高性能连续碳纤维增强碳化硅复合材料的制备及其高温力学性能的研究  

The preparation and the high-temperature properties of 3D C_f/SiC composite material by PIP process

作　　者：焦健[1] 史一宁 邱海鹏[1] 孙明[1] 李秀倩[1] 罗京华[1] 

机构地区：[1]北京航空制造工程研究所,北京100024 [2]空军驻北京地区军事代表室,北京100024

出　　处：《功能材料》2011年第B06期401-404,共4页Journal of Functional Materials

摘　　要：连续碳纤维增强碳化硅(Cf/SiC)复合材料以其耐高温、高强度、低密度等特性已成为新一代航空发动机高温部件的首选材料。采用聚合物浸渍裂解法(PIP)成功制备出适用于航空发动机高温部件的Cf/SiC复合材料,其密度为1.83g/cm3。在发动机典型工作温度1200℃条件下,通过本工艺制备Cf/SiC材料的弯曲强度高达712MPa,略高于材料的室温弯曲强度(641MPa)。这一现象可能由碳纤维在冷却过程中产生的残余应力引起。此外,在温度为1200℃、加载压力120MPa的条件下,材料的稳态高温蠕变速率为2.08×10-3%/h,基体开裂和界面滑动可能是材料宏观变形的主要原因。C_fSiC composite material is one of the most promising canchciates to sulastltute superattoy, which Has,been used in current aeronautic engine components working under high-temperature for decades. Towards the requirements of these high temperature components, we successfully prepared 3D C_f/SiC composite material via PIP process with a low density of 1.83g/cm^3. Subsequently, mechanical tests of this material including flexural properties and tensile creep were carried out at a typical engine working temperature of 1200℃. In the test of flexural properties, a flexural strength （δ^1200_b） of 712MPa was obtained, which is higher than the value of the same material measured at room temperature （δ^RT_b=641MPa）. This may be due to the deforming of carbon fiber occurred during the cooling process of the material. Furthermore, according to the obtained creep curve at 1200℃ and the constant stress of 120MPa, a creep rate of 2.08×10^-3%h was calculated, which agrees well with the creep rate of 3D C_f/SiC composite material prepared by CVI process measured under the similar condi tions.

关 键 词：聚合物浸渍裂解法 C_f/SiC复合材料 高温 力学性能 

分 类 号：TB332[一般工业技术—材料科学与工程]