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    High performance convergent divergent nozzle
    1.
    发明授权
    High performance convergent divergent nozzle 有权

    公开(公告)号：US10550704B2

    公开(公告)日：2020-02-04

    申请号：US14911889

    申请日：2014-08-22

    Applicant: United Technologies Corporation

    Inventor： Michael Joseph Murphy ,  Oleg Petrenko

    IPC: F02K1/82 ,  F01D9/02 ,  F02K1/78 ,  F01D25/24 ,  F02C3/04 ,  F02C7/36 ,  F02K3/04

    Abstract: A turbofan engine includes a fan section. A core engine section drives the fan section. An outer nacelle surrounds the fan section and defines a radially outer surface of a fan duct. An inner nacelle surrounds the core engine section and defines a radially inner surface of the fan duct. A nozzle is disposed at a terminal end of the outer nacelle that defines an exit area for bypass air flow through the fan duct. The nozzle includes a convergent portion forward of a divergent portion and a turning angle for the divergent portion greater than about 12 degrees. A nacelle assembly and method are also disclosed.

    VARIABLE AREA FAN NOZZLE WITH WALL THICKNESS DISTRIBUTION
    2.
    发明申请
    VARIABLE AREA FAN NOZZLE WITH WALL THICKNESS DISTRIBUTION 审中-公开

    公开(公告)号：US20200032739A1

    公开(公告)日：2020-01-30

    申请号：US16422181

    申请日：2019-05-24

    Applicant: United Technologies Corporation

    Inventor： Oliver V. Atassi ,  Oleg Petrenko

    IPC: F02K1/15 ,  F02K1/82 ,  F02K1/06 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06

    Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nozzle is aft of the fan and defines an exit area. The fan nozzle has a body with an airfoil cross-section geometry. The body includes a wall that has a controlled mechanical property distribution that varies in material macro- or micro-structure by location on the wall in accordance with a desired flutter characteristic at the location.

    VARIABLE AREA FAN NOZZLE WITH WALL THICKNESS DISTRIBUTION
    5.
    发明申请
    VARIABLE AREA FAN NOZZLE WITH WALL THICKNESS DISTRIBUTION 审中-公开
    可变区域风扇喷嘴与壁厚分布

    公开(公告)号：US20170058827A1

    公开(公告)日：2017-03-02

    申请号：US15177657

    申请日：2016-06-09

    Applicant: United Technologies Corporation

    Inventor： Oliver V. Atassi ,  Oleg Petrenko

    IPC: F02K1/15 ,  F02C7/36 ,  F02C3/04 ,  F02K1/82 ,  F02K3/06

    CPC classification number: F02K1/15 ,  F02C3/04 ,  F02C7/36 ,  F02K1/06 ,  F02K1/82 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2260/81 ,  F05D2300/173 ,  F05D2300/6033 ,  Y02T50/672

    Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nozzle is aft of the fan and defines an exit area. The fan nozzle has a body that defines an airfoil cross-section geometry. The body includes a wall that has a controlled mechanical property distribution that varies by location on the wall in accordance with a desired flutter characteristic at the location.

    Abstract translation: 燃气涡轮发动机包括至少具有压缩机部分，燃烧器部分和沿中心轴线布置的涡轮部分的核心发动机。 风扇被联接以由涡轮部分驱动。 风扇喷嘴位于风扇后部并限定出口区域。 风扇喷嘴具有限定翼型横截面几何形状的主体。 主体包括具有受控的机械属性分布的壁，其根据位置处的期望的颤动特性随墙壁上的位置而变化。

    Variable area fan nozzle with wall thickness distribution
    7.
    发明授权
    Variable area fan nozzle with wall thickness distribution 有权
    可变面积风扇喷嘴，壁厚分布

    公开(公告)号：US09394852B2

    公开(公告)日：2016-07-19

    申请号：US13834123

    申请日：2013-03-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Oliver V. Atassi ,  Oleg Petrenko

