首页> 外国专利> Method for treating fatigue crack of turbojet engine of aircraft, involves measuring temperature value in zone around propagation end of fatigue crack, and stopping compression of machine element when value corresponds to reference value

Method for treating fatigue crack of turbojet engine of aircraft, involves measuring temperature value in zone around propagation end of fatigue crack, and stopping compression of machine element when value corresponds to reference value

机译：一种飞机涡轮喷气发动机疲劳裂纹的处理方法，包括测量疲劳裂纹传播端周围区域的温度值，并在该值与参考值相对应时停止机械元件的压缩

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摘要

The method involves compressing a machine element perpendicular to a surface on a zone around a propagation end of a fatigue crack by hammering the element on the end by using a compression device (12). A value of parameter i.e. temperature, in the zone is measured by a measurement device (14). The measured value is compared with a reference value by a comparison module (16). Compression of the element is stopped by a stop module (18) when the measured value corresponds to the reference value, where the compression, measurement and comparison steps are performed in a simultaneous manner. An independent claim is also included for a system for treating fatigue crack of a mechanical element.

机译：该方法包括通过使用压缩装置（12）在末端上锤击元件，从而在与疲劳裂纹的传播末端周围区域垂直的表面上压缩机器元件。通过测量装置（14）测量该区域中的参数值，即温度。通过比较模块（16）将测量值与参考值进行比较。当测量值对应于参考值时，由停止模块（18）停止元件的压缩，其中压缩，测量和比较步骤同时进行。还包括用于处理机械元件的疲劳裂纹的系统的独立权利要求。

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公开/公告号FR2983101A1

专利类型
公开/公告日2013-05-31

原文格式PDF
申请/专利权人 SNECMA;
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申请/专利号FR20110060927
发明设计人 DERRIEN GERARD;
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申请日2011-11-29
分类号B23P9/04;B23P15/02;G01N3/08;G01N3/34;
国家 FR
入库时间 2022-08-21 16:21:02

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