Special Issue "Microstructural Degradation of Superalloys during Service: Mechanical and/or Corrosion"

A special issue of Crystals (ISSN 2073-4352). This special issue belongs to the section "Alloys and Compounds".

Deadline for manuscript submissions: 15 December 2021.

Special Issue Editors

Prof. Dr. Yanhui Chen
E-Mail Website
Guest Editor
Beijing Key Lab of Microstructure and Property of Advanced Materials, Beijing University of Technology, Beijing 100124, China
Interests: in situ; TEM; superalloy; microstructure; turbine blade
Prof. Dr. Yunsong Zhao
E-Mail Website
Guest Editor
Science and Technology on Advanced High Temperature Structural Materials Laboratory, Beijing Institute of Aeronautical Materials, Beijing 100095, China
Interests: superalloy; creep; microstructure; grain boundary; single crystals

Special Issue Information

Dear Colleagues,

Superalloys used as blade material for gas turbines are strengthened by small intermetallic γ'-precipitates of the Ni3Al type. γ'-precipitation provides excellent mechanical properties at high temperatures, but its efficiency strongly depends on the size and morphology of the γ'-precipitates. During high temperature service in aircraft and power gas turbines, the γ/γ'-microstructure of nickel-base superalloys gradually degrades, i.e., coarsens and becomes rafted. This degradation of the microstructure deteriorates the mechanical properties. The relationship between microstructure and its properties are thus important to evaluate the service of the blade.

In this thematic issue, we invite contributions on the microstructure degradation of superalloys and the microstructural characterization and relationships between microstructure and its properties. The submitted works are expected to feature but are not limited to the following topics:

  • Microstructural characterization of superalloys;
  • Relationship between microstructural variation and its properties;
  • Microstructural variation during corrosion of superalloys;
  • Stress corrosion induced microstructural degradation in superalloys;
  • Evaluation of serviced turbine blade;
  • Newly developed superalloys: high entropy alloys, etc.

Prof. Dr. Yanhui Chen
Prof. Dr. Yunsong Zhao
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All papers will be peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Crystals is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 1800 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.


  • microstructure
  • superalloys
  • degradation
  • creep
  • oxidation

Published Papers (1 paper)

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Effect of Overheating Temperature on Thermal Cycling Creep Properties of K465 Superalloy
Crystals 2021, 11(12), 1458; https://doi.org/10.3390/cryst11121458 - 25 Nov 2021
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Turbine blades in aircraft engines may encounter overheating and suffer serious creep property degradation. In this study, the thermal cycling creep experiments were conducted on K465 superalloy under (900 °C/30 min–1100 °C/3 min)/50 MPa, (900 °C/30 min–1150 °C/3 min)/50 MPa and (1000 °C/30 [...] Read more.
Turbine blades in aircraft engines may encounter overheating and suffer serious creep property degradation. In this study, the thermal cycling creep experiments were conducted on K465 superalloy under (900 °C/30 min–1100 °C/3 min)/50 MPa, (900 °C/30 min–1150 °C/3 min)/50 MPa and (1000 °C/30 min–1150 °C/3 min)/50 MPa. The investigated thermal cycling creep properties were dramatically degraded, and increasing the overheating temperatures significantly decreased the thermal cycling creep life. The secondary γ′ precipitates obviously dissolved and the area fraction decreased to around 35.2% under (900 °C/30 min–1150 °C/3 min)/50 MPa and (1000 °C/30 min–1150 °C/3 min)/50 MPa, which was almost half that after the standard solution treatment. The decline of the thermal cycling creep properties was mainly due to the significant dissolution of γ′ precipitates. The creep holes/cracks were mainly distributed at the M6C carbides and γ/γ′ eutectics interfaces, M6C carbides and γ′ film interfaces in the grain boundaries, and resulted in the final intergranular fracture. Full article
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Planned Papers

The below list represents only planned manuscripts. Some of these manuscripts have not been received by the Editorial Office yet. Papers submitted to MDPI journals are subject to peer-review.

Haibo Long, Beijing University of Technology

Yunsong zhao, Beijing Institute of Aeronautical Materials

Chenguang Liu, Beijing Institute of Aeronautical Materials

Yanhui Chen, Beijing University of Technology

Qingqing Ding, Zhejiang University

Song Lu, University of Science and Technology Beijing

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