SiC單纖維增強(qiáng)TC17復(fù)合材料橫向拉伸性能研究

SiC單纖維增強(qiáng)TC17復(fù)合材料橫向拉伸性能研究RESEARCH ON SINGLE SIC FIBER REINFORCED TC17 COMPOSITES UNDER TRANSVERSE TENSION

采用單纖維十字架結(jié)構(gòu)試樣測(cè)試分析了SiC纖維增強(qiáng)TC17復(fù)合材料橫向力學(xué)性能，利用SEM對(duì)拉伸斷口及橫切面進(jìn)行了顯微觀察，分析了界面失效位置，并結(jié)合有限元數(shù)值模擬計(jì)算，研究了界面損傷失效機(jī)制及裂紋擴(kuò)展規(guī)律。結(jié)果表明，在橫向載荷的作用下，單纖維試樣應(yīng)力-應(yīng)變曲線的非線性拐點(diǎn)應(yīng)力值為271±12MPa，該點(diǎn)是界面完全失效的起始點(diǎn)。復(fù)合材料界面失效模式為剪切失效，裂紋萌生于反應(yīng)層和碳涂層的界面，位置在與加載方向成40°~50°的圓周之間。裂紋萌生后，在剪切應(yīng)力作用下沿軸向和周向同時(shí)擴(kuò)展，在沿周向擴(kuò)展過程中，0°附近界面在徑向拉伸應(yīng)力作用下先于90°附近界面失效，隨后90°附近界面在周向剪切應(yīng)力作用下失效。界面完全失效后，應(yīng)力重新分配，隨載荷增加界面張開程度加大，基體局部出現(xiàn)屈服，直至材料完全斷裂。

Transverse mechanical properties of TMCs play an important role during its engineering service. Although SiCf/TC17 composite is one of the most promising TMC candidates for aeroengine, its transverse properties have not been reported yet. In this paper, transverse strength of single SiC fiber reinforced TC17 composite was evaluated using cruciform specimen. The surface and cross-section of fractured specimen were investigated by SEM to determine the failure position during tensile test. Finite element simulation method was also used to analyze the mechanism of interfacial failure and crack propagation. During the transverse tensile test of single fiber specimen, the initial non-linearity in the stress-strain curve occurred at the stress of 271±12MPa, which indicated the beginning of fiber-matrix interface failure. The finite element simulation results based on bilinear cohesive element model showed that transverse fracture of composite interface was shear failure mode. Before the occurrence of non-linearity in the stress-strain curve, the crack initiated at the circular interface between reaction layer and carbon coating with a 40°~50° angle to the applied loading direction. Then the crack propagated along both circumferential and axial direction because of the shear stress. As the crack growing, the interface close to 0° angle to the applied loading direction failed first caused by the radial tensile stress, whereas the interface near 90° failed later as a result of circumferential shear stress. After complete failure of the interface, stress redistribution occurred around the SiC fiber and the interface separation increased with the increasing of the applied load, which gave rise to the yielding and deforming of the matrix near fiber until the final fracture of the composite.

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