    公开(公告)日：2015-07-30

    申请号：PCT/US2015/012180

    申请日：2015-01-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： HARRIS, Meggan

    IPC: F02K1/12 ,  B64D33/04

    CPC classification number: F02K1/1223 ,  B64D33/04 ,  F02K1/12 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2230/30 ,  F05D2230/31 ,  F05D2240/128 ,  F05D2260/202 ,  Y02T50/675

    Abstract: A divergent flap includes a hinge joint to connect the divergent flap to a convergent flap, a plow structure, a first wall, a second wall, and two side walls. The plow structure is at a plow end of the flap opposite the hinge joint. The first wall and the second wall each extend from the hinge joint to the plow end. The second wall is spaced apart from the first wall by the two side walls to form at least one cooling channel extending between the hinge joint and the plow end. The divergent flap is integrally formed in layer-by-layer fashion as a single piece.

    Abstract translation: 发散片包括铰链接头，用于将发散片连接到收敛片，犁结构，第一壁，第二壁和两个侧壁。 犁式结构位于翼片的与铰链接头相对的犁端。 第一壁和第二壁各自从铰链接头延伸到犁端。 第二壁通过两个侧壁与第一壁间隔开，以形成在铰链接头和犁端之间延伸的至少一个冷却通道。 发散片整体形成为一体的单层。

    SWIRLER MOUNT INTERFACE FOR GAS TURBINE ENGINE COMBUSTOR
    3.
    发明申请
    SWIRLER MOUNT INTERFACE FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    燃气轮机燃烧器的SWIRLER MOUNT接口

    公开(公告)号：WO2015053818A2

    公开(公告)日：2015-04-16

    申请号：PCT/US2014/038214

    申请日：2014-05-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： DRAKE, Christopher ,  MAX, Seth A. ,  HARRIS, Meggan

    IPC: F23R3/14

    CPC classification number: F23R3/14 ,  B23P19/00 ,  F23R3/002 ,  F23R3/283 ,  F23R2900/00012 ,  Y02T50/675

    Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a swirler threaded section defined around a swirler central longitudinal axis. A bulkhead support shell for a combustor of a gas turbine engine includes a swirler boss with a boss threaded section defined around a swirler central longitudinal axis. A combustor of a gas turbine engine includes a bulkhead support shell with a swirler boss. The combustor also includes a swirler mountable to the swirler boss at a threaded interface defined around a swirler central longitudinal axis.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的旋流器包括具有围绕旋流器中心纵向轴线限定的旋流器螺纹部分的旋流器外体。 用于燃气涡轮发动机的燃烧器的隔板支撑壳体包括具有围绕旋流器中心纵向轴线限定的凸台螺纹部分的旋流器凸台。 燃气涡轮发动机的燃烧器包括具有旋流器凸台的隔壁支撑壳体。 燃烧器还包括旋流器，该旋流器可安装在旋流器中心纵轴周围的螺纹接口处的旋流器轴套上。

    STRUCTURAL HONEYCOMB PANEL
    4.
    发明申请
    STRUCTURAL HONEYCOMB PANEL 审中-公开
    结构蜂窝板

    公开(公告)号：WO2015130377A2

    公开(公告)日：2015-09-03

    申请号：PCT/US2014/069289

    申请日：2014-12-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： HARRIS, Meggan

    IPC: F01D25/24 ,  F01D25/12 ,  F02C7/12 ,  F02C7/20 ,  F16S1/00

    CPC classification number: F01D9/02 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/10 ,  B22F2207/11 ,  B33Y10/00 ,  B33Y80/00 ,  F01D25/12 ,  F01D25/24 ,  F02C7/24 ,  F02K1/822 ,  F05D2220/32 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2230/53 ,  F05D2250/132 ,  F05D2250/283 ,  F05D2250/314 ,  F05D2260/202 ,  Y02P10/295 ,  Y02T50/671 ,  Y02T50/675

    Abstract: A structural panel for use with a gas turbine engine includes a first exterior wall, a second exterior wall, and interior walls. The first exterior wall includes a first exterior surface and a first interior surface parallel to the first exterior surface. The second exterior wall includes a second exterior surface and a second interior surface parallel to the second exterior surface. The interior walls extend from the first interior surface to the second interior surface. The interior walls are arranged to form a pattern of hexagonal cells. The pattern of hexagonal cells includes cell groups having a variation in structural strength such that at least one of the cell groups has a structural strength that is not the same as the remaining cell groups.

