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    TURBINE ENGINE EXHAUST NOZZLE FLAP
    1.
    发明申请
    TURBINE ENGINE EXHAUST NOZZLE FLAP 审中-公开
    涡轮发动机排气喷嘴

    公开(公告)号：WO2014011279A2

    公开(公告)日：2014-01-16

    申请号：PCT/US2013036194

    申请日：2013-04-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MOON FRANCIS R ,  BARNETT JR CLAUDE ,  JACQUES JEFFREY M

    CPC classification number: F02K1/1223

    Abstract: An exhaust nozzle flap for a turbine engine may include an exhaust nozzle flap linkage, an exhaust nozzle flap panel and a mounting pin. The linkage may include a first linkage segment that extends longitudinally from a linkage end to a second linkage segment, and a mounting aperture that extends transversely through the second linkage segment. The panel may include a first panel segment that extends longitudinally from a panel end to a second panel segment. The first panel segment may be pivotally engaged with the first linkage segment. The mounting pin may extend through and move transversely within the mounting aperture, and may be connected to the second panel segment.

    Abstract translation: 用于涡轮发动机的排气喷嘴挡板可以包括排气喷嘴挡板连接件，排气喷嘴挡板和安装销。 连接件可以包括从连接端纵向延伸到第二连杆段的第一连杆段和横向延伸穿过第二连杆段的安装孔。 面板可以包括从面板端部纵向延伸到第二面板区段的第一面板区段。 第一面板片段可以与第一连接片段枢转地接合。 安装销可以延伸穿过并且在安装孔内横向移动，并且可以连接到第二面板段。

    REVERSE CORE GEAR TURBOFAN
    2.
    发明申请
    REVERSE CORE GEAR TURBOFAN 审中-公开
    反转核心齿轮涡轮机

    公开(公告)号：WO2014007880A3

    公开(公告)日：2014-03-20

    申请号：PCT/US2013033776

    申请日：2013-03-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  MOON FRANCIS R

    IPC: F02C7/36 ,  F02C3/067 ,  F02K3/072

    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 has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The booster fan delivers air into a radially middle duct, and across a cold turbine into a radially inner core duct being directed into a compressor. From the compressor, air flows axially in a direction back toward the fan through a combustor section, and across an exhaust of the turbine section as directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method is also disclosed.

    Abstract translation: 燃气涡轮发动机在轴向外部位置具有风扇。 风扇绕旋转轴旋转。 风扇将空气输送到外部旁路管道中，并且跨过位于外部旁路管道的径向内侧的增压风扇。 增压风扇将空气输送到径向中间的管道中，并且将冷却涡轮机转入径向内部的芯管道，将其导入压缩机。 从压缩机，空气沿着朝向风扇的方向通过燃烧器部分轴向流动，并且沿着涡轮机部分的排气指向中间管道。 齿轮减速器从风扇驱动涡轮机部分驱动风扇。 还公开了一种方法。

    REVERSE CORE GEAR TURBOFAN
    3.
    发明专利
    REVERSE CORE GEAR TURBOFAN 未知

    公开(公告)号：SG11201404963VA

    公开(公告)日：2014-10-30

    申请号：SG11201404963V

    申请日：2013-03-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  MOON FRANCIS R

    Abstract: A method of operating a gas turbine engine comprising the steps of: (a) operating a turbine section having blades with a radially outermost extent, and a flow diverter that is operable to divert air radially inwardly of the radially outermost extent of the turbine blades, or allow air to pass radially outwardly of the radially outermost extent of the turbine blades; and (b) positioning said flow diverter to increase or decrease the amount of gas passing across that turbine section to increase or decrease a power output by said turbine section.

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