HIGH TEMPERATURE TENSILE STRENGTH ANALYSIS OF C/SIC COMPOSITE AND SUPERALLOY BOLTED JOINT STRUCTURE

摘要

Ceramic Composite Materials (CMC) and superalloy bolted joint structures have received considerable attention for propulsion system and vehicle hot structure applications. In their service conditions, the hybrid bolted joint structures are subjected to superimposed thermal and mechanical loads. The thermal expansion mismatch between CMC and superalloy plates will cause complex thermal stress and strain distribution at hole-edge area and significant changes in assembly parameters of the joint. These effects might lead to early damage of joint structure, which will endanger the structural integrity and load carrying capacity of aircraft components. To address this issue, in this work, a progressive damage model for 2D woven C/SiC composite including a nonlinear macroscopic constituent model and Tsai-Wu failure criterion was established to predict high temperature tensile performance and failure behavior of single-lap, single-bolt 2D C/SiC composite and superalloy joint. The variations of failure strength with imposed temperature and bolt preload were discussed for the studied bolted joint. The present work provides valuable information in design of CMC joint structures on next-generation aircrafts.