FEM ANALYSIS OF RESIDUAL STRESS AND DAMAGE OF EXPANDED HOLE IN AIRCRAFT ALLOY D16ChT
DOI:
https://doi.org/10.20535/2305-9001.2015.73.40272Keywords:
residual stress, damage, expanding hole, hardening, plastic strain, finite element method, aviation alloyAbstract
Purpose.Determination of residual stress, strain and initial damage distribution for expanding hole. Influence of this parameters on life time safety factor.
Design/methodology/approach. In article was realise finite element simulation of expanding hole process using explicit dynamic method for thee different levels of total plastic deformation 1%, 2%, 3%. It was taken in account damage parameter, which was described during D16chT alloy macro mechanical property degradation through elastic modulus change .
Findings.It is found that expanding hole plastic deformation 2% and 3% can damage hole surface even during expanding process and on starting point of life cycle.
Originality/value. These discourses, that only 1% total plastic deformation can increase life cycle safety factor on the external tension stress level behind 50-60 MPa.
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