首页> 外国专利> High pressure turbine ring assembly for gas turbine of aviation engine, has ring sectors with pie shaped section, and upstream and downstream end portions of tabs maintained without radial clearance by metallic ring support structure

High pressure turbine ring assembly for gas turbine of aviation engine, has ring sectors with pie shaped section, and upstream and downstream end portions of tabs maintained without radial clearance by metallic ring support structure

机译：用于航空发动机的燃气轮机的高压涡轮机环组件，具有带扇形截面的环扇形部分，并且凸片的上游和下游端部通过金属环支撑结构保持无径向间隙

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摘要

The assembly has ring sectors (10) made of a single piece and of composite material with ceramic matrix. Each sector has an annular base (12) whose inner face defines an inner face of turbine ring (1). The base has an outer face from which an upstream tab (14) and a downstream tab (16) are extended. Upstream end portion (14a) and downstream end portion (16a) of the tabs are engaged in a hook (34) of a metallic ring support structure (3). The ring sectors have a section in the shape of pie, and the end portions of the tabs are maintained without radial clearance by the structure.

机译：该组件具有由单个部件以及具有陶瓷基体的复合材料制成的环形扇区（10）。每个区段具有环形基部（12），该环形基部的内表面限定涡轮环（1）的内表面。基座具有外表面，上游凸片（14）和下游凸片（16）从该外表面延伸。突片的上游端部（14a）和下游端部（16a）接合在金属环支撑结构（3）的钩（34）中。环形扇区具有扇形的截面，并且通过该结构保持凸片的端部没有径向间隙。

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公开/公告号FR2942845A1

专利类型
公开/公告日2010-09-10

原文格式PDF
申请/专利权人 SNECMA;SNECMA PROPULSION SOLIDE;
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申请/专利号FR20090051446
发明设计人 DENECE FRANCK ROGER DENIS;GENDRAUD ALAIN DOMINIQUE;HABAROU GEORGES;ILLAND HUBERT;
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申请日2009-03-09
分类号F01D11/08;F01D11/12;F02C7/28;
国家 FR
入库时间 2022-08-21 18:26:34

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