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    GAS TURBINE ENGINE WITH EMBEDDED DISTRIBUTED FANS
    62.
    发明申请
    GAS TURBINE ENGINE WITH EMBEDDED DISTRIBUTED FANS 审中-公开
    具有嵌入式分布式风机的气体涡轮发动机

    公开(公告)号：US20150361879A1

    公开(公告)日：2015-12-17

    申请号：US14600304

    申请日：2015-01-20

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Jesse M. Chandler ,  Stephen G. Pixton

    IPC: F02C3/10 ,  B64D33/02 ,  B64D33/04 ,  F02K1/54 ,  B64D27/12

    CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C6/206 ,  F02C7/36 ,  F02K1/54

    Abstract: An aircraft body comprises a support structure. A gas turbine engine comprises a gas generator having at least one compressor rotor, at least one gas generator turbine rotor, and a combustion section. A fan drive turbine is positioned downstream of at least one gas generator turbine rotor, and is configured to drive a shaft. The shaft engages gears to drive a plurality of fan rotors. The gas turbine engine is embedded into the support structure such that there is an inlet leading through the support structure to the fan rotors to deliver air to the fan rotors. A gas turbine engine is also disclosed.

    Abstract translation: 飞机主体包括支撑结构。 燃气涡轮发动机包括具有至少一个压缩机转子，至少一个气体发生器涡轮机转子和燃烧部分的气体发生器。 风扇驱动涡轮机位于至少一个气体发生器涡轮转子的下游，并且构造成驱动轴。 轴接合齿轮以驱动多个风扇转子。 燃气涡轮发动机被嵌入到支撑结构中，使得有一个入口通过支撑结构通向风扇转子，以将空气输送到风扇转子。 还公开了一种燃气涡轮发动机。

    ASYMMETRIC THRUST REVERSERS
    64.
    发明申请
    ASYMMETRIC THRUST REVERSERS 有权
    不对称扭矩反转器

    公开(公告)号：US20150291289A1

    公开(公告)日：2015-10-15

    申请号：US14646752

    申请日：2013-03-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

    IPC: B64D33/04 ,  B64C5/02 ,  F02K1/60 ,  B64D27/14

    CPC classification number: B64D33/04 ,  B64C5/02 ,  B64D27/14 ,  B64D27/20 ,  F02K1/60

    Abstract: An aircraft includes a propulsion supported within an aft portion of a fuselage A thrust reverser is mounted in the aft portion of the fuselage proximate the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser includes an upper blocker door movable about a first pivot axis to a deployed position and a lower blocker door movable about a second pivot axis not parallel to the first pivot axis.

    Abstract translation: 飞行器包括支撑在机身的后部的推进器。推力反向器安装在靠近推进系统的机身的后部，用于引导推进以减缓飞行器的方向。 推力反向器包括可围绕第一枢转轴线移动到展开位置的上部阻挡门，以及可围绕不平行于第一枢转轴线的第二枢转轴线移动的下部阻挡门。

    ATR FULL RING SLIDING NACELLE
    65.
    发明申请
    ATR FULL RING SLIDING NACELLE 有权
    ATR全滑动滑轨

    公开(公告)号：US20150125284A1

    公开(公告)日：2015-05-07

    申请号：US14187021

    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 includes a core, a first annular portion, a rail, and a second annular portion. The first annular portion is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion, and a fore bi-fi. The rail is coupled to the fore pylon portion and extending in the aft direction from the stationary portion. The second annular portion is arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion comprises an aft bi-fi configured to engage with the fore bi-fi when the gas turbine engine is in the closed position.

