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Published: 01 January 1990
Fig. 9 Effect of cobalt on hot corrosion; modified Udimet 700, 170 1-h cycles at 900 °C (1650 °F), with 0.5 ppm by weight Na as NaCl, Mach 0.5 More
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Published: 01 January 2003
Fig. 8 Types of sustained hot corrosion of a pure metal. Site I is the oxide-salt interface, and site II is the salt-gas interface. Source: Ref 15 More
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Published: 01 January 2003
Fig. 11 The role of chromium in inhibiting hot corrosion attack More
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Published: 01 January 2003
Fig. 16 Ni-20Cr-2ThO 2 after simulated type I hot-corrosion exposure (coated with Na 2 SO 4 and oxidized in air at 1000 °C, or 1832 °F). A, nickel-rich scale; B, Cr 2 O 3 subscale; C, chromium sulfides. Courtesy of I.G. Wright, Battelle Columbus Division More
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Published: 01 January 2002
Fig. 11 Hot corrosion attack of René 77 nickel-base alloy turbine blades. (a) Land-based, first-stage turbine blade. Notice deposit buildup, flaking, and splitting of leading edge. (b) Stationary vanes. (c) A land-based, first-stage gas turbine blade that had type 2 hot corrosion attack. (d More
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Published: 01 January 2002
Fig. 11 Degradation of rupture for Udimet 500 due to hot corrosion at 705 °C (1300 °F) More
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Published: 01 January 2003
Fig. 21 Effects of fuel carbon residue (10% bottoms) on type II hot corrosion of nickel aluminide high-temperature coatings. Source: Ref 135 More
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Published: 15 January 2021
Fig. 23 Effect of molten salt on hot corrosion at 700 °C (1290 °F) in air. With the lower melting temperatures of salt mixtures, the corrosion rate increases with increasing volume fraction of liquid. Courtesy of Z. Tang and B. Gleeson, University of Pittsburgh More
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Published: 30 August 2021
Fig. 21 (a) Type I hot corrosion at a blade tip IN-738 alloy. Note the subsurface sulfides (arrows). (b) Type II hot corrosion attack of a blade shank (below the platform) CMSX-4 (single-crystal) alloy. The sample was etched with Marble’s reagent to show the lack of alloy depletion under More
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Published: 01 January 2006
Fig. 28 Severe attack of an aeroderivative gas turbine blade by hot corrosion. See the article “Corrosion of Industrial Gas Turbines” in this Volume. More
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Published: 01 January 2005
Fig. 66 Hot corrosion of alloys MA 953, HDA 8077, and MA 956 compared to that of some non-ODS alloys. Test conditions: 900 °C (1650 °F), 1 h, followed by a 3 min air blast, 5 ppm sea salt. Source: Ref 46 More
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Published: 01 January 2006
Fig. 8 Examples of engine component surface damage. (a) Evidence of hot corrosion damage on the pressure side of a MAR-M-246 turbine blade. (b) Metallographic section across the airfoil of the MAR-M-246 blade, showing evidence of hot corrosion damage penetrating the leading edge (B) right More
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Published: 01 January 2006
Fig. 5 Severe attack of an aeroderivative gas turbine blade by hot corrosion More
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Published: 01 January 2006
Fig. 6 Type I high-temperature hot corrosion. D is the external deposit, which also contains oxidation products. O is the internally oxidized metal. S is the layer of sulfides. B is the base metal. As-polished More
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Published: 01 January 2006
Fig. 7 Type II low-temperature hot corrosion, showing the layered appearance of the scale. As-polished More
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Published: 01 January 2006
Fig. 8 Degradation in rupture life for various superalloys due to hot corrosion at 705 °C (1300 °F) More
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Published: 01 January 1994
Fig. 8 Corrosion losses of hot dip coatings in the industrial environment of Bethlehem, PA. Source: Ref 18 More
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Published: 01 December 1998
Fig. 2 Corrosion losses of hot-dip coatings in the industrial environment of Bethlehem, PA More
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Published: 01 January 2006
Fig. 16 Corrosion of hot water line after insulation was degraded by water intrusion. See the article “Corrosion Control for Military Facilities” in this Volume. More
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Published: 01 January 1997
Fig. 2 Corrosion losses of hot dip coatings in the industrial environment of Bethlehem, PA. Source: Ref 13 More