    Abstract translation: 用于燃气涡轮发动机的结构板包括第一外壁，第二外壁和内壁。 第一外壁包括第一外表面和平行于第一外表面的第一内表面。 第二外壁包括第二外表面和平行于第二外表面的第二内表面。 内壁从第一内表面延伸到第二内表面。 内壁排列成六角形格子的图案。 六角形细胞的图案包括具有结构强度变化的细胞群，使得至少一个细胞群具有与剩余细胞群不同的结构强度。

    HEAT-SHIELDED CONDUIT
    7.
    发明申请
    HEAT-SHIELDED CONDUIT 审中-公开
    加热管道

    公开(公告)号：WO2015089033A1

    公开(公告)日：2015-06-18

    申请号：PCT/US2014/069284

    申请日：2014-12-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： HARRIS, Meggan

    IPC: F16L9/18 ,  F16L59/14

    CPC classification number: F28D7/10 ,  B23P15/26 ,  B33Y80/00 ,  F16L9/18 ,  F16L53/70 ,  F16L59/12 ,  F16L59/123 ,  F16L59/143 ,  F28D7/106 ,  F28F1/003 ,  F28F13/08 ,  F28F2240/00 ,  F28F2265/10

    Abstract: A heat-shielded conduit includes a tube, a heat shield, and a truss structure. The tube has a tube inner diameter and a tube outer diameter. The heat shield radially surrounds the tube. The heat shield has a shield inner diameter greater than the tube outer diameter to form a first gap between the heat shield and the tube. The truss structure is integrally formed together with both of the tube and the heat shield to space the shield inner diameter from the tube outer diameter and maintain the first gap.

    Abstract translation: 隔热导管包括管，隔热罩和桁架结构。 管具有管内径和管外径。 隔热罩径向包围管子。 隔热罩具有大于管外径的屏蔽内径，以在隔热罩和管之间形成第一间隙。 桁架结构与管和隔热罩一体形成，以使屏蔽内径与管外径隔开并保持第一间隙。

    VARIABLE OUTER AIR SEAL SUPPORT
    8.
    发明申请
    VARIABLE OUTER AIR SEAL SUPPORT 审中-公开
    可变的外部密封支持

    公开(公告)号：WO2014123601A2

    公开(公告)日：2014-08-14

    申请号：PCT/US2013/071429

    申请日：2013-11-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： HARRIS, Meggan

    CPC classification number: F01D11/22 ,  F01D25/24 ,  F01D25/246

    Abstract: A variable outer air seal support system according to an exemplary aspect of the present disclosure includes, among other things, a case having a plurality of slots, and an extension of a variable outer air seal segment. The extension provides at least one extension aperture. A connector pin is configured to move within the slot to move the variable outer air seal segment from a first position to a second position. The variable outer air seal segment overlaps a circumferentially adjacent variable outer air seal segment more in the first position than in the second position.

    Abstract translation: 根据本公开的示例性方面的可变外部空气密封支撑系统尤其包括具有多个狭槽的壳体和可变外部空气密封段的延伸部。 延伸部至少提供一个延伸孔。 连接器销构造成在槽内移动以将可变外部空气密封段从第一位置移动到第二位置。 可变外部空气密封段在第一位置比在第二位置更多地与周向相邻的可变外部空气密封段重叠。

    VARIABLE BLADE OUTER AIR SEAL
    10.
    发明申请
    VARIABLE BLADE OUTER AIR SEAL 审中-公开
    可变叶片外密封

    公开(公告)号：WO2014031198A2

    公开(公告)日：2014-02-27

    申请号：PCT/US2013/042447

    申请日：2013-05-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： HARRIS, Meggan

    IPC: F01D11/08 ,  F01D25/24 ,  F02C7/20

    CPC classification number: F01D11/22 ,  F01D17/08 ,  F01D17/085 ,  F01D17/143 ,  F02C9/16 ,  F05D2240/11 ,  F05D2250/38 ,  F05D2260/57 ,  F05D2270/20 ,  F05D2270/301 ,  F05D2270/303 ,  F05D2270/44

    Abstract: A system for a turbofan has a variable outer air seal, an actuator coupled to the variable outer air seal, a sensor positioned inside the turbofan for sensing an engine parameter, and a flight controller connected to the turbofan for receiving the parameter from the sensor. The flight controller directs the actuator to regulate the position of the actuator based on the flight condition resulting form the received parameter.

    Abstract translation: 用于涡轮风扇的系统具有可变的外部空气密封件，联接到可变外部空气密封件的致动器，位于涡轮风扇内部以用于感测发动机参数的传感器，以及连接到涡轮风扇以用于从传感器接收参数的飞行控制器。 飞行控制器根据从接收到的参数形成的飞行条件，引导执行机构调节执行机构的位置。

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