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    Grounding for fan blades on an underblade spacer
    1.
    发明授权
    Grounding for fan blades on an underblade spacer 有权
    接地底片上的风扇叶片

    公开(公告)号：US09297272B2

    公开(公告)日：2016-03-29

    申请号：US13658887

    申请日：2012-10-24

    Applicant: United Technologies Corporation

    Inventor： Lee Drozdenko ,  Allan R. Penda

    IPC: F01D5/30 ,  F01D21/14 ,  F04D29/02 ,  F04D29/32

    CPC classification number: F01D21/14 ,  F01D5/3007 ,  F04D29/023 ,  F04D29/322 ,  F05D2220/36 ,  F05D2260/95 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/50 ,  F05D2300/614

    Abstract: A fan rotor includes a rotor body with at least one slot receiving a fan blade. The fan blade has an outer surface, at least at some areas, formed of a first material and an airfoil extending from a dovetail. The dovetail is received in the slot. A spacer is positioned radially inwardly of the dovetail biasing the fan blade against the slot. The spacer includes a grounding element, which is in contact with a portion of the dovetail formed of a second material that is more electrically conductive than the first material. The grounding element is in contact with a rotating element that rotates with the rotor. The rotating element is formed of a third material. The first material is less electrically conductive than the third material. The grounding and rotating elements form a ground path from the portion of the dovetail into the rotor.

    Abstract translation: 风扇转子包括具有容纳风扇叶片的至少一个槽的转子体。 风扇叶片至少在某些区域具有由第一材料形成的外表面和从燕尾形延伸的翼型件。 燕尾接收在槽中。 间隔件位于燕尾径向向内的位置，将风扇叶片偏置在狭槽上。 间隔件包括接地元件，该接地元件与由第二材料形成的燕尾形部分接触，该第二材料比第一材料更具导电性。 接地元件与转子一起旋转的旋转元件接触。 旋转元件由第三材料形成。 第一种材料比第三种材料导电性差。 接地和旋转元件形成从燕尾的部分到转子的接地路径。

    TURBOFAN THRUST REVERSER SYSTEM
    2.
    发明申请
    TURBOFAN THRUST REVERSER SYSTEM 审中-公开
    TURBOFAN THRUST REVERSER系统

    公开(公告)号：US20150337762A1

    公开(公告)日：2015-11-26

    申请号：US14284893

    申请日：2014-05-22

    Applicant: United Technologies Corporation

    Inventor： Allan R. Penda ,  Gabriel L. Suciu ,  William G. Sheridan ,  Wesley K. Lord

    IPC: F02K1/70 ,  F16H3/70 ,  F02C7/36

    CPC classification number: F02K1/70 ,  F02C3/10 ,  F02C3/113 ,  F02C3/145 ,  F02C6/04 ,  F02C7/36 ,  F02K1/32 ,  F02K3/075 ,  F05D2260/40311 ,  F16H3/60 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a core engine, a fan, a bypass duct and a clutch. The fan is driven by the core engine. The bypass duct is configured to receive airflow from the fan. The clutch links the core engine and the fan. The core comprises a reverse-flow, two-spool gas generator in one embodiment. In another embodiment, the fan is driven by a free turbine aerodynamically powered by the core engine. In one embodiment, the clutch includes reverse gearing to reverse rotational output of the fan. In one embodiment, the clutch and reverse gearing are implemented in an epicyclic gear system.

    Abstract translation: 燃气涡轮发动机包括核心发动机，风扇，旁通管道和离合器。 风扇由核心发动机驱动。 旁路管道被配置为从风扇接收气流。 离合器连接核心发动机和风扇。 核心包括在一个实施例中的逆流双阀气体发生器。 在另一个实施例中，风扇由空气动力学地由核心发动机驱动的自由涡轮机驱动。 在一个实施例中，离合器包括倒档以反转风扇的旋转输出。 在一个实施例中，离合器和倒档传动装置实现在行星齿轮系统中。

    Low profile compressor bleed air-oil coolers
    4.
    发明授权
    Low profile compressor bleed air-oil coolers 有权

    公开(公告)号：US09714610B2

    公开(公告)日：2017-07-25

    申请号：US13645067

    申请日：2012-10-04

    Applicant: United Technologies Corporation

    Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Simon Pickford ,  Allan R. Penda

    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.

    GROUNDING FOR FAN BLADES ON AN UNDERBLADE SPACER
    5.
    发明申请
    GROUNDING FOR FAN BLADES ON AN UNDERBLADE SPACER 有权
    接头用于风扇叶片

    公开(公告)号：US20140109546A1

    公开(公告)日：2014-04-24

    申请号：US13658887

    申请日：2012-10-24

    Applicant: United Technologies Corporation

    Inventor： Lee Drozdenko ,  Allan R. Penda

    IPC: F01D21/14

    CPC classification number: F01D21/14 ,  F01D5/3007 ,  F04D29/023 ,  F04D29/322 ,  F05D2220/36 ,  F05D2260/95 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/50 ,  F05D2300/614

    Abstract: A fan rotor includes a rotor body with at least one slot receiving a fan blade. The fan blade has an outer surface, at least at some areas, formed of a first material and an airfoil extending from a dovetail. The dovetail is received in the slot. A spacer is positioned radially inwardly of the dovetail biasing the fan blade against the slot. The spacer includes a grounding element, which is in contact with a portion of the dovetail formed of a second material that is more electrically conductive than the first material. The grounding element is in contact with a rotating element that rotates with the rotor. The rotating element is formed of a third material. The first material is less electrically conductive than the third material. The grounding and rotating elements form a ground path from the portion of the dovetail into the rotor.

    Abstract translation: 风扇转子包括具有容纳风扇叶片的至少一个槽的转子体。 风扇叶片至少在某些区域具有由第一材料形成的外表面和从燕尾形延伸的翼型件。 燕尾接收在槽中。 间隔件位于燕尾径向向内的位置，将风扇叶片偏置在狭槽上。 间隔件包括接地元件，该接地元件与由第二材料形成的燕尾形部分接触，该第二材料比第一材料更具导电性。 接地元件与转子一起旋转的旋转元件接触。 旋转元件由第三材料形成。 第一种材料比第三种材料导电性差。 接地和旋转元件形成从燕尾的部分到转子的接地路径。

    INTEGRATED THERMAL SYSTEM FOR A GAS TURBINE ENGINE
    10.
    发明申请
    INTEGRATED THERMAL SYSTEM FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的集成热系统

    公开(公告)号：US20150267617A1

    公开(公告)日：2015-09-24

    申请号：US14729800

    申请日：2015-06-03

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Allan R. Penda ,  Brian D. Merry ,  Christopher M. Dye ,  Nathan Snape

    IPC: F02C7/18 ,  F02C7/14 ,  F02C7/08

    CPC classification number: F02C7/185 ,  F02C7/08 ,  F02C7/14 ,  F02C7/18 ,  Y02T50/671

    Abstract: A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.

    Abstract translation: 用于燃气涡轮发动机的热系统包括在交叉口处与旁路流动管道相交的旁通流动管道和压缩机流动管道。 阀位于交叉口内，并可在第一位置和第二位置之间移动。 第一位置可操作以选择性地使来自旁路流动管道的风扇旁路流动并且阻塞压缩机流动管道。 第二位置可操作以选择性地阻挡旁路流动管道并且连通通过压缩机流动管道的排出流。

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