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For a turbomachine compressor nozzle ring, including heads of blades montees with the aid of a vibration damper on the outer shell

机译：用于涡轮机压缩机喷嘴环，包括在外壳上带有减振器的叶尖头

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摘要

The stage (4) has a set of blades (14) arranged between concentric inner and outer shells (10, 12) and mounted on the inner and outer shells. A fixation unit fixes a blade tip (32) in a mortise (30) of the outer shell, where the fixation unit is in the form of a seal (34) made of vibration damping material i.e. silicone resin. Each blade has a root (18) mounted in a mortise (16) of the inner shell by another fixation unit that is in the form of weld (20). The inner shell is segmented, along a circumferential direction, into a set of angular sectors. Independent claims are also included for the following: (1) a turbomachine for an aircraft, comprising a compressor rectifier stage (2) a method for fabricating a compressor rectifier stage.

机译：平台（4）具有一组叶片（14），其设置在同心的内壳（10）和外壳（12）之间，并安装在内壳和外壳上。固定单元将叶片尖端（32）固定在外壳的榫眼（30）中，其中该固定单元为由减振材料即硅树脂制成的密封件（34）的形式。每个叶片具有根部（18），根部（18）通过呈焊接（20）形式的另一固定单元安装在内壳的榫眼（16）中。内壳沿着圆周方向被分成一组角扇区。还包括以下方面的独立权利要求：（1）一种用于飞机的涡轮机，包括压缩机整流器级（2）一种制造压缩机整流器级的方法。

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公开/公告号FR2950116B1

专利类型
公开/公告日2011-12-09

原文格式PDF
申请/专利权人 SNECMA;
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申请/专利号FR20090056332
发明设计人 CLAUDE MARCEL MONS;
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申请日2009-09-15
分类号F04D29/54;
国家 FR
入库时间 2022-08-21 17:04:19

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