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    ATR GUIDE PINS FOR SLIDING NACELLE
    101.
    发明申请
    ATR GUIDE PINS FOR SLIDING NACELLE 有权
    ATR指南针

    公开(公告)号：US20150125270A1

    公开(公告)日：2015-05-07

    申请号：US14187034

    申请日：2014-02-21

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: B64D29/06 ,  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 extending in the aft direction from the first annular portion. A second annular portion, aft of the first annular portion and coupled to the rail, 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 when the second annular portion is in the closed position, thereby providing access to the engine core. A guide pin extends forward from the second annular portion. A locking mechanism is disposed within the first annular portion for engaging the guide pin when the second annular portion is in the closed position.

    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。 第一环形部分的后部并且联接到轨道的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。 第二环形部分构造成当第二环形部分处于关闭位置时与第一环形部分接合，从而提供对发动机芯的通路。 引导销从第二环形部分向前延伸。 当第二环形部分处于关闭位置时，锁定机构设置在第一环形部分内用于接合引导销。

    VARIABLE CYCLE INTAKE FOR REVERSE CORE ENGINE
    103.
    发明申请
    VARIABLE CYCLE INTAKE FOR REVERSE CORE ENGINE 审中-公开
    反向核心发动机的可变周期摄入

    公开(公告)号：US20140260183A1

    公开(公告)日：2014-09-18

    申请号：US14142966

    申请日：2013-12-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph B. Staubach

    IPC: F02C7/057 ,  F02C7/055

    CPC classification number: F02C7/057 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0286 ,  F02C3/10 ,  F02C7/042 ,  F02C7/052 ,  F02C7/055 ,  F02K3/077 ,  F05D2250/314

    Abstract: A gas generator for a reverse core engine propulsion system has a variable cycle intake for the gas generator, which variable cycle intake includes a duct system. The duct system is configured for being selectively disposed in a first position and a second position, wherein free stream air is fed to the gas generator when in the first position, and fan stream air is fed to the gas generator when in the second position.

    Abstract translation: 用于逆向核心发动机推进系统的气体发生器具有用于气体发生器的可变循环进气口，该可变循环进气口包括管道系统。 管道系统被配置为选择性地设置在第一位置和第二位置，其中当处于第一位置时，自由流空气被供给到气体发生器，并且当处于第二位置时，风扇流空气被供给到气体发生器。

    REVERSE CORE ENGINE THRUST REVERSER FOR UNDER WING
    104.
    发明申请
    REVERSE CORE ENGINE THRUST REVERSER FOR UNDER WING 有权
    反向核心发动机扭转逆向

    公开(公告)号：US20140252167A1

    公开(公告)日：2014-09-11

    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: F02K1/70 ,  B64D33/04

    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。

    REAR MOUNTED REVERSE CORE ENGINE THRUST REVERSER
    105.
    发明申请
    REAR MOUNTED REVERSE CORE ENGINE THRUST REVERSER 有权
    后安装反向核心发动机逆转器

    公开(公告)号：US20140250863A1

    公开(公告)日：2014-09-11

    申请号：US14190171

    申请日：2014-02-26

    Applicant: United Technologies Corporation

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

    IPC: F02K1/62

    CPC classification number: F02K1/60 ,  F05D2210/40 ,  F05D2250/314

    Abstract: In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage 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 vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

    Abstract translation: 在一个实施例中，用于安装到飞行器机身后部的燃气涡轮发动机具有在第一轴线上旋转的推进器，以及包括压缩机部分，燃烧器部分和涡轮部分的发动机芯，涡轮部分是 比压缩机部分更靠近推进器。 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垂直展开位置之间枢转，门中阻止流动以提供逆流。

    Gas turbine engine heat exchanger for annular flowpaths
    106.
    发明授权
    Gas turbine engine heat exchanger for annular flowpaths 有权

    公开(公告)号：US11378341B2

    公开(公告)日：2022-07-05

    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: F28D7/04 ,  F01K25/10 ,  F02C7/16 ,  F01K23/06 ,  F02C1/05 ,  F28D21/00

    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.

    Aft counter-rotating boundary layer ingestion engine
    107.
    发明授权
    Aft counter-rotating boundary layer ingestion engine 有权

    公开(公告)号：US11098678B2

    公开(公告)日：2021-08-24

    申请号：US15945907

    申请日：2018-04-05

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02K3/072 ,  F02K5/00 ,  F04D29/58 ,  B64D27/20 ,  F02C7/36 ,  B64D27/02

    Abstract: A boundary layer ingestion engine includes a fan section configured to extend into a boundary layer of a full annulus of an aft end of a fuselage of an aircraft. The fan section includes a first fan stage and a second fan stage. The boundary layer ingestion engine also includes a differential planetary gear system is operable to transform rotation of an input shaft into counter rotation of a first shaft coupled to the first fan stage and a second shaft coupled to the second fan stage. The boundary layer ingestion engine further includes a motor operable to drive rotation of the input shaft.

    Boundary layer cooling air for embedded engine
    108.
    发明授权
    Boundary layer cooling air for embedded engine 有权

    公开(公告)号：US10934938B2

    公开(公告)日：2021-03-02

    申请号：US15217108

    申请日：2016-07-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler ,  Steven H. Zysman

    IPC: F02C7/18 ,  B64D27/20 ,  F02C3/04

    Abstract: A gas turbine engine has an inner housing surrounding a compressor, a combustor, and a turbine, with an inlet leading into the compressor, and a cooling sleeve defined radially outwardly of the inlet to the compressor for receiving cooling air radially outward of the compressor inlet. The cooling sleeve extends along a length of the engine, and radially outwardly of the inner housing, with the cooling air in the cooling sleeve being ejected at a downstream end to mix with products of combustion downstream of the turbine. An aircraft is also disclosed.

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