Abstract
The content of titanium is about 0.63% in the earth’s crust, and it ranks 10th among all elements. The content of titanium is next to the metal elements of aluminum, iron and magnesium, iron, and magnesium; titanium alloys have low density, high specific strength (the ratio of tensile strength to density), wide working range (−253°C–600°C), and excellent corrosion resistance melting point; the chemical activity of titanium alloy is very high, and it easily reacts with hydrogen, oxygen, and nitrogen, so it is difficult to be smelted and processed, and the processing cost is high. Titanium alloys also have poor thermal conductivity (only 1/5 of iron and 1/15 of aluminum), small deformation coefficient, large friction coefficient, and other characteristics. They are widely used in aircraft fuselage, gas turbine, petrochemical, automotive industry, medical, and other fields for important parts.
Highlights
Because the depth of X-ray penetration is small, only the residual stress on the material’s surface can be measured. erefore, the electropolishing corrosion technique is used to polish the surface of the sample, peel off layer by layer, and measure the residual stress at different depths. e surface residual stresses at different cycles were measured when the stress ratio R was −1.0, −0.6, and 0.1, respectively, and the distribution of residual stress with cyclic loading and its effect on fatigue strength are studied
It can be found that the fatigue cracks all start from the surface of the crack, and the origin of the crack is a bright white spot
It is found by observing the fatigue fracture surface of the unrelieved stress specimen that the location of fatigue initiation is different for different stress ratios, see Table 3
Summary
It can be found that the fatigue cracks all start from the surface of the crack, and the origin of the crack is a bright white spot. It is found by observing the fatigue fracture surface of the unrelieved stress specimen that the location of fatigue initiation is different for different stress ratios, see Table 3. When the stress ratio R is −1.0 and 0.6, the fatigue crack
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