Search Results for solution treating

Fig. 21 Effect of solution-treating temperature on the solution-treated and aged properties of Ti-6Al-4V. Age cycle: 540 °C (1000 °F) for 8 h More

Fig. 20 Effect of solution-treating temperature on the tensile properties of Ti-6Al-4V More

Fig. 26 Microstructures after solution treating below, near, and above the β-transus temperature; forged and aged prior to solution treatments. Etch: Kroll’s reagent. Ti-6Al-2Sn-4Zr-6Mo, β-transus temperature: 935 °C (1715 °F). Prior treatment: forged below β transus at 870 °C (1600 °F), water More

Fig. 8 Tensile properties of alloy QE22A-T6 as functions of solution-treating temperature. Data were obtained from test bars of casting alloy QE22A-T6 machined from 25 mm (1 in.) diam cast specimens. The bars were held at temperature for 4 h. More

Fig. 18 Fixture for solution treating and end quenching of 18 depleted uranium bars More

Fig. 61 Effect of stretching (after solution treating and quenching) on the number and size of precipitation platelets on aged 2024. All specimens aged 12 h at 190 °C (375 °F). (a) 2024-T6, no stretching after quenching. (b) 2024-T81 stretched 1.5% before aging, resulting in smaller and more More

Fig. 4 Example of a solution treating and aging cycle for Inconel 718 that uses a double aging treatment. Source: Ref 8 More

Fig. 42 Examples of TTS fracture in Ti-6Al-4V α-β alloys. (a) Solution treated and aged microstructure consisting of about 10-μm diam primary α particles in a matrix of about 70 vol% of fine Widmanstätten α and β. The microstructural constituents are not evident on the fracture surface More

Fig. 872 Fracture surface of a specimen of Duranickel, vacuum solution treated and quenched, aged 1 h at 500 °C (930 °F) and cooled in air. The specimen, which was notched, precracked, and slow-bend fracture-toughness tested in hydrogen, broke by combined cleavage and intergranular fracture More

Fig. 1088 Transgranular corrosion-fatigue crack propagation in a solution-treated and peak-aged Al-5.6Zn-1.9Mg sample tested in humid nitrogen gas. Compare with Fig. 1091 and 1092 . SEM, 5000× (R.E. Ricker, University of Notre Dame, and D.J. Duquette, Rensselaer Polytechnic Institute) More

Fig. 50 Stress-corrosion cracking of a solution-treated and aged Ti-6Al-4V Apollo service propulsion system (SPS) fuel pressure vessel during a system checkout test. Fluid test medium was methanol. (a) Cross section adjacent to weld in cracked vessel. 65×. (b) Another crack near the same weld More

Fig. 1 Aging curves for cast and solution-treated C81800 More

Fig. 2 Aging curves for cast and solution-treated C82000 More

Fig. 3 Hot hardness of C82000, TF00 temper. Cast specimens were solution treated, then aged at 480 °C (900 °F). Useful design range is up to about 400 °C (750 °F). More

Fig. 6 Aging curves for solution-treated C82500 or beryllium-copper alloy 21C More

Fig. 7 Hot hardness of C82500, TF00 temper. Specimens were solution treated, then aged at 345 °C (650 °F). More

Fig. 9 Aging curves for solution-treated C82800 More

Fig. 10 Hot hardness of 82800, TF00 temper. Specimens were solution treated, then aged at 345 °C (650 °F). More

Fig. 7 Effect of cutting speed and feed in the face milling of solution-treated and aged Ti-6Al-2Sn-4Zr-2Mo having 321 HB hardness. Feed rate: A, 0.25 mm/tooth (0.010 in./tooth) and B, 0.13 mm/tooth (0.005 in./tooth). The cutter was a 100 mm (4 in.) diam single-tooth face mill with a C-2 (883 More

Fig. 9 Effect of cutting speed and cutting fluids in drilling solution-treated and aged Ti-6Al-4V having 375 HB hardness. Cutting fluids, wear rates, and tool life: A, chemical emulsion (1:15), 0.15 mm (0.006 in.) wear at 13 m/min (43 sfm), 250 holes; B, heavy-duty soluble oil (1:15), 0.15 mm More