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    CONVERGENT-DIVERGENT NOZZLE FOR A TURBINE ENGINE
    1.
    发明申请
    CONVERGENT-DIVERGENT NOZZLE FOR A TURBINE ENGINE 有权
    用于涡轮发动机的多变流量喷嘴

    公开(公告)号：US20150033747A1

    公开(公告)日：2015-02-05

    申请号：US14363508

    申请日：2012-12-04

    Applicant: SNECMA

    Inventor： Matthieu Leyko ,  Jean Bertucchi ,  Mathieu Gaillot

    IPC: F02K1/00

    CPC classification number: F02K1/00 ,  F02K1/82 ,  F02K3/06 ,  F05D2250/71

    Abstract: A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitudinal section that are modeled by curves having respective radii of curvature that are identical in absolute value.

    Abstract translation: 涡轮发动机会聚发散喷嘴，包括环形中心元件和环形盖，该环形中心元件和环形盖同轴地布置在中心元件周围，以与中心元件配合以限定用于来自发动机的气流的环形流动通道。 在喉部和喷嘴的喷射部分之间，中心元件和帽在纵向截面中呈现相应的内部轮廓，该曲线由具有相同绝对值相同的曲率半径的曲线建模。

    Convergent-divergent nozzle for a turbine engine
    2.
    发明授权
    Convergent-divergent nozzle for a turbine engine 有权

    公开(公告)号：US09683516B2

    公开(公告)日：2017-06-20

    申请号：US14363508

    申请日：2012-12-04

    Applicant: SNECMA

    Inventor： Matthieu Leyko ,  Jean Bertucchi ,  Mathieu Gaillot

    IPC: F02K1/00 ,  F02K1/82 ,  F02K3/06

    CPC classification number: F02K1/00 ,  F02K1/82 ,  F02K3/06 ,  F05D2250/71

    Abstract: A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitudinal section that are modeled by curves having respective radii of curvature that are identical in absolute value.

    Discharge system of a separated twin-flow turbojet for an aircraft, corresponding turbojet and associated design method
    3.
    发明授权
    Discharge system of a separated twin-flow turbojet for an aircraft, corresponding turbojet and associated design method 有权

    公开(公告)号：US09726111B2

    公开(公告)日：2017-08-08

    申请号：US13950608

    申请日：2013-07-25

    Applicant: SNECMA

    Inventor： Matthieu Leyko ,  Jean Bertucchi ,  Arthur Droit

    IPC: F02K1/78 ,  B64D33/04 ,  F02K1/52 ,  F02K3/06 ,  F02C7/12

    Abstract: A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of annular shape defining upstream and downstream portions of the cowl and which is traversed by the suspension mast. The downstream portion of the cowl of the main nozzle includes a first part extending downstream from the upstream portion of the cowl to a trailing edge of the main nozzle, on either side of the suspension mast along two predefined angular sectors; and a second part formed from an internal contour of the slot and having a trailing edge with a diameter smaller than that of the trailing edge associated with the first part of the downstream portion of the cowl. Connecting walls laterally connect the first and second parts of the downstream portion.

    DISCHARGE SYSTEM OF A SEPARATED TWIN-FLOW TURBOJET FOR AN AIRCRAFT, CORRESPONDING TURBOJET AND ASSOCIATED DESIGN METHOD
    5.
    发明申请
    DISCHARGE SYSTEM OF A SEPARATED TWIN-FLOW TURBOJET FOR AN AIRCRAFT, CORRESPONDING TURBOJET AND ASSOCIATED DESIGN METHOD 有权
    用于飞机的相应的双流涡轮机的排放系统，相应的涡轮机和相关设计方法

    公开(公告)号：US20140061331A1

    公开(公告)日：2014-03-06

    申请号：US13950608

    申请日：2013-07-25

    Applicant: SNECMA

    Inventor： Matthieu LEYKO ,  Jean Bertucchi ,  Arthur Droit

    IPC: F02K1/78

    CPC classification number: F02K1/78 ,  B64D33/04 ,  F02C7/12 ,  F02K1/52 ,  F02K3/06 ,  Y02T50/675 ,  Y10T29/49346

    Abstract: A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of annular shape defining upstream and downstream portions of the cowl and which is traversed by the suspension mast. The downstream portion of the cowl of the main nozzle includes a first part extending downstream from the upstream portion of the cowl to a trailing edge of the main nozzle, on either side of the suspension mast along two predefined angular sectors; and a second part formed from an internal contour of the slot and having a trailing edge with a diameter smaller than that of the trailing edge associated with the first part of the downstream portion of the cowl. Connecting walls laterally connect the first and second parts of the downstream portion.

    Abstract translation: 公开了一种用于飞机的分离的双流涡轮喷气发动机的排出系统，其由悬架杆支撑。 该系统包括由环形整流罩限定的主喷嘴，其具有限定整流罩的上游和下游部分的环形形状的狭槽，并且由悬架桅杆穿过。 主喷嘴的整流罩的下游部分包括在整流罩的上游部分的下游延伸到主喷嘴的后缘的第一部分，沿着两个预定义的角度部分在悬架的两侧; 以及第二部分，其由所述狭槽的内部轮廓形成，并具有直径小于与所述整流罩的所述下游部分的所述第一部分相关联的所述后缘的直径的后缘。 连接壁横向连接下游部分的第一和第二部分。

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