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    VARIABLE EXHAUST MIXER AND COOLER FOR A THREE-STREAM GAS TURBINE ENGINE
    2.
    发明申请
    VARIABLE EXHAUST MIXER AND COOLER FOR A THREE-STREAM GAS TURBINE ENGINE 审中-公开
    三流式涡轮发动机的可变排气混合器和冷却器

    公开(公告)号：US20170009703A1

    公开(公告)日：2017-01-12

    申请号：US15271541

    申请日：2016-09-21

    Applicant: United Technologies Corporation

    Inventor： Francis R. Moon ,  Daniel B. Kupratis

    IPC: F02K1/12 ,  F02K3/06

    CPC classification number: F02K1/12 ,  F02K1/06 ,  F02K1/36 ,  F02K1/38 ,  F02K1/386 ,  F02K1/46 ,  F02K3/06 ,  F02K3/077 ,  F05D2220/323

    Abstract: A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure. An inner case structure is included inboard of the intermediate case structure. A variable area exhaust mixer is included, which is movable between a closed position adjacent to the intermediate case structure and an open position adjacent to the inner case structure.

    Abstract translation: 燃气涡轮发动机包括围绕中心纵向发动机轴线的外壳结构。 中间壳体结构包括在外壳结构内。 内壳结构包括在中间壳结构的内侧。 包括可变面积排气混合器，其可在与中间壳体结构相邻的关闭位置和与内壳结构相邻的打开位置之间移动。

    REVERSE CORE GEAR TURBOFAN
    3.
    发明申请
    REVERSE CORE GEAR TURBOFAN 审中-公开
    反向齿轮齿轮涡轮机

    公开(公告)号：US20150345384A1

    公开(公告)日：2015-12-03

    申请号：US14824157

    申请日：2015-08-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Daniel Bernard Kupratis ,  Francis R. Moon

    IPC: F02C3/14 ,  F02C7/36 ,  F02C3/05

    CPC classification number: F02C6/02 ,  F01D17/141 ,  F02C3/05 ,  F02C3/10 ,  F02C3/107 ,  F02C3/13 ,  F02C3/145 ,  F02C7/36 ,  F02C9/18 ,  F02K3/06 ,  F02K3/065 ,  F02K3/075 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2250/36 ,  F05D2260/4023 ,  F05D2260/4031 ,  F05D2270/053

    Abstract: A gas turbine engine comprises a fan at an axially outer location, the fan rotating about an axis of rotation, delivering air into an outer bypass duct, a radially middle duct, and a radially inner core duct. Air from the inner core duct is directed into a compressor, and then flows axially in a direction back toward the fan through a combustor section, and across a core turbine section, and is then directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method of operating a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括在轴向外部位置处的风扇，风扇围绕旋转轴线旋转，将空气输送到外部旁路管道，径向中间管道和径向内部核心管道。 来自内芯管道的空气被引导到压缩机中，然后沿着朝向风扇的方向轴向流动通过燃烧器部分，并且穿过芯部涡轮部分，然后被引导到中间管道中。 齿轮减速器从风扇驱动涡轮机部分驱动风扇。 还公开了一种操作燃气涡轮发动机的方法。

    Gas turbine engine with stream diverter
    5.
    发明授权
    Gas turbine engine with stream diverter 有权
    燃气涡轮发动机配有分流器

    公开(公告)号：US09523329B2

    公开(公告)日：2016-12-20

    申请号：US13937670

    申请日：2013-07-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Daniel Bernard Kupratis ,  Francis R. Moon

    IPC: F02K3/075 ,  F02K3/077 ,  F02C3/14 ,  F02C9/18 ,  F02C3/13 ,  F02K3/06

    CPC classification number: F02K3/075 ,  F02C3/13 ,  F02C3/145 ,  F02C9/18 ,  F02K1/80 ,  F02K3/06 ,  F02K3/077 ,  F05D2210/40 ,  F05D2250/311

    Abstract: In accordance with one aspect of the disclosure, a stream diverter for a gas turbine engine is disclosed. The stream diverter may include a first air duct, a second air duct, a third air duct, and a door operatively associated with the second and third air ducts of the gas turbine engine. The door may have at least an open position allowing air from the second air duct to flow into the third air duct and a closed position preventing air from flowing between the ducts.

    Abstract translation: 根据本公开的一个方面，公开了一种用于燃气涡轮发动机的液流分流器。 流分流器可以包括第一空气管道，第二空气管道，第三空气管道和与燃气涡轮发动机的第二和第三空气管道可操作地相关联的门。 门可以具有至少一个打开位置，允许来自第二空气管道的空气流入第三空气管道和封闭位置，防止空气在管道之间流动。

    VARIABLE EXHAUST MIXER AND COOLER FOR A THREE-STREAM GAS TURBINE ENGINE
    8.
    发明申请
    VARIABLE EXHAUST MIXER AND COOLER FOR A THREE-STREAM GAS TURBINE ENGINE 审中-公开
    三流式涡轮发动机的可变排气混合器和冷却器

    公开(公告)号：US20150211441A1

    公开(公告)日：2015-07-30

    申请号：US14553284

    申请日：2014-11-25

    Applicant: United Technologies Corporation

    Inventor： Francis R. Moon ,  Daniel B. Kupratis

    IPC: F02K1/46

    CPC classification number: F02K1/12 ,  F02K1/06 ,  F02K1/36 ,  F02K1/38 ,  F02K1/386 ,  F02K1/46 ,  F02K3/06 ,  F02K3/077 ,  F05D2220/323

    Abstract: A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure. An inner case structure is included inboard of the intermediate case structure. A variable area exhaust mixer is included, which is movable between a closed position adjacent to the intermediate case structure and an open position adjacent to the inner case structure.

    Abstract translation: 燃气涡轮发动机包括围绕中心纵向发动机轴线的外壳结构。 中间壳体结构包括在外壳结构内。 内壳结构包括在中间壳结构的内侧。 包括可变面积排气混合器，其可在与中间壳体结构相邻的关闭位置和与内壳结构相邻的打开位置之间移动。

    REVERSE-FLOW CORE GAS TURBINE ENGINE WITH A PULSE DETONATION SYSTEM
    9.
    发明申请
    REVERSE-FLOW CORE GAS TURBINE ENGINE WITH A PULSE DETONATION SYSTEM 审中-公开

    公开(公告)号：US20190093553A1

    公开(公告)日：2019-03-28

    申请号：US16142337

    申请日：2018-09-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Daniel Bernard Kupratis ,  Francis R. Moon

    IPC: F02C3/14 ,  F23G7/06 ,  F23R7/00 ,  F02C3/107 ,  F02K3/11 ,  F02C7/36 ,  F02C7/06 ,  F02C5/02 ,  F02K3/06

    Abstract: The engine (10) includes a low spool (16) disposed aft of an air inlet (12) and a high spool (34) disposed aft of the low spool (16). An intake reverse-duct (44) is disposed radially outward of the high spool (34) and reverses direction of low pressure compressed air from the low spool (16) into a forward-flow high pressure compressor (40) of the high spool (34). A discharge reverse-manifold (48) directs flow of an exhaust gas stream (50) from a forward-flow low pressure turbine (20) into a rearward-flow direction and into at least one pulse detonation firing tube (54). An annular bypass air duct (72) directs cooling air along the engine (10)—The at least, one firing tube is positioned radially outward of the high spool (34), overlies the high spool (34) and is also positioned within the bypass air duct (72).

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