Experimental Investigation on Heat Transfer Characteristics of Thermal Barrier Coating on Aero Engine Components

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Year : January 26, 2024 | Volume : 11 | [if 424 equals=”Regular Issue”]Issue[/if 424][if 424 equals=”Special Issue”]Special Issue[/if 424] [if 424 equals=”Conference”][/if 424] : 13 | Page : 50-58

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    Srikanth H.V., Fareen Nizami

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  1. Associate Professor, Assistant Professor, Research Scholar,, Department of Aeronautical Engineering, Nitte Meenakshi Institute of Technology, Department of Aeronautical Engineering, Nitte Meenakshi Institute of Technology, epartment of Mechanical Engineering, NITK, Karnataka, Karnataka, Tamil Nadu, India, India, India
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Abstract

nThe gas turbine blades play a crucial role in harnessing energy from the high-temperature and highpressure
gas generated by the combustor. To withstand this challenging environment, turbine blades
often employ super-alloys and incorporate new manufacturing technologies such as Direct
Solidification (DS) and Single Crystal (SC). Additionally, the development of advanced ceramic
Thermal Barrier Coating (TBC) is imperative to achieve higher operating temperatures (>1200°C).
Therefore, the primary focus of this study is on advancing TBC with reduced thermal conductivity and
increased operating temperature, without imposing a significant weight penalty on components. Two
sample specimens, measuring 75 mm × 75 mm × 10 mm, were manufactured from SS 316L and 8%
Yttrium Stabilized Zirconia (YSZ-ZrO2.Y2O3), as well as 8% Yttria Stabilized Alumina (YSAAl2O3.
Y2O3). These specimens were coated with a bond coat of Nickel Chromite (NiCr) using the
Atmospheric Plasma Spray Method (APS). The temperature variations across a 250 μm layer of 8%
YSZ and 8% YSA were analyzed through both simulation and thermo-mechanical tests. This analysis
aims to elucidate the efficacy of TBC materials in enhancing the operational limits of components
subjected to elevated temperatures, particularly in aerospace and automobile applications.

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Keywords: Thermal Barrier Coating, Yttrium Stabilized Zirconia, Yttrium Stabilized Alumina. plasma spray method, heat transfer, turbine blades

n[if 424 equals=”Regular Issue”][This article belongs to Journal of Polymer and Composites(jopc)]

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[/if 424][if 424 equals=”Special Issue”][This article belongs to Special Issue under section in Journal of Polymer and Composites(jopc)][/if 424][if 424 equals=”Conference”]This article belongs to Conference [/if 424]

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How to cite this article: Srikanth H.V., Fareen Nizami Experimental Investigation on Heat Transfer Characteristics of Thermal Barrier Coating on Aero Engine Components jopc January 26, 2024; 11:50-58

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How to cite this URL: Srikanth H.V., Fareen Nizami Experimental Investigation on Heat Transfer Characteristics of Thermal Barrier Coating on Aero Engine Components jopc January 26, 2024 {cited January 26, 2024};11:50-58. Available from: https://journals.stmjournals.com/jopc/article=January 26, 2024/view=0

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References

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Special Issue Open Access Original Research

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Journal of Polymer and Composites

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[if 344 not_equal=””]ISSN: 2321–2810[/if 344]

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Volume 11
[if 424 equals=”Regular Issue”]Issue[/if 424][if 424 equals=”Special Issue”]Special Issue[/if 424] [if 424 equals=”Conference”][/if 424] 13
Received December 11, 2023
Accepted January 18, 2024
Published January 26, 2024

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