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    Two Spool Gas Generator with Mount Ring
    281.
    发明申请
    Two Spool Gas Generator with Mount Ring 审中-公开
    两个带安装环的阀芯气体发生器

    公开(公告)号：US20150354463A1

    公开(公告)日：2015-12-10

    申请号：US14758368

    申请日：2013-06-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02C7/36 ,  F02C7/06 ,  F02C7/32

    CPC classification number: F02C7/36 ,  B64D27/10 ,  B64D2027/005 ,  F02C7/06 ,  F02C7/20 ,  F02C7/32 ,  F02K3/072 ,  F05D2240/90 ,  Y02T50/66

    Abstract: A gas turbine engine has a first shaft including a first turbine rotor, and a second shaft including a second turbine rotor disposed downstream of the first turbine rotor. A third shaft includes a propulsor turbine positioned downstream of the second turbine rotor for driving a propeller. A mount ring is secured between the second turbine rotor and the propeller.

    Abstract translation: 燃气涡轮发动机具有包括第一涡轮转子的第一轴和包括设置在第一涡轮转子下游的第二涡轮转子的第二轴。 第三轴包括位于第二涡轮转子下游的推进涡轮机，用于驱动螺旋桨。 安装环固定在第二涡轮转子和螺旋桨之间。

    Below Wing Reverse Core Gas Turbine Engine With Thrust Reverser
    283.
    发明申请
    Below Wing Reverse Core Gas Turbine Engine With Thrust Reverser 审中-公开
    低于逆向核心燃气轮机发动机与推力反转器

    公开(公告)号：US20150354449A1

    公开(公告)日：2015-12-10

    申请号：US14759703

    申请日：2013-05-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02C3/107 ,  F02K1/70

    CPC classification number: F02C3/107 ,  F02K1/60 ,  F02K1/70 ,  F02K3/00

    Abstract: A core engine includes a compressor section, a combustor and a turbine section, with the turbine section being closest to a fan, the combustor section and then the compressor section being positioned further away from the fan relative to the turbine section. A downstream end of a nozzle has at least one pivoting shell and an actuator pivots the shell between a stowed position and a deployed position. A mount bracket is mounted at one circumferential location of the engine. The shell moves in a direction having at least a component perpendicular to a vertical direction defined perpendicular to a top surface of the mount bracket.

    Abstract translation: 核心发动机包括压缩机部分，燃烧器和涡轮机部分，其中涡轮部分最靠近风扇，燃烧器部分然后压缩机部分相对于涡轮部分定位成更远离风扇。 喷嘴的下游端具有至少一个枢转壳体，并且致动器在收起位置和展开位置之间枢转壳体。 安装支架安装在发动机的一个圆周位置。 壳体沿着至少垂直于垂直于安装支架的顶表面限定的垂直方向的分量的方向移动。

    TWO SPOOL GAS GENERATOR TO CREATE FAMILY OF GAS TURBINE ENGINES
    284.
    发明申请
    TWO SPOOL GAS GENERATOR TO CREATE FAMILY OF GAS TURBINE ENGINES 有权
    两台气体发生器创造气体涡轮发动机系列

    公开(公告)号：US20150300250A1

    公开(公告)日：2015-10-22

    申请号：US14647537

    申请日：2013-05-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Brian D. Merry

    IPC: F02C6/02 ,  F02C7/06

    CPC classification number: F02C6/02 ,  F02C3/10 ,  F02C7/06 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/324 ,  F05D2220/326 ,  F05D2250/31 ,  F05D2260/4031

    Abstract: A method of configuring a plurality of gas turbine engines includes the steps of configuring each of the engines with respective ones of a plurality of propulsors. Each propulsor includes a propulsor turbine and one of a fan and a propeller. Each of the engines is configured with respective ones of a plurality of substantially mutually alike gas generators, with the respective propulsor turbine driven by products of combustion downstream of the gas generator.

    Abstract translation: 配置多个燃气涡轮发动机的方法包括以下步骤：用多个推进器中的相应的发动机配置每个发动机。 每个推进器包括推进涡轮机和风扇和螺旋桨之一。 每个发动机配置有多个基本相互相似的气体发生器中的相应的发动机，相应的推进涡轮机由气体发生器下游的燃烧产物驱动。

    Cooling System with a Bearing Compartment Bypass
    286.
    发明申请
    Cooling System with a Bearing Compartment Bypass 有权
    带有轴承舱的冷却系统旁路

    公开(公告)号：US20150285147A1

    公开(公告)日：2015-10-08

    申请号：US14594663

    申请日：2015-01-12

    Applicant: United Technologies Corporation

    Inventor： Justin J. Phillips ,  James D. Hill ,  William K. Ackermann ,  Chris J. Niggemeier ,  Gabriel L. Suciu ,  Anthony R. Bifulco ,  Julian Partyka

    IPC: F02C7/18 ,  F01D25/12

    CPC classification number: F02C7/185 ,  F01D5/081 ,  F01D5/082 ,  F01D5/186 ,  F01D5/187 ,  F01D9/06 ,  F01D9/065 ,  F01D25/08 ,  F01D25/12 ,  F01D25/125 ,  F02C6/08 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/221 ,  F05D2260/232 ,  Y02T50/671 ,  Y02T50/676

    Abstract: A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.

