Thermal Analysis & Studies on Low Pressure Gas Turbine Blades Coated with Yitria Stabilized Zirconia (YSZ)

N. Rajasekar; P.M. Shivraj; C.J. Thomas Renald; K. Karthick; M.P. Tamizhmani

doi:10.4028/www.scientific.net/AMR.622-623.1596

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 622-623Thermal Analysis & Studies on Low Pressure Gas...

Thermal Analysis & Studies on Low Pressure Gas Turbine Blades Coated with Yitria Stabilized Zirconia (YSZ)

Abstract:

The thermal barrier coatings have many potential applications in the protection of gas turbine engine components, essentially the turbine blades.In this study micro analysis was carried out on Yitria Stabilized Zirconia(YSZ) coated turbine blades and the results are compared with the uncoated blades.We have used the atmosphere plasma sprayed thermal barrier coating with a thickness of 0.25mm to withstand the high temperature of about 2000 C.We observed that by increasing the thermal coating thickness of about 0.25mm cause to increase 50% of the surface temperature of the turbine blade,which in turn increased the aero engine thrust.

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Periodical:

Advanced Materials Research (Volumes 622-623)

Pages:

1596-1600

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.622-623.1596

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Online since:

December 2012

Authors:

N. Rajasekar, P.M. Shivraj, C.J. Thomas Renald, K. Karthick, M.P. Tamizhmani

Keywords:

Low Pressure Turbine Blades, Metco 204 – NS (YSZ Powder), Visual Optical Imaging Systems, Yitria Stabilized Zirconia

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References

[1] Tamarin Y., Protective coating for turbine blades, ASM International, Materials Park, OH 44073-0002, USA, ISBN: 0-87170-759-4, (2002).

Google Scholar

[2] Misbahul Amin.M., Oxidation Behaviour of IN-738 LC Super alloys in the presence of ionic salts at 1173 k, Department of Chemistry, Faculty of Science & Technology, University College of Science & Technology Malaysia, Malaysia. November (2003).

Google Scholar

[3] Asok Kumar N., Kale S.R., Numerical simulation of steady state heat transfer in a Ceramic-coated gas turbine blade, International Journal of Heat and Mass Transfer 45(2002) 4831-4845.

DOI: 10.1016/s0017-9310(02)00190-4

Google Scholar

[4] Antonio Licciulli, Thermal barrier coatings for aeronautic engines turbine blades', Science Technology of Ceramic Materials, (2002).

Google Scholar

[5] Botto D., Martena M., Saddadini s., Numerical model of a TBC system stress distribution as thermal expansion mismatch, XXXIII Convegno Nazionale dell'Associazione Italiana per l'Analisi delle Sollecitazioni, 31 August-2 September, (2004).

Google Scholar