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Supervised by Ministry of Industry and Information Technology of The People''s Republic of China Sponsored by Harbin Institute of Technology Editor-in-chief Yu Zhou ISSNISSN 1005-9113 CNCN 23-1378/T

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Related citation:Shuyuan Zhao,Zhengyu Li,Zeliang Pu,Xinyang Sun,Wenjiao Zhang.Thermal Stress and Assembling Parameters Evolution of CMC Bolted Joint under Transient Thermal Loads[J].Journal of Harbin Institute Of Technology(New Series),2021,28(3):1-8.DOI:10.11916/j.issn.1005-9113.2019038.
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Thermal Stress and Assembling Parameters Evolution of CMC Bolted Joint under Transient Thermal Loads
Author NameAffiliation
Shuyuan Zhao National Key Laboratory of Science and Technology for National Defense on Advanced Composites in Special Environments, Harbin Institute of Technology, Harbin 150080, China 
Zhengyu Li National Key Laboratory of Science and Technology for National Defense on Advanced Composites in Special Environments, Harbin Institute of Technology, Harbin 150080, China 
Zeliang Pu National Key Laboratory of Science and Technology for National Defense on Advanced Composites in Special Environments, Harbin Institute of Technology, Harbin 150080, China 
Xinyang Sun School of Aeronautics and Astronautics, Harbin Institute of Technology, Harbin 150001, China 
Wenjiao Zhang Engineering College, Northeast Agricultural University, Harbin 150030, China 
Abstract:
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.
Key words:  ceramic matrix composite  heat transfer  thermal stress  pre-load  bolt-hole clearance
DOI:10.11916/j.issn.1005-9113.2019038
CLC NUMBER:V19
Fund:
Descriptions in Chinese:
  

瞬态热载荷下陶瓷基复合材料螺栓连接结构热应力及装配参数演化

赵淑媛1,李正禹1,蒲泽良1,孙新杨2,张文娇3

(1哈尔滨工业大学 特种环境复合材料技术国家级重点实验室,哈尔滨 150080;

2哈尔滨工业大学 航天学院,哈尔滨 150001;

3东北农业大学 工程学院,哈尔滨 150030)

创新点说明:

采用有限元软件对陶瓷基复合材料和高温合金螺栓连接结构进行热力耦合分析,分析了瞬态热载荷作用下热应力及装配参数的变化,为避免连接结构的早期破坏提供理论基础。

研究目的:

陶瓷基复合材料由于其耐高温、耐磨、抗高温蠕变、导热系数和热膨胀系数较低等特点,逐渐在飞行器热结构上得到广泛的应用。在飞行器结构中,陶瓷基复合材料常常不可避免的与金属件组成连接结构。当这种类型的结构件被用于高温瞬态热载荷状态下时,由于陶瓷基复合材料与金属的热膨胀不匹配,会导致连接部位产生额外的热应力,并改变接头的连接参数,从而使结构提前发生破坏。因此,研究瞬态热加载对陶瓷基复合材料-高温合金螺栓连接结构的影响,对其在航空航天领域的运用具有重要意义。

研究方法:

针对2D编织C/SiC陶瓷基复合材料与高温合金GH4169组成的螺栓连接结构,使用有限元软件ABAQUS建立单钉单搭接螺栓连接结构的热分析模型。通过计算得到模型在给定的热边界载荷作用下的瞬态温度场,将温度场结果导入到应力场分析中,结合材料模型的UMAT程序,实现了模型的热力耦合分析。通过研究连接结构在高温热载荷作用下产生的热应力场,讨论了瞬态升温过程对连接结构预紧力、钉孔配合精度产生的影响

结果:

2D编织C/SiC复合材料与高温合金组成的螺栓连接结构在受到温度载荷作用而产生温度变化后,装配时施加的预紧力会发生松弛现象,并且螺栓钉孔间的间隙也会缩小,预紧力下降值与温度载荷值呈现线性关系,钉孔间隙的减小值与温度载荷值呈现二次曲线的关系。

结论:

本研究针对陶瓷基复合材料和高温合金螺栓连接结构,研究了瞬态热加载条件下结构热应力及螺栓预紧力和钉孔间隙等装配参数的演化,所得结果将用以指导工程实践中陶瓷基复合材料连接件的设计和使用。

关键词:陶瓷基复合材料;热分析;热应力;预紧力;钉孔间隙

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