Sodium Sulphate and V2O5-induced Hot Corrosion Kinetics and Oxides Characteristics of the Weldments in SA213 T11 Steels

2021 ◽  
pp. 130359
Author(s):  
Ravindra Kumar
Keyword(s):  
Hot Corrosion ◽  
Sodium Sulphate ◽  
Corrosion Kinetics

SMA, GTA and P-GMA dissimilar weld joints of 304LN stainless steel to HSLA steel; Part-2: hot corrosion kinetics

2018 ◽  
Vol 5 (9) ◽  
pp. 096503 ◽  
Author(s):  
Ramkishor Anant ◽  
Jag Parvesh Dahiya ◽  
B P Agrawal ◽  
P K Ghosh ◽  
Ravindra Kumar ◽  
...  
Keyword(s):  
Stainless Steel ◽  
Hot Corrosion ◽  
Hsla Steel ◽  
Steel Part ◽  
Dissimilar Weld ◽  
Weld Joints ◽  
Corrosion Kinetics ◽  
304Ln Stainless Steel

The mechanism of sodium sulphate-induced low temperature hot corrosion of pure iron

1990 ◽  
Vol 30 (4-5) ◽  
pp. 327-349 ◽  
Author(s):  
V. Buscaglia ◽  
P. Nanni ◽  
C. Bottino
Keyword(s):  
Low Temperature ◽  
Hot Corrosion ◽  
Pure Iron ◽  
Sodium Sulphate

Hot corrosion behavior of Pt-Ir modified aluminide coatings on the nickel-base single crystal superalloy TMS-82+

2007 ◽  
Vol 22 (1) ◽  
pp. 206-216 ◽  
Author(s):  
Y.N. Wu ◽  
A. Yamaguchi ◽  
H. Murakami ◽  
S. Kuroda
Keyword(s):  
Single Crystal ◽  
Corrosion Behavior ◽  
Hot Corrosion ◽  
Aluminide Coating ◽  
Mass Gain ◽  
Heating Time ◽  
Single Crystal Superalloy ◽  
Aluminide Coatings ◽  
Corrosion Kinetics ◽  
Nickel Base

Platinum-iridium films (Ir = 0, 32, 46, 83, 100 at.%) were deposited on the nickel-base single crystal superalloy through magnetron sputtering. After annealing and aluminizing, the Pt-Ir modified aluminide coatings mainly consisted of PtAl2 and β-(Ni,Pt,Ir)Al phases. Hot corrosion resistance of Pt-Ir modified aluminide coatings with the different Ir contents were evaluated by exposure at 1173 K in the presence of the 90%Na2SO4 + 10%NaCl (wt%) salt deposits. The corrosion kinetics curves of the specimens were plotted up to 100 h heating time. The phase constitution, morphology of corrosion products, and element concentrations along the cross section were also measured. The lowest mass gain (0.299 mg/cm2, after 100 h) was observed for Pt-46Ir aluminide coating because the dense and continuous protective Al2O3 scale formed. Phase transformation from β-(Ni,Pt)Al to γ′-(Ni,Pt)3Al, characteristics of the scale, and protection by Pt/Ir enriched layer had the important effects on the hot corrosion behavior of modified aluminide coatings.

Type II Hot Corrosion: Kinetics Studies of CMSX-4

2013 ◽  
Vol 80 (5-6) ◽  
pp. 553-563 ◽  
Author(s):  
Joy Sumner ◽  
Adriana Encinas-Oropesa ◽  
Nigel J. Simms ◽  
John R. Nicholls
Keyword(s):  
Hot Corrosion ◽  
Type Ii ◽  
Kinetics Studies ◽  
Corrosion Kinetics ◽  
Type Ii Hot Corrosion

Hot corrosion of NiCr alloys in SO2+O2 atmospheres—I. Corrosion kinetics

1976 ◽  
Vol 16 (5) ◽  
pp. 261-277 ◽  
Author(s):  
V. Vasantasree ◽  
M.G. Hocking
Keyword(s):  
Hot Corrosion ◽  
Corrosion Kinetics

Comparison of Sodium Sulphate Deposition Rate Models Based on Operational Factors Influencing Hot Corrosion Damage in Aero-Engines

2020 ◽  
Author(s):  
Evangelia Pontika ◽  
Panagiotis Laskaridis ◽  
Theoklis Nikolaidis ◽  
Max Koster
Keyword(s):  
Gas Turbine ◽  
Analysis Of Variance ◽  
Deposition Rate ◽  
Hot Corrosion ◽  
Molten Salts ◽  
Experimental Studies ◽  
Corrosion Damage ◽  
Sodium Sulphate ◽  
Operating Conditions ◽  
Aircraft Engines

Abstract Hot corrosion is defined as the accelerated oxidation/sulphidation in the presence of alkali metal molten salts. It is a form of chemical attack that causes good metal loss. Current lifing models in aircraft engines focus on creep, fatigue and oxidation while hot corrosion damage has been overlooked as being of secondary importance. However, the absence of hot corrosion lifing models for aircraft engines often leads to unexpected and unexplained hot corrosion findings by aircraft engine operators and Maintenance, Repair and Overhaul (MRO) providers during inspections. Although hot corrosion does not cause failure on its own, the interaction with other damage mechanisms can reduce component life significantly, consequently, there is a requirement for including hot corrosion in the damage prediction process of aircraft engines. In both theoretical and experimental studies in literature, deposition of molten salts is identified as one of the primary conditions for hot corrosion to occur and an increased amount of deposited liquid salts accelerates the attack. Currently, most hot corrosion studies are limited to experimental testing of superalloys which are pre-coated with a controlled layer of salts. Such experimental studies are disconnected from gas turbine operating conditions during service. The present paper analyses two deposition rate models applicable to gas turbine operating conditions using Design of Experiments. Design space exploration is presented by taking into account gas turbine operating parameters which vary during a flight as well as temperature ranges where hot corrosion can occur. Analysis of variance is presented for 6 input parameters using Box-Behnken 3-level factorial design. Results from the Analysis of Variance indicate that the deposition rate models are sensitive to pressure and salt concentration in the gas flow. Finally, the saturation point of sodium sulphate has been investigated within the operating range of gas turbine and it was found that it can vary significantly under different conditions.

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