DISCHARGE SYSTEM OF A SEPARATED TWIN-FLOW TURBOJET FOR AN AIRCRAFT, CORRESPONDING TURBOJET AND ASSOCIATED DESIGN METHOD
    2.
    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

    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。

    Discharge system of a separated twin-flow turbojet for an aircraft, corresponding turbojet and associated design method

    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

    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.

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