Nozzle for an aircraft turboprop engine with an unducted fan

    公开(公告)号:US10113506B2

    公开(公告)日:2018-10-30

    申请号:US14881886

    申请日:2015-10-13

    Applicant: AIRCELLE

    Abstract: The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.

    NOZZLE FOR AN AIRCRAFT TURBOPROP ENGINE WITH AN UNDUCTED FAN
    2.
    发明申请
    NOZZLE FOR AN AIRCRAFT TURBOPROP ENGINE WITH AN UNDUCTED FAN 审中-公开
    用于具有开发风扇的飞机涡轮发动机的喷嘴

    公开(公告)号:US20160032863A1

    公开(公告)日:2016-02-04

    申请号:US14881886

    申请日:2015-10-13

    Applicant: AIRCELLE

    Abstract: The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.

    Abstract translation: 本公开提供了一种用于具有未引导风扇的飞机涡轮螺旋桨发动机的喷嘴,包括:内壁,与内壁径向间隔开并与内壁同心的外壁,内壁和外壁的接合面积包括 开口包含在横向于喷嘴的纵向轴线的平面中。 特别地,内壁和外壁的接合区域包括两个连接板和用于将两个连接板固定在一起的构件,或者以另一种形式,连接区域包括固定到内壁的垫,以及固定到 外壁,面向喷嘴内壁的垫。

    Gas ejection cone for aircraft turbojet engines

    公开(公告)号:US09611807B2

    公开(公告)日:2017-04-04

    申请号:US14484684

    申请日:2014-09-12

    Applicant: AIRCELLE

    CPC classification number: F02K1/36 B64C7/02 F02K1/04

    Abstract: A gas ejection cone includes a cylindrical-shaped front cone portion, a conical-shaped rear cone portion, a ventilation tube and a support bearing of this drainage and/or ventilation tube. The ventilation tube extends inside the cylindrical-shaped front and conical-shaped rear cone portions and emerges at the end of the conical-shaped rear cone portion. In particular, the conical-shaped rear cone portion includes a front sub-portion connected to the cylindrical-shaped front cone portion, and a rear sub-portion removably secured to the front sub-portion. The rear sub-portion is further equipped with an outlet port of the ventilation tube.

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