SiC_(f)/SiC复合材料涡轮导向叶片的抗热冲击性能研究  

Study on the Thermal Shock Property of Turbine Guide Blade of SiC_(f)/SiC Composites

作　　者：焦春荣 赵春玲 孙世杰 高晔 杨金华 蒋康河 贺宜红 焦健 JIAO Chunrong;ZHAO Chunling;SUN Shijie;GAO Ye;YANG Jinhua;JIANG Kanghe;HE Yihong;JIAO Jian(National Key Laboratory of Advanced Composites,AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China;AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,Hunan,China)

机构地区：[1]中国航发北京航空材料研究院先进复合材料国防科技重点实验室,北京100095 [2]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《陶瓷学报》2021年第2期301-307,共7页Journal of Ceramics

基　　金：国家科技重大专项(2017-VI-0007-0077)。

摘　　要：SiC_(f)/SiC复合材料是新型航空发动机热端部件的标志性材料,涡轮导叶在发动机中的服役环境最为苛刻,其中,抗热冲击性能是考核导叶的关键性能之一。本文以不同铺层方式的SiC_(f)/SiC复合材料涡轮导向叶片的叶身典型结构为研究对象,针对不同SiC纤维铺层方式对叶身结构的成型缺陷、水淬热震性能等的影响进行了探索研究,结果显示:采用单向铺层制备的叶身质量均匀、内部致密,但是抗热冲击性能最差,仅仅十几个循环后便彻底开裂;采用正交铺层得到的叶身内部存在少量的孔洞和分层缺陷,抗热冲击性能可达到30次以上;要获得较好的抗热冲击性能,叶身环向纤维比例应大于1/2。SiC_(f)/SiC composites are the landmark materials for new type of aeroengine hot-section component.The engine service environment of the turbine guide vanes is the most critical,while thermal shock resistance is one of the most important properties.In this paper,thermal shock resistance of blade body structures with different laminates of SiC_(f)/SiC composites was studied.The eflect of the laminate structure on the formation of defects in the blades and the water quenching thermal shock performance were evaluated.It is found that the blade with unidirectional laminated structure has uniform and dense microstructure,but its thermal shock resistance is the worst,which cracks completely after only ten cycles.Although there are more holes and defects in the blade with orthogonal lamination,it possesses stronger thermal shock resistance with more than 30 cycles.The ratio of the circumferential fibers should be more than 1/2,in order to achieve sufficiently high thermal shock resistance for the blade.

关 键 词：叶身 热冲击性能 水淬试验 

分 类 号：TQ174.75[化学工程—陶瓷工业]