Skip Nav Destination
Close Modal
Search Results for
hot corrosion
Update search
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
NARROW
Format
Topics
Book Series
Date
Availability
1-20 of 689 Search Results for
hot corrosion
Follow your search
Access your saved searches in your account
Would you like to receive an alert when new items match your search?
1
Sort by
Book Chapter
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...
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 with the underlying alloy matrix depleted in chromium, followed (below) by internal chromium-rich sulfides. Type II hot corrosion is characterized by pitting with little or no internal attack underneath. As the chapter explains, chromium additions make alloys more resistant to all types of hot corrosion attacks.
Image
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
Image
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
Image
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
Image
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
Image
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
Image
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
Image
Published: 01 March 2002
Image
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
Image
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
Image
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
Image
in Materials for Advanced Steam Plants
> Damage Mechanisms and Life Assessment of High-Temperature Components
Published: 01 December 1989
Fig. 8.7. Relationship between hot-corrosion weight loss and temperature for ferritic steels ( Ref 41 ).
More
Image
in Materials for Advanced Steam Plants
> Damage Mechanisms and Life Assessment of High-Temperature Components
Published: 01 December 1989
Fig. 8.8. Relationship between hot-corrosion weight loss and chromium content for various alloys ( Ref 42 ).
More
Image
in Life-Assessment Techniques for Combustion Turbines
> Damage Mechanisms and Life Assessment of High-Temperature Components
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
Image
in Life-Assessment Techniques for Combustion Turbines
> Damage Mechanisms and Life Assessment of High-Temperature Components
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
Image
in Life-Assessment Techniques for Combustion Turbines
> Damage Mechanisms and Life Assessment of High-Temperature Components
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
Image
in Life-Assessment Techniques for Combustion Turbines
> Damage Mechanisms and Life Assessment of High-Temperature Components
Published: 01 December 1989
Image
in Life-Assessment Techniques for Combustion Turbines
> Damage Mechanisms and Life Assessment of High-Temperature Components
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
Image
in Surface Engineering to Add a Surface Layer or Coating
> Surface Engineering for Corrosion and Wear Resistance
Published: 01 March 2001
Fig. 4 Corrosion losses of hot dip coatings in the industrial environment of Bethlehem, PA. Source: Ref 18
More
Image
Published: 01 December 2000
Fig. 13.4 Parametric (Larson-Miller type) relationships for hot salt stress-corrosion cracking of selected titanium alloys
More
1
