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    LOW PROFILE COMPRESSOR BLEED AIR-OIL COOLERS
    1.
    发明申请
    LOW PROFILE COMPRESSOR BLEED AIR-OIL COOLERS 审中-公开
    低型压缩机压缩空气冷却器

    公开(公告)号：WO2014081493A2

    公开(公告)日：2014-05-30

    申请号：PCT/US2013057080

    申请日：2013-08-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNAPE NATHAN ,  SUCIU GABRIEL L ,  PICKFORD SIMON ,  PENDA ALLAN R

    IPC: F02C7/18 ,  F02C6/08

    CPC classification number: F02C6/08 ,  F02C7/14 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/675

    Abstract: An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.

    Abstract translation: 公开了一种用于燃气涡轮发动机的空气 - 油冷却器（AOC）。 AOC可以包括进油口，出油口以及进油口和出油口之间的热交换元件。 AOC可以纵向定位在发动机的风扇和V形槽之间，并且在低压压缩机和低压压缩机面板之间径向间隔开。 公开了一种包括AOC的燃气涡轮发动机。 发动机的AOC可以包括进油口，出油口和进油口和出油口之间的热交换元件。 发动机的AOC可以纵向地定位在发动机的风扇和V形槽之间，并且在低压压缩机和低压压缩机板之间径向间隔开。 还公开了一种操作用于燃气涡轮发动机的AOC的方法。

    LOW PROFILE COMPRESSOR BLEED AIR-OIL COOLERS
    2.
    发明申请
    LOW PROFILE COMPRESSOR BLEED AIR-OIL COOLERS 审中-公开

    公开(公告)号：WO2014081493A3

    公开(公告)日：2014-07-17

    申请号：PCT/US2013057080

    申请日：2013-08-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNAPE NATHAN ,  SUCIU GABRIEL L ,  PICKFORD SIMON ,  PENDA ALLAN R

    IPC: F02C7/141

    CPC classification number: F02C6/08 ,  F02C7/14 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/675

    Abstract: An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.

    POWER CABLE AND CONNECTOR ARRANGEMENT FOR A GAS TURBINE ENGINE
    4.
    发明申请
    POWER CABLE AND CONNECTOR ARRANGEMENT FOR A GAS TURBINE ENGINE 审中-公开
    燃气涡轮发动机的电力电缆和连接器装置

    公开(公告)号：WO2014092835A3

    公开(公告)日：2014-08-21

    申请号：PCT/US2013061333

    申请日：2013-09-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LIOR RAPHAEL ,  SNAPE NATHAN

    IPC: F01D25/28 ,  F01D25/00 ,  F02C7/00

    CPC classification number: F02C7/00 ,  F05D2220/76 ,  F05D2230/72 ,  F05D2260/30 ,  Y10T29/49229

    Abstract: A gas turbine engine component assembly according to an exemplary aspect of the present disclosure includes, among other things, a nacelle including a moveable portion. A generator is configured to be received within a space established by the nacelle. A plurality of cables are at least partially supported on the moveable portion of the nacelle, the plurality of cables being selectively electrically coupled with the generator.

    Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机部件组件包括其中包括包括可移动部分的机舱。 发电机被配置为接收在由机舱建立的空间内。 多个电缆至少部分地支撑在机舱的可移动部分上，多个电缆选择性地与发电机电耦合。

    GAS TURBINE ENGINE OIL TANK
    7.
    发明公开
    GAS TURBINE ENGINE OIL TANK 有权
    燃气涡轮发动机滑油

    公开(公告)号：EP2847448A4

    公开(公告)日：2015-12-23

    申请号：EP13787212

    申请日：2013-04-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  SNAPE NATHAN ,  DYE CHRISTOPHER M

    IPC: F02C7/06 ,  B64D33/00 ,  F01D25/12 ,  F01D25/18 ,  F01M11/00 ,  F02C7/14 ,  F02C7/32

    CPC classification number: F02C3/04 ,  F01D25/12 ,  F01D25/18 ,  F02C7/06 ,  F02C7/12 ,  F02C7/14 ,  F02C7/32

    Abstract: A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. Fan and core nacelles define an annular bypass flow path. The core nacelle provides a core compartment and includes an opening into the core compartment. The oil tank is arranged in the core compartment and includes a portion aligned with the opening that is exposed to the bypass flow path. The engine static structure is supported relative to a fan case by a radial structure. The oil tank is mounted to the engine static structure. An oil fill tube is mounted to the fan case and is fluidly connected to the oil tank.

    LOW PROFILE COMPRESSOR BLEED AIR-OIL COOLERS
    9.
    发明公开
    LOW PROFILE COMPRESSOR BLEED AIR-OIL COOLERS 审中-公开
    WITH LOW PROFILE压缩机放机油冷却器

    公开(公告)号：EP2904237A4

    公开(公告)日：2016-07-27

    申请号：EP13857505

    申请日：2013-08-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNAPE NATHAN ,  SUCIU GABRIEL L ,  PICKFORD SIMON ,  PENDA ALLAN R

    IPC: F02C7/14 ,  F02C6/08

    CPC classification number: F02C6/08 ,  F02C7/14 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/675

    Abstract: An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.

    TURBO COMPRESSOR FOR BLEED AIR
    10.
    发明公开
    TURBO COMPRESSOR FOR BLEED AIR 审中-公开
    TURBOVERDICHTERFÜREIN LUFTABLASSSYSTEM

    公开(公告)号：EP2932073A4

    公开(公告)日：2016-08-03

    申请号：EP13863329

    申请日：2013-12-10

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNAPE NATHAN ,  MERRY BRIAN D ,  PENDA ALLAN R ,  SUCIU GABRIEL L

    IPC: F02C6/08 ,  F02C6/12 ,  F02C7/141 ,  F02C9/18

    CPC classification number: F02C9/18 ,  F02C6/08 ,  F02C6/12 ,  F02C7/141 ,  Y02T50/675

    Abstract: A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air.

    Abstract translation: 公开的泄放空气系统利用来自高压压缩机的高压空气来驱动涡轮压缩机以增加从低压压缩机抽出的排出空气的压力。 从低压压缩机抽出的空气的压力低于高压压缩机所遇到的温度和压力。 涡轮压缩机增加了气流的压力，并且使得流入主排气通道的气流被传送到利用排放空气的系统。

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