    Abstract translation: 公开了一种用于向燃气涡轮发动机的涡轮部分提供缓冲冷却的冷却空气的冷却系统。 冷却系统可以包括构造成将冷却空气朝向涡轮机部分传送的第一管道，被配置为冷却从第一管道转向以提供缓冲空气的排出气流的热交换器，以及配置成引导至少一部分 的缓冲空气通过绕过燃气涡轮发动机的轴承室的至少一个通道。 冷却系统还可以包括歧管，其配置成允许从第一导管排出的冷却空气和离开旁路导管的缓冲空气混合并提供缓冲冷却的冷却空气;以及喷嘴组件，其配置成将缓冲冷却的冷却空气输送到 涡轮段。

    GEARED TURBOFAN WITH A GEARBOX UPSTREAM OF A FAN DRIVE TURBINE
    287.
    发明申请
    GEARED TURBOFAN WITH A GEARBOX UPSTREAM OF A FAN DRIVE TURBINE 审中-公开
    具有风力发电机组的齿轮式上升装置的齿轮涡轮机

    公开(公告)号：US20150176497A1

    公开(公告)日：2015-06-25

    申请号：US14573812

    申请日：2014-12-17

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C7/36 ,  F02C7/32

    CPC classification number: F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/4031 ,  F05D2260/40311

    Abstract: A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a combustor section located axially upstream of the drive turbine, and a speed change mechanism located axially downstream of the combustor section and axially upstream of the drive turbine. An output of the speed change mechanism connects to the fan.

    Abstract translation: 根据本公开的示例的燃气涡轮发动机包括驱动涡轮机，其构造成驱动风扇部分，位于驱动涡轮机轴向上游的燃烧器部分，以及位于燃烧器部分的轴向下游并且位于轴向上游 驱动涡轮机。 变速机构的输出与风扇连接。

    ATR AXIAL V-GROOVE
    288.
    发明申请
    ATR AXIAL V-GROOVE 有权
    ATR轴V-GROOVE

    公开(公告)号：US20150125286A1

    公开(公告)日：2015-05-07

    申请号：US14187038

    申请日：2014-02-21

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F01D25/24

    CPC classification number: B64D29/06 ,  F01D9/02 ,  F01D25/24 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2230/80 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/128 ,  F05D2240/1281 ,  F05D2240/14 ,  F05D2240/55 ,  F05D2240/91 ,  F05D2250/192 ,  F05D2250/292 ,  F05D2250/294 ,  F05D2250/34 ,  F05D2250/75 ,  F05D2260/96 ,  Y10T29/49721

    Abstract: A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon connecting portion and extends in the aft direction from the first annular portion. A second annular portion is positioned aft of the first portion and coupled to the rail. The second portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage with the first annular portion in the closed position, thereby providing access to the engine core. A mating axial groove and rib connection is located between the first annular portion and the second annular portion.

    Abstract translation: 燃气涡轮发动机机舱包括固定的并适于部分围绕发动机芯的第一环形部分。 第一环形部分包括前挂架连接部分。 轨道联接到前挂架连接部分并且在后方向上从第一环形部分延伸。 第二环形部分位于第一部分的后部并且联接到轨道。 第二部分可沿着发动机芯心中心线在关闭位置和至少一个打开位置之间移动。 第二环形部分构造成在关闭位置与第一环形部分接合，从而提供对发动机芯的通路。 配合的轴向槽和肋连接件位于第一环形部分和第二环形部分之间。

    TANDEM THRUST REVERSER WITH MULTI-BAR LINKAGE
    290.
    发明申请
    TANDEM THRUST REVERSER WITH MULTI-BAR LINKAGE 有权

    公开(公告)号：US20150121839A1

    公开(公告)日：2015-05-07

    申请号：US14184368

    申请日：2014-02-19

    Applicant: United Technologies Corporation

    Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

    IPC: F02K1/72

    CPC classification number: F02K1/763 ,  B23P19/04 ,  B64D29/00 ,  B64D33/04 ,  F02K1/60 ,  F02K1/605 ,  F02K1/62 ,  F02K1/64 ,  F02K1/72 ,  F05D2260/50 ,  Y10T29/49229

    Abstract: One embodiment includes a pivot thrust reverser. The pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and the outer panel are connected so as to rotate simultaneously about respective pivot axises that are each positionally fixed axises relative to the gas turbine engine assembly. A second tandem pivot door subassembly is included, spaced from the first tandem pivot door subassembly and comprising an inner panel and an outer panel. The inner panel and the outer panel are connected so as to rotate simultaneously about respective pivot axises that are each positionally fixed axises relative to the gas turbine engine assembly.

    Abstract translation: 一个实施例包括枢轴推力反向器。 枢轴推力反向器包括第一串联枢轴门子组件，其包括内板和外板。 内板和外板被连接成围绕相对于燃气涡轮发动机组件各自位置固定的轴线的相应枢转轴线同时旋转。 包括第二串联枢轴门子组件，与第一串联枢轴门子组件间隔开并且包括内板和外板。 内板和外板被连接成围绕相对于燃气涡轮发动机组件各自位置固定的轴线的相应枢转轴线同时旋转。

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