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    Reverse core engine thrust reverser for under wing
    23.
    发明授权
    Reverse core engine thrust reverser for under wing 有权
    逆向核心发动机推力反向器用于下翼

    公开(公告)号：US09574520B2

    公开(公告)日：2017-02-21

    申请号：US14190178

    申请日：2014-02-26

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Brian D. Merry

    IPC: F02K1/54 ,  F02K1/70 ,  B64D33/04 ,  B64D29/06

    CPC classification number: F02K1/70 ,  B64D29/06 ,  B64D33/04 ,  F05D2250/314 ,  Y02T50/671

    Abstract: A gas turbine engine for mounting under a wing of an aircraft has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a horizontal deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

    Abstract translation: 用于安装在飞行器的机翼下方的燃气涡轮发动机具有在第一轴线上旋转的推进器和包括压缩机部分，燃烧器部分和涡轮部分的发动机核心，其中涡轮机部分更靠近推进器， 压缩机部分。 发动机机芯与空气动力学连接，并具有第二轴。 机舱位于推进器和发动机内核周围。 机舱附着在飞机的机翼上。 机舱的下游端具有至少一个枢转门，其具有致动机构，以使门在收起位置和水平展开位置之间枢转，门中阻止流动以提供逆流。

    INTERCOOLED COOLING AIR USING EXISTING HEAT EXCHANGER
    25.
    发明申请
    INTERCOOLED COOLING AIR USING EXISTING HEAT EXCHANGER 审中-公开
    使用现有热交换器的干式冷却空气

    公开(公告)号：US20160237908A1

    公开(公告)日：2016-08-18

    申请号：US14804534

    申请日：2015-07-21

    Applicant: United Technologies Corporation

    Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian D. Merry ,  Jesse M. Chandler

    IPC: F02C7/18

    CPC classification number: F02C6/08 ,  F02C7/143 ,  F02C7/185 ,  F02C7/32 ,  F05D2260/213 ,  Y02T50/671 ,  Y02T50/676

    Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger also receives air to be delivered to an aircraft cabin. An intercooling system for a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机的主压缩机部分和更多的上游位置。 涡轮机部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，使抽头的空气通过热交换器，然后通过冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 热交换器还接收要传送到飞机机舱的空气。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

    Two Spool Gas Generator with Mount Ring
    26.
    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
    27.
    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。

    ATR AXIAL V-GROOVE
    28.
    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
    30.
    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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