Fig. 7 Distribution of welding in first accumulator More

Fig. 11 Section at sixth circular seam of first accumulator showing seal-weld and fissures × 1 1 4 More

Fig. 13 Termination of fissure in first accumulator × 150 More

Fig. 3 Fractured clamping rods (note the fracture location is on the first or second thread) More

Fig. 10 Vibrational fracture of a screw in the first supporting thread. Fractue, 1× b). Longitudinal section, etched in copper ammonium chloride. 2× More

Fig. 4 Weibull plot of first sample test. More

Fig. 1 Schematic of first-stage gas turbine blade that experienced cracking after 32,000 h in service. (a) Sectioning planes at three locations on the blade airfoil. (b) Cross-sectional view of the blade airfoil showing the cooling holes and numbering sequence More

Fig. 1 (a) Some blades belonging to the first two rows of blades of the IP turbine. (b) Mounds of unidentified deposits on the inside of the shroud of the first row of blades on the IP turbine in 1979. More

Fig. 85 Fracture obtained by first plastic straining in torsion and then straining in tension. The fracture appearance becomes more characteristic of the first strain increment as the first strain increment increases in magnitude. Source: Ref 4 More

Fig. 2 First fixture used by Lodge to simulate spalling. Source: Ref 4 More

Fig. 4 Examples of thermal-mechanical fatigue cracking and oxidation in a first-stage turbine blade More

Fig. 12 Heat-damaged turbine blades. (a) Heat-damaged first- or second-stage turbine blade (A), which remained intact but with a darkened appearance. It is common to have blades that appear to be in relatively good condition but with an underlying overtemperature condition. (b) Two third-stage More

Fig. 20 Schematic of first-stage gas turbine blade that experienced cracking after 32,000 h in service. (a) Sectioning planes at three locations on the blade airfoil. (b) Cross-sectional view of the blade airfoil showing the cooling holes and numbering sequence More

Fig. 13 X-ray photoelectron spectroscopy montage display of iron in the first eight sputter cycles of the depth profile (Fig. 6) More

Fig. 14 X-ray photoelectron spectroscopy montage display of Cr in the first nine sputter cycles of the depth profile (Fig. 6) More

Fig. 19 Illustration of the first-passage problem More

Fig. 2 Cracked first steps MAR-M302 Turbine engine vane in the as-received condition. (a) Concave airfoil surface; (b) Convex airfoil surface. Metallographic sampling location indicated by arrow M. More

Fig. 1 The horizontal crack happened first (see text). More

Fig. 1 Fragments of first crankcase. 1 × More

Fig. 2 Fracture of first crankcase. 1 × More