Details
| Originalsprache | Englisch |
|---|---|
| Seiten (von - bis) | 196-199 |
| Seitenumfang | 4 |
| Fachzeitschrift | CIRP Journal of Manufacturing Science and Technology |
| Jahrgang | 19 |
| Frühes Online-Datum | 20 Mai 2017 |
| Publikationsstatus | Veröffentlicht - Nov. 2017 |
Abstract
High pressure single-crystal turbine blades made from nickel-based superalloys can withstand temperatures of up to 1100 °C due to their superior creep and fatigue properties compared to polycrystalline material. However, these parts undergo erosion and cracking due to the extreme conditions they are subject to in the engines of commercial airplanes. Since there is no effective method of repairing these expensive parts, while maintaining the necessary microstructure, the need to develop and establish a reproducible process is of high importance. The process of Laser Material Deposition (LMD) has shown promising results in the building-up of single-crystal or directionally solidified structures, while laser remelting has been shown to extend this monocrystalline height. By combining the two processes, this study aimed to deposit and remelt single-crystal structures on substrates of the nickel-based superalloys CMSX-4 and turbine blade tips of PWA 1426. Experiments were carried out to establish laser parameters that resulted in a monocrystalline microstructure. This study showed that the combination of cladding and remelting can be used to deposit single-crystal structures and was able to establish a reproducible laser process to this effect. The results obtained indicate that the process is a promising candidate for the repair of turbine blade tips and warrants further research into the microstructure and thermomechanical properties of the repaired areas.
ASJC Scopus Sachgebiete
- Ingenieurwesen (insg.)
- Wirtschaftsingenieurwesen und Fertigungstechnik
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in: CIRP Journal of Manufacturing Science and Technology, Jahrgang 19, 11.2017, S. 196-199.
Publikation: Beitrag in Fachzeitschrift › Artikel › Forschung › Peer-Review
}
TY - JOUR
T1 - Single-crystal turbine blade tip repair by laser cladding and remelting
AU - Kaierle, Stefan
AU - Overmeyer, Ludger
AU - Alfred, Irene
AU - Rottwinkel, Boris
AU - Hermsdorf, Jörg
AU - Wesling, Volker
AU - Weidlich, Nils
N1 - Funding information: This work was funded by the German Research Foundation (DFG) within the scope of the Collaborative Research Centre “Product Regeneration” (SFB871). The authors would like to express their gratitude for the support.
PY - 2017/11
Y1 - 2017/11
N2 - High pressure single-crystal turbine blades made from nickel-based superalloys can withstand temperatures of up to 1100 °C due to their superior creep and fatigue properties compared to polycrystalline material. However, these parts undergo erosion and cracking due to the extreme conditions they are subject to in the engines of commercial airplanes. Since there is no effective method of repairing these expensive parts, while maintaining the necessary microstructure, the need to develop and establish a reproducible process is of high importance. The process of Laser Material Deposition (LMD) has shown promising results in the building-up of single-crystal or directionally solidified structures, while laser remelting has been shown to extend this monocrystalline height. By combining the two processes, this study aimed to deposit and remelt single-crystal structures on substrates of the nickel-based superalloys CMSX-4 and turbine blade tips of PWA 1426. Experiments were carried out to establish laser parameters that resulted in a monocrystalline microstructure. This study showed that the combination of cladding and remelting can be used to deposit single-crystal structures and was able to establish a reproducible laser process to this effect. The results obtained indicate that the process is a promising candidate for the repair of turbine blade tips and warrants further research into the microstructure and thermomechanical properties of the repaired areas.
AB - High pressure single-crystal turbine blades made from nickel-based superalloys can withstand temperatures of up to 1100 °C due to their superior creep and fatigue properties compared to polycrystalline material. However, these parts undergo erosion and cracking due to the extreme conditions they are subject to in the engines of commercial airplanes. Since there is no effective method of repairing these expensive parts, while maintaining the necessary microstructure, the need to develop and establish a reproducible process is of high importance. The process of Laser Material Deposition (LMD) has shown promising results in the building-up of single-crystal or directionally solidified structures, while laser remelting has been shown to extend this monocrystalline height. By combining the two processes, this study aimed to deposit and remelt single-crystal structures on substrates of the nickel-based superalloys CMSX-4 and turbine blade tips of PWA 1426. Experiments were carried out to establish laser parameters that resulted in a monocrystalline microstructure. This study showed that the combination of cladding and remelting can be used to deposit single-crystal structures and was able to establish a reproducible laser process to this effect. The results obtained indicate that the process is a promising candidate for the repair of turbine blade tips and warrants further research into the microstructure and thermomechanical properties of the repaired areas.
KW - Laser cladding
KW - Laser metal deposition
KW - Laser remelting
KW - Single-crystal
KW - Superalloys
KW - Turbine blade repair
UR - http://www.scopus.com/inward/record.url?scp=85019935188&partnerID=8YFLogxK
U2 - 10.1016/j.cirpj.2017.04.001
DO - 10.1016/j.cirpj.2017.04.001
M3 - Article
AN - SCOPUS:85019935188
VL - 19
SP - 196
EP - 199
JO - CIRP Journal of Manufacturing Science and Technology
JF - CIRP Journal of Manufacturing Science and Technology
SN - 1755-5817
ER -