航空发动机热结构部件的RMI工艺研究进展

Research Progress of RMI Process for Aero-Engine Thermal Structural Components

连续碳化硅纤维增韧碳化硅陶瓷基复合材料(SiC/SiC)具有低密度、高损伤容限、优异的高温力学和抗氧化性能等一系列优点,作为航空发动机热结构部件具有广阔的应用前景。复合材料的性能与制备工艺密切相关,相比于化学气相渗透(CVI)和先驱体浸渍裂解(PIP)工艺,反应熔体渗透(RMI)工艺具有周期短、成本低、制备的复合材料致密度高等特点,成为航空发动机热结构部件用SiC/SiC复合材料的研究热点。本文阐述了RMI工艺过程中碳硅反应基本原理,介绍了国内外RMI工艺研究现状,总结了该工艺目前存在的问题,并对未来工艺发展方向做出展望。

Continuous SiC fiber toughened SiC ceramic matrix composites(SiC/SiC)have a series of advantages such as low density,high damage tolerance,excellent high temperature mechanical properties and oxidation resistance,and have broad application prospects as aero-engine hot-section components.The performance of composite materials is closely related to the preparation process.Compared to chemical vapor infiltration(CVI)and precursor impregnation cracking(PIP)processes,reactive melt infiltration(RMI),the RMI process has the characteristics of short cycle,low cost,and high density of the prepared composite materials,and has become a research hotspot of SiC/SiC composite materials for aero-engine hot-section components.This paper expounds the basic principle of carbon-silicon reaction in the RMI process,introduces the research status of the RMI process at home and abroad,summarizes the current problems of the process,and makes an outlook on the future development direction of the process.