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Thermal Stress and Assembling Parameters Evolution of CMC Bolted Joint under Transient Thermal Loads

Journal of Harbin Institute of Technology(New Series) 2021年第3期28卷 1-8页

作者： Shuyuan Zhao Zhengyu Li zeliang pu Xinyang Sun Wenjiao Zhang National Key Laboratory of Science and Technology for National Defense on Advanced Composites in Special Environments Harbin Institute of TechnologyHarbin 150080China School of Aeronautics and Astronautics Harbin Institute of TechnologyHarbin 150001China Engineering College Northeast Agricultural UniversityHarbin 150030China

Ceramic matrix composite(CMC) and superalloy bolted joints have exhibited great potential for high temperature hot structure application in hypersonic aircraft. In service conditions, the thermal expansion mismatch between CMC and superalloy plates will cause complex thermal stress and strain distributions at hole-edge areas and assembly parameters changes of the joints under elevated temperatures. These effects might lead to early damage of joint structure, which will endanger the structural integrity and load carrying capacity of aircraft components. In the present study, transient heat transfer and thermo-structural analysis of C/SiC composite and superalloy bolted joint were carried out by using a commercial FEA software ABAQUS. The stress distributions at hole-edge areas, pre-load loosening, and variation of bolt-hole clearance of CMC bolted joints under transient temperature rises were discussed for better understanding of high temperature structural behaviors. Results showed that pre-load declined with the increase of imposed hot side temperature, due to the thermal expansion mismatch between CMC and superalloy. The bolt-hole clearance for the composite plate decreased, whereas the clearance for the superalloy plate increased with the rise of temperature.

关键词： ceramic matrix composite heat transfer thermal stress pre-load bolt-hole clearance

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Bolt Design of Ceramic Matrix Composite and Superalloy Bolted Joint Based on Damage Failure Load

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Journal of Harbin Institute of Technology(New Series) 2021年第2期28卷 55-61页

作者： Chao Lv Shuyuan Zhao Zhengyu Li zeliang pu Jianglong Dong Xinyang Sun Wenjiao Zhang China Academy of Aerospace Aerodynamics Beijing 100074China National Key Laboratory of Science and Technology for National Defense on Advanced Composites in Special Environments Harbin Institute of TechnologyHarbin 150080China School of Aeronautics and Astronautics Harbin Institute of TechnologyHarbin 150001China Engineering College Northeast Agricultural UniversityHarbin 150030China

Ceramic matrix composite(CMC)and superalloy bolted joints are commonly used high temperature connection structures in aerospace and aeronautical fields.In this paper,a finite element model coupled with progressive damage analysis of 2D C/SiC composites and superalloy bolted joint was implemented to simulate the uniaxial tensile loading process by using the ABAQUS finite element software.The parametric effects of raised head bolt on stress distribution,tensile performance,and damage process were studied for the CMC⁃superalloy bolted joint structures.The results showed that the final failure load increased first to the maximum value,and then decreased with the rise of bolt diameter,bolt head diameter,and bolt head thickness,respectively.When the three parameters were 5.0 mm,9.5 mm,and 2.8 mm for the current studied bolt configuration,the joint structure gave the maximum load bearing capacity for the considered parameter ranges.It was also found that around 42%potential improvement in load bearing capacity could be achieved by very small adjustments in bolt parameters of the joints.

关键词： 2D C/SiC composite progressive damage analysis tensile properties bolted joint bolt parameters

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