    Abstract translation: 燃气涡轮发动机包括铁芯，第一环形部分，轨道和第二环形部分。 第一环形部分是静止的并且适于部分地围绕发动机芯。 第一环形部分包括前挂架连接部分和前部双向翼片。 导轨连接到前挂架部分并且在后方向上从固定部分延伸。 第二环形部分布置在第一部分的后部并且联接到轨道。 第二环形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。 第二环形部分包括后部双层结构，其构造成当燃气涡轮发动机处于关闭位置时与前部双向接合。

    TANDEM THRUST REVERSER WITH MULTI-POINT ACTUATION
    66.
    发明申请
    TANDEM THRUST REVERSER WITH MULTI-POINT ACTUATION 有权
    TANDEM THRUST REVERSER多点执行

    公开(公告)号：US20150122912A1

    公开(公告)日：2015-05-07

    申请号：US14184398

    申请日：2014-02-19

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02K1/76 ,  F02K1/72 ,  B23P19/04

    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 comprising a first tandem pivot door subassembly comprising an inner panel and outer panel connected. A second tandem pivot door subassembly is included comprising an inner panel and outer panel connected. Also included are a first actuator located on a first side of an attachment location to pivot the first tandem pivot door subassembly, a second actuator located on a second side of the attachment location to pivot the second tandem pivot door subassembly, and a third actuator located substantially radially opposite the attachment location to pivot both the first tandem pivot door subassembly and the second tandem pivot door subassembly. The first tandem pivot door is configured to be pivoted from stowed to deployed by the first actuator and the third actuator, and the second tandem pivot door is configured to be pivoted from stowed to deployed by the second actuator and the third actuator.

    Abstract translation: 一个实施例包括枢轴推力反向器，其包括第一串联枢轴门子组件，其包括连接的内板和外板。 包括第二串联枢轴门子组件，包括连接的内板和外板。 还包括位于附接位置的第一侧上以枢转第一串联枢转门子组件的第一致动器，位于附接位置的第二侧以枢转第二串联枢转门子组件的第二致动器，以及位于 基本上径向地相对于所述附接位置枢转所述第一串联枢轴门子组件和所述第二串联枢轴门子组件。 第一串联枢转门构造成从收起枢转以由第一致动器和第三致动器展开，并且第二串联枢转门构造成从收起枢转以由第二致动器和第三致动器展开。

    Gas Turbine Engine Heat Exchanger for Annular Flowpaths
    67.
    发明申请
    Gas Turbine Engine Heat Exchanger for Annular Flowpaths 有权

    公开(公告)号：US20210207534A1

    公开(公告)日：2021-07-08

    申请号：US16733646

    申请日：2020-01-03

    Applicant: United Technologies Corporation

    Inventor： Joseph B. Staubach ,  Amanda Jean Boucher ,  Jesse M. Chandler

    IPC: F02C7/143 ,  F02C7/16 ,  F28D7/02

    Abstract: A heat exchanger has arcuate inlet and outlet manifolds and a plurality of tube banks, each tube bank coupling one of the inlet manifold outlets to an associated one of the outlet manifold inlets. Each tube bank partially nests with one or more others of the tube banks and has: a first header coupled to the associated inlet manifold outlet and the associated the outlet manifold inlet; a second header; and a plurality of tube bundles each having a first end coupled to the associated first header and a second end coupled to the associated second header. A flowpath from the each inlet manifold outlet passes sequentially through flowpath legs formed by each of the tube bundles in the associated tube bank to exit the tube bank to the associated outlet manifold inlet.

    Intercooled cooling air
    68.
    发明授权
    Intercooled cooling air 有权

    公开(公告)号：US10731560B2

    公开(公告)日：2020-08-04

    申请号：US15907942

    申请日：2018-02-28

    Applicant: United Technologies Corporation

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

    IPC: F02C7/143 ,  F02C6/08 ,  F02C7/18 ,  F02C9/18 ,  F02C7/32 ,  F02K3/06

    Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap and configured to deliver air to an aircraft fuselage. A cooling compressor is connected downstream of the heat exchanger. A high pressure feed is configured to deliver air at a second pressure which is higher than the first pressure. The cooling compressor is configured to deliver air to at least one of the plurality of rotating components. A valve assembly that can select whether air from the first tap or air from the high pressure feed is delivered to the aircraft pneumatic system.

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