首页> 外国专利> Movable fin for turbo machine e.g. turbojet engine, of aircraft, has blade formed of wires or filaments connected together by binder, and vibration damping device arranged at interior of winglet and including viscoelastic material element

Movable fin for turbo machine e.g. turbojet engine, of aircraft, has blade formed of wires or filaments connected together by binder, and vibration damping device arranged at interior of winglet and including viscoelastic material element

机译：涡轮机的活动翅片飞机的涡轮喷气发动机，具有由通过粘合剂连接在一起的金属丝或细丝形成的叶片，以及布置在小翼内部并包括粘弹性材料元件的减振装置。

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摘要

The fin has a blade (116) formed of wires or filaments connected together by a binder. The blade defines a leading edge (116c) and a trailing edge (116d) between an extrados wall and an intrados wall. The blade includes a top (116b) provided at a blade end opposed to a bottom part. The blade top is provided with a winglet (116a) or vane, where the winglet includes a vibration damping device (20). The vibration damping device is arranged at an interior of the winglet, and includes a viscoelastic material element.

机译：鳍片具有刀片（116），该刀片由通过粘合剂连接在一起的金属丝或细丝形成。叶片在拱顶壁和拱顶壁之间限定前缘（116c）和后缘（116d）。叶片包括设置在与底部相对的叶片端的顶部（116b）。叶片顶部设置有小翼（116a）或叶片，其中小翼包括减振装置（20）。减振装置布置在小翼的内部，并且包括粘弹性材料元件。

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公开/公告号FR2964426A1

专利类型
公开/公告日2012-03-09

原文格式PDF
申请/专利权人 SNECMA;
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申请/专利号FR20100057035
发明设计人 FABRE ADRIEN;LOMBARD JEAN PIERRE;
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申请日2010-09-06
分类号F04D29/38;B64C11/26;F02K3/02;F02K3/06;F04D29/66;
国家 FR
入库时间 2022-08-21 17:04:08

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