Search Results for fatigue crack propagation

Fig. 24 Mechanism of fatigue crack propagation by alternate slip at the crack tip. Sketches are simplified to clarify the basic concepts. (a) Crack opening and crack-tip blunting by slip on alternate slip planes with increasing tensile stress. (b) Crack closure and crack-tip resharpening More

Fig. 23 Mechanism of fatigue crack propagation by alternate slip at the crack tip. Sketches are simplified to clarify the basic concepts. (a) Crack opening and crack tip blunting by slip on alternate slip planes with increasing tensile stress. (b) Crack closure and crack tip resharpening More

Fig. 10 Crack tip stress-intensity control of fatigue crack propagation in 7075-T6 aluminum alloy sheet—long-transverse loading. Remote and wedge force methods of loading specimens in aqueous 3.5% sodium chloride environment and benign dry air environment. Source: Ref 46 More

Fig. 39 (a) Fatigue crack propagation regimes and (b) crack growth rates of wrought aluminum alloys. L-T, longitudinal transverse; T-L, transverse longitudinal. Source: Ref 65 More

Fig. 15 Mechanism of fatigue crack propagation by alternate slip at the crack tip. Sketches are simplified to clarify the basic concepts. (a) Crack opening and crack tip blunting by slip on alternate slip planes with increasing tensile stress. (b) Crack closure and crack tip resharpening More

Fig. 3 Thermal fatigue failure and conventional fatigue crack-propagation fracture during reversed-load cycling of acetal. Source: Ref 36 More

Fig. 9 Comparison of fatigue crack propagation rates of BE and I/M Ti-6Al-4V as a function of the stress intensity factor range at room temperature in air. Stress ratio ( R ), +0.1 ( R = σ min /σ max , where σ min is the minimum stress and σ max is the maximum stress); frequency ( f ), 5 Hz More

Fig. 9 Fatigue-crack propagation in alloy 2048-T851 plate More

Fig. 15 Fatigue crack propagation data for 2090-T83 sheet, 2090-T81 plate, and 7×75-T6 sheet. Crack orientation, L-T (crack plane and propagation direction perpendicular to the principal direction of metal-working); stress ratio ( R ), 0.33. Testing conducted in high-humidity air (>90 More

Fig. 10 Schematic representation of fatigue crack propagation behavior. In regime I the crack growth rate is low since the threshold for crack propagation is approached. In regime II the so-called Paris law is obeyed while in regime III the crack growth rate increases above that predicted More

Fig. 10 Plots of n and C from the Paris fatigue crack propagation equation, comparing noted microstructures in a number of steels with various quality levels and testing orientations More

Fig. 11 Comparison of n and C values for the Paris fatigue crack propagation equation comparing three grades of steel with various quality levels and testing orientations. No effect of strength level is shown. More

Fig. 13 Plots of n and C from the Paris fatigue crack propagation equation for A633C steels in salt water in conventional and calcium-treated quality levels and three testing orientations (LT, TL, SL). Comparison is made to overall scatterband of all carbon and alloy steels in air testing More

Fig. 42 Fractography of fatigue crack propagation at intermediate (region 2) and high (region 3) growth rates in steels tested in moist air at R = 0.1. See text for details about regions. (a) Ductile striations in 9Ni-4Co steel at Δ K = 30 MPa m . (b) Additional cleavage fracture More

Fig. 63 Influence of testing temperature on fatigue crack propagation exponent for iron-based alloys. Source: Ref 68 More

Fig. 22 Fatigue crack propagation behavior of modified 9Cr-1Mo steel (ASTM A387, grade 91), tested in air at room temperature (800 cpm) and at elevated temperatures (40 cpm). R = 0.05. Source: Ref 25 More

Fig. 22 Fatigue crack propagation behavior of various polymers. Source: Ref 51 More

Fig. 14 Composite plot of Waspaloy fatigue crack propagation data. GS, grain size More

Fig. 15 Fatigue crack propagation response of small γ′ materials. (a) Results plotted vs. Δ K eff , thus accounting for crack closure. (b) Material response at R = 0.8 More

Fig. 18 Vacuum and air/vacuum/air fatigue crack propagation tests. Results for alloy II-S at 427 °C and R = 0.1. Environmental and closure effects can be separated. More