    IPC: F02K1/82 ,  F02K1/06

    CPC classification number: F02K1/15 ,  F02C3/04 ,  F02C7/36 ,  F02K1/06 ,  F02K1/82 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2260/81 ,  F05D2300/173 ,  F05D2300/6033 ,  Y02T50/672

    Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nacelle is arranged around the fan, and a bypass passage extends between the fan nacelle and the core engine. A variable area fan nozzle (VAFN) extends at least partially around the central axis and defines an exit area of the bypass passage. The VAFN is selectively movable to vary the exit area. The VAFN includes a body that defines an airfoil cross-section shape. The VAFN includes a wall that has a mechanical property distribution in accordance with a computer-simulated vibration profile of a flutter characteristic of the VAFN.

    Abstract translation: 燃气涡轮发动机包括至少具有压缩机部分，燃烧器部分和沿中心轴线布置的涡轮部分的核心发动机。 风扇被联接以由涡轮部分驱动。 风扇周围布置有风扇机舱，并且旁通通道在风扇机舱和核心发动机之间延伸。 可变区域风扇喷嘴（VAFN）至少部分地围绕中心轴延伸并且限定旁路通道的出口区域。 VAFN选择性地可移动以改变出口区域。 VAFN包括限定翼型横截面形状的主体。 VAFN包括具有根据VAFN的颤振特性的计算机模拟振动分布的机械特性分布的壁。

    Gas Turbine Engine Assembly Including A Thrust Reverser
    8.
    发明申请
    Gas Turbine Engine Assembly Including A Thrust Reverser 审中-公开
    包括推力逆变器的燃气轮机发动机组件

    公开(公告)号：US20140216005A1

    公开(公告)日：2014-08-07

    申请号：US13630234

    申请日：2012-09-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Dmitriy B. Sidelkovskiy ,  Robert E. Malecki ,  Oleg Petrenko

    IPC: F02K1/72

    CPC classification number: F02K1/72 ,  F02K3/06 ,  F05D2220/323

    Abstract: An exemplary gas turbine engine assembly includes a thrust reverser that is selectively moveable between a stowed position and a thrust reversing position. The thrust reverser includes an outer surface having a first outer surface area when the thrust reverser is in the stowed position and a second, smaller outer surface area when the thrust reverser is in the thrust reversing position.

    Abstract translation: 示例性的燃气涡轮发动机组件包括可在收起位置和推力反向位置之间选择性地移动的推力反向器。 推力反向器包括当推力反向器处于收起位置时具有第一外表面区域的外表面和当推力反向器处于推力反向位置时的第二较小的外表面区域。

    CONVERGENT DIVERGENT EXIT NOZZLE FOR A GAS TURBINE ENGINE
    10.
    发明申请
    CONVERGENT DIVERGENT EXIT NOZZLE FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的变流器出口喷嘴

    公开(公告)号：US20160195038A1

    公开(公告)日：2016-07-07

    申请号：US14817611

    申请日：2015-08-04

    Applicant: United Technologies Corporation

    Inventor： Dmitriy B. Sidelkovskiy ,  Oleg Petrenko ,  Robert E. Malecki ,  Steven H. Zysman

    IPC: F02K1/78 ,  F02C3/04 ,  F02K3/06

    CPC classification number: F02K1/78 ,  B64D29/00 ,  B64D29/02 ,  B64D29/04 ,  F02C3/04 ,  F02K1/00 ,  F02K1/36 ,  F02K1/40 ,  F02K1/52 ,  F02K1/82 ,  F02K3/06 ,  F02K3/077

    Abstract: A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.

    Abstract translation: 用于燃气涡轮发动机的机舱包括限定中心轴线并具有径向向外表面和径向向内表面的环形主体。 径向向内表面的后部包括轴向延伸的收敛发散出口。 轴向延伸的二次管道穿过会聚发散出口喷嘴中的机舱。 轴向延伸的次级管道包括在收敛发散出口喷嘴的收敛部分处的入口和在会聚发散出口喷嘴的发散部分处的出口。

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