Correction to: Correlation between platinum–aluminide coating features and tensile behavior of nickel-based superalloy Rene®80

In this paper, mechanical properties of the as-received and aluminide layer coated MAR 247 nickel based superalloy were examined through creep and fatigue tests. The aluminide layer of 20 µm was obtained through the chemical vapor deposition (CVD) process in the hydrogen protective atmosphere for 8 h at the temperature of 1040 °C and internal pressure of 150 mbar. A microstructure of the layer was characterized using the scanning electron microscopy (SEM) and X-ray Energy Dispersive Spectroscopy (EDS). It was found that aluminide coating improve the high temperature fatigue performance of MAR247 nickel based superalloy at 900 °C significantly. The coated MAR 247 nickel based superalloy was characterized by the stress amplitude response ranging from 350 MPa to 520 MPa, which is twice as large as that for the uncoated alloy.

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Creep rupture properties of bare and coated polycrystalline nickel-based superalloy Rene®80

Journal of Mining and Metallurgy Section B Metallurgy ◽

10.2298/jmmb201203036b ◽

2021 ◽

pp. 36-36

Author(s):

M.M. Barjesteh ◽

S.M. Abbasi ◽

K.Z. Madar ◽

K. Shirvani

Keyword(s):

Elevated Temperatures ◽

Life Time ◽

Creep Rupture ◽

Polycrystalline Nickel ◽

Creep Life ◽

Nickel Based Superalloy ◽

Platinum Aluminide ◽

Rupture Properties ◽

Low Activity ◽

Rupture Behavior

Creep deformation is one of the life time limiting reasons for gas turbine parts that are subjected to stresses at elevated temperatures. In this study, creep rupture behavior of uncoated and platinum-aluminide coated Rene?80 has been determined at 760?C/657 MPa, 871?C/343 MPa and 982?C/190 Mpa in air. For this purpose, an initial layer of platinum with a thickness of 6?m was applied on the creep specimens. Subsequently, the aluminizing were formed in the conventional pack cementation method via the Low Temperature-High Activity (LTHA) and High Temperature-Low Activity (HTLA) processes. Results of creep-rupture tests showed a decrease in resistance to creep rupture of coated specimen, compared to the uncoated ones. The reductions in rupture lives in LTHA and HTLA methods at 760?C/657 MPa, 871?C/343 MPa and 982?C/190 MPa were almost (26% and 41.8%), (27.6% and 38.5%) and (22.4% and 40.3%), respectively as compared to the uncoated ones. However, the HTLA aluminizing method showed an intense reduction in creep life. Results of fractographic studies on coated and uncoated specimens indicated a combination of ductile and brittle failure mechanisms for all samples. Although, the base failure mode in substrate was grain boundary voids, cracks initiated from coating at 760?C/657MPa and 871?C/343. No cracking in the coating was observed at 982?C/190MPa.

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Influence of heat treatment on microstructure and tensile behavior of a hot isostatically pressed nickel-based superalloy

Journal of Alloys and Compounds ◽

10.1016/j.jallcom.2013.06.045 ◽

2013 ◽

Vol 578 ◽

pp. 454-464 ◽

Cited By ~ 47

Author(s):

Chunlei Qiu ◽

Xinhua Wu ◽

Junfa Mei ◽

Paul Andrews ◽

Wayne Voice

Keyword(s):

Heat Treatment ◽

Tensile Behavior ◽

Nickel Based Superalloy

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Influence of an Aluminide Coating on the TMF Life of a Single Crystal Nickel-Base Superalloy

Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education ◽

10.1115/98-gt-318 ◽

1998 ◽

Author(s):

Ernst E. Affeldt

Keyword(s):

Single Crystal ◽

Aluminide Coating ◽

Turbine Blades ◽

Temperature Cycling ◽

Nickel Base Superalloy ◽

Test Results ◽

Bending Tests ◽

Quantitative Correlation ◽

Nickel Based Superalloy ◽

Nickel Base

TMF tests were conducted with bare and aluminide coated single crystal nickel-based superalloy specimens. Temperature cycling was between 400°C and 1100°C with a phase shift (135°) which is typical for damaged locations on turbine blades. Stress response is characterized by a constant range and the formation of a tensile mean stress as a result of relaxation in the high temperature part of the cycle which is in compression. Bare specimens showed crack initiation from typical oxide hillocks. Coated specimens showed life reduction with respect to the bare ones caused by brittle cracking of the coating in the low temperature part of the cycle. Isothermal bending tests of coated specimens confirmed the low ductility of the coating at tempeatures below 600°C but quantitative correlation with the TMF test results failed.

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