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hot corrosion

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Series: ASM Technical Books
Publisher: ASM International
Published: 01 November 2007
DOI: 10.31399/asm.tb.htcma.t52080249
EISBN: 978-1-62708-304-1
... Abstract This chapter examines the hot corrosion resistance of various nickel- and cobalt-base alloys in gas turbines susceptible to high-temperature (Type I) and low-temperature (Type II) hot corrosion. Type I hot corrosion is typically characterized by a thick, porous layer of oxides...
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Published: 30 November 2013
Fig. 9 Hot-corrosion attack of René 77 nickel-base alloy turbine blades. (a) A land-based, first-stage turbine blade. Notice the deposit buildup and flaking and splitting of the leading edge. (b) Stationary vanes. (c) A land-based, first-stage gas turbine blade that had type 2 hot-corrosion More
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Published: 01 November 2007
Fig. 9.1 Relative hot corrosion resistance of cobalt-base alloys obtained from burner rig tests using 3% S residual oil and 325 ppm NaCl in fuel (equivalent to 5 ppm NaCl in air) at 870 °C (1600 °F) for 600 h. Source: Beltran ( Ref 21 ) More
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Published: 01 November 2007
Fig. 9.2 Relative hot corrosion resistance of nickel- and cobalt-base alloys obtained from burner rig tests at 870, 950, and 1040 °C (1600, 1750, and 1900 °F) for 100 h, using 1% S diesel fuel, 30:1 air-to-fuel ratio, and 200 ppm sea-salt injection. Source: Bergman et al. ( Ref 22 ) More
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Published: 01 November 2007
Fig. 9.3 Relative hot corrosion resistance of experimental alloys obtained from burner rig tests at 950 and 1040 °C (1750 and 1900 °F) for 100 h, using 1% S diesel fuel, 30:1 air-to-fuel ratio, and 200 ppm sea-salt injection. Source: Bergman et al. ( Ref 22 ) More
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Published: 01 November 2007
Fig. 9.4 Relative hot corrosion resistance of experimental alloys obtained from burner rig tests at 910, 950, and 1040 °C (1675, 1750, and 1900 °F) for 100 h, using 1% S diesel fuel, 30:1 air-to-fuel ratio, and 200 ppm sea salt injection. Source: Bergman et al. ( Ref 22 ) More
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Published: 01 December 2018
Fig. 6.117 Optical micrographs of outer surface showing hot corrosion in the form of grain boundary attack. Microstructure is essentially ferrite-pearlite with some surface decarburization, (a) and (b), 400× More
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Published: 01 March 2002
Fig. 13.4 Specimen weight change during 899 °C (1650 °F) isothermal hot corrosion test More
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Published: 01 March 2002
Fig. 13.11 Type 1 hot corrosion attack on a Ni-20Cr-2ThO 2 oxide-dispersion-strengthened superalloy. Specimen was coated with Na 2 SO 4 and oxidized in air at 1000 °C (1832 °F). (a) Nickel-rich scale, (b) CrO 3 subscale, and (c) chromium sulfides More
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Published: 01 March 2002
Fig. 13.14 Effect of a nickel-aluminide-type coating on the hot corrosion resistance of an IN-713 nickel-base superalloy turbine blade compared with an uncoated blade. (a) Uncoated blade after 118 test cycles, (b) micrograph showing severe degradation of IN-713 by hot corrosion, (c) aluminide More
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Published: 01 December 1989
Fig. 8.7. Relationship between hot-corrosion weight loss and temperature for ferritic steels ( Ref 41 ). More
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Published: 01 December 1989
Fig. 8.8. Relationship between hot-corrosion weight loss and chromium content for various alloys ( Ref 42 ). More
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Published: 01 December 1989
Fig. 9.20. Three different forms of hot corrosion observed in Udimet 710 ( Ref 33 ). (a) Layer type. (b) Transition type. (c) Nonlayer type. More
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Published: 01 December 1989
Fig. 9.24. Effect of prior exposure to hot corrosion (without chlorides) on the fatigue life of IN 738 ( Ref 45 and 46 ). More
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Published: 01 December 1989
Fig. 9.26. Effect of hot corrosion on high-cycle-fatigue life of IN 738 LC at 850 °C (1560 °F) ( Ref 48 and 49 ). More
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Published: 01 December 1989
Fig. 9.27. Effect of hot corrosion on high-cycle-fatigue life of IN 939 ( Ref 48 and 49 ). More
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Published: 01 December 1989
Fig. 9.28. Effect of hot corrosion and coating on the high-cycle-fatigue behavior of Udimet 720 at 705 °C (1300 °F) ( Ref 50 and 51 ). More
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Published: 01 December 2015
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 2000
Fig. 10 Corrosion losses of hot-dip coatings in the industrial environment of Bethlehem, PA More
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Published: 01 December 2000
Fig. 13.4 Parametric (Larson-Miller type) relationships for hot salt stress-corrosion cracking of selected titanium alloys More