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    Non-circular aft nacelle cowling geometry
    35.
    发明授权
    Non-circular aft nacelle cowling geometry 有权

    公开(公告)号：US09995180B2

    公开(公告)日：2018-06-12

    申请号：US14676354

    申请日：2015-04-01

    Applicant: United Technologies Corporation

    Inventor： Michael J. Murphy ,  Robert E. Malecki

    IPC: F01D25/24 ,  B64D29/02 ,  F02C3/10 ,  F01D25/28

    CPC classification number: F01D25/24 ,  B64D29/02 ,  F02C3/10

    Abstract: A nacelle for a turbofan propulsion system that extends along a centerline includes a forward cowling and an aft cowling. To improve the fit of a turbofan propulsion system in the space between the wing and ground of a fixed-wing aircraft, the aft cowling of the nacelle is modified. The aft cowling has a non-circular cross-sectional geometry disposed in a plane substantially perpendicular to the centerline. The non-circular cross-sectional geometry includes a radially recessed section disposed between first and second curved sections. The first and the second curved sections each have a radius that is greater than a radial distance between the centerline and a center point of the radially recessed section.

    TRACK FAIRING ASSEMBLY FOR A TURBINE ENGINE NACELLE
    38.
    发明申请
    TRACK FAIRING ASSEMBLY FOR A TURBINE ENGINE NACELLE 审中-公开
    用于涡轮发动机抽油烟机的履带组件

    公开(公告)号：US20160237856A1

    公开(公告)日：2016-08-18

    申请号：US14621456

    申请日：2015-02-13

    Applicant: United Technologies Corporation

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

    IPC: F01D25/28 ,  F01D25/24

    CPC classification number: F01D25/28 ,  B64D29/00 ,  B64D29/06 ,  F01D25/24 ,  F02C7/20 ,  F02K1/52 ,  F02K1/72 ,  F05D2240/55

    Abstract: The present disclosure relates generally to an aerodynamic track fairing assembly used on an engine nacelle, the track fairing assembly positionable on the aft section of the engine nacelle, the aerodynamic track fairing assembly including an upper section extending toward an aft end of the aft section of the engine nacelle, a bottom section extending toward the aft end of the aft section of the engine nacelle, the bottom section affixed to the upper section to form a track cavity therebetween, and a fairing fitting disposed within the track cavity and affixed to the bottom section.

    Abstract translation: 本公开总体上涉及在发动机舱上使用的空气动力学轨道整流罩组件，轨道整流罩组件可定位在发动机舱的后部，气动履带整流罩组件包括朝向后部的后部的后端延伸的上部 所述发动机舱，朝向所述发动机舱的后部的后端延伸的底部，所述底部固定到所述上部以在其间形成轨道腔;以及整流罩，其布置在所述轨道腔内并固定到所述底部 部分。

    EXHAUST NOZZLE ARRANGEMENT FOR GEARED TURBOFAN
    39.
    发明申请
    EXHAUST NOZZLE ARRANGEMENT FOR GEARED TURBOFAN 审中-公开
    用于齿轮涡轮机的排气喷嘴装置

    公开(公告)号：US20160201570A1

    公开(公告)日：2016-07-14

    申请号：US14875762

    申请日：2015-10-06

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Robert E. Malecki

    IPC: F02C7/36 ,  F02K3/06 ,  F02C3/10

    CPC classification number: F02C7/36 ,  B64D33/02 ,  B64D2033/0286 ,  F02C3/10 ,  F02C3/107 ,  F02K3/06 ,  F02K3/068 ,  F05D2220/36 ,  Y02T50/672

    Abstract: A propulsion system according to an example of the present disclosure includes, among other things, a geared architecture configured to drive a fan section including a fan, and a turbine configured to drive the geared architecture. The turbine has an exit point, and a diameter (Dt) defined as the radially outer diameter of a last blade airfoil stage in the turbine at the exit point. A nacelle at least partially surrounds a core engine housing. The fan configured to deliver air into a bypass duct is defined between the nacelle and the core engine housing. A core engine exhaust nozzle is downstream of the exit point, with a downstream most point of the core engine exhaust nozzle being defined at a distance (Lc or Ln) from the exit point.

    Abstract translation: 根据本公开示例的推进系统尤其包括被配置为驱动包括风扇的风扇部分和配置成驱动齿轮架构的涡轮机的齿轮架构。 涡轮机具有出口点，并且直径（Dt）被定义为涡轮机在出口处的最后叶片翼型段的径向外径。 机舱至少部分地围绕核心发动机壳体。 被配置为将空气输送到旁通管道中的风扇被限定在机舱和核心发动机壳体之间。 核心发动机排气喷嘴位于出口点的下游，核心发动机排气喷嘴的下游最点定义在距离出口点的距离（Lc或Ln）处。

    NACELLE INTERNAL AND EXTERNAL FLOW CONTROL
    40.
    发明申请
    NACELLE INTERNAL AND EXTERNAL FLOW CONTROL 审中-公开
    NACELLE内部和外部流量控制

    公开(公告)号：US20160003091A1

    公开(公告)日：2016-01-07

    申请号：US14768132

    申请日：2014-03-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Robert E. Malecki

    IPC: F01D17/10 ,  F01D15/08 ,  F01D25/24

    CPC classification number: F01D17/10 ,  B64D31/00 ,  B64D33/02 ,  B64D2033/0226 ,  F01D15/08 ,  F01D25/24 ,  F05D2220/32

    Abstract: A nacelle (12) for a gas turbine engine (10) that extends along an engine centerline (CO includes an inner portion (28), an outer portion (30), and a nacelle flow control system (26). The outer portion (30) surrounds the inner portion (28) and connects to the inner portion (28) at a leading edge (32). The nacelle flow control system (26) includes an internal flow control (38) for the inner portion (28) and an external flow control (40) for the outer portion (30).

    Abstract translation: 一种用于燃气涡轮发动机（10）的机舱（12），其沿着发动机中心线（CO包括内部部分），外部部分（30）和机舱流量控制系统（26）延伸，外部部分 所述机舱流量控制系统（26）包括用于所述内部部分（28）的内部流动控制（38）和所述内部部分（28）的内部流动控制（38），并且所述内部部分 用于外部部分（30）的外部流量控制（40）。

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