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Abstract No.: |
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Scheduled at:
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Wednesday, May 11, 2016, Yellow River Hall 12:20 PM Aviation Industry I
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Title: |
Practical surface solutions for thermal barrier turbine coating applications
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Authors: |
Malko Gindrat* / Oerlikon Metco AG, CH Mitch Dorfman / Oerlikon Metco (US) Inc., USA Christopher Dambra/ Oerlikon Metco (US) Inc., USA Scott Wilson/ Oerlikon Metco AG (Switzerland), Switzerland Riston Rocchio-Heller/ Oerlikon Metco (US) Inc., USA Omar Sabouni/ Oerlikon Metco (US) Inc., USA
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Abstract: |
Zirconium oxide based ceramic coatings have been used for over 40 years in various turbine applications as thermal barrier coatings (TBC). Over the years new material solutions, more robust equipment and processes have helped to improve the performance and extended the life of critical components in many demanding turbine applications. As an illustration of these new challenges, today some TBC coatings potentially can see gas temperatures greater than 1600 °C.
In order to know which coating system is best suited for turbine engine components either in industrial gas turbine (IGT) or aerospace applications, it is necessary to better understand the technical and commercial advantages associated with the different processes to produce these coatings, namely electron beam physical vapor deposition (EB-PVD), plasma spray physical vapor deposition (PS-PVD) and air plasma spray (APS).
This paper will give an overview of these processes, in particular the APS processes using some newly developed technologies with single or triple cathode cascaded arc plasma guns to apply porous, dense and dense/porous vertically cracked 7-8 wt% yttrium oxide stabilized zirconium oxide as well as other zirconia-based systems. The paper will also compare and review the different microstructure, erosion, thermal conductivity and thermal cyclic life of coatings obtained by such processes.
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