NDLI: A Study of Deposition on a Turbine Vane With a Thermal Barrier Coating and Various Film Cooling Geometries

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Davidson, F. Todd David, A. Kistenmacher David, G. Bogard
Copyright Year	2012
Abstract	Recent interest has been shown in using synthetic gaseous (syngas) fuels to power gas turbine engines. An important issue concerning these fuels is the potential for increased contaminate deposition that can inhibit cooling designs and expedite the material degradation of vital turbine components. The purpose of this study was to provide a detailed understanding of how contaminates deposit on the surface of a turbine vane with a thermal barrier coating (TBC). The vane model used in this study was designed to match the thermal behavior of real engine components by properly scaling the convective heat transfer coefficients as well as the thermal conductivity of the vane wall. Four different film cooling configurations were studied: round holes, craters, a trench and a modified trench. The contaminates used in this study were small particles of paraffin wax that were sprayed into the mainstream flow of the wind tunnel. The wax particles modeled both the molten nature of contaminates in an engine as well as the particle trajectory by properly matching the expected range of Stokes number. This study found that the presence of film cooling significantly increased the accumulation of deposits. It was also found that the deposition behavior was strongly affected by the film cooling configuration that was used on the pressure side of the vane. The craters and trench performed the best in mitigating the accumulation of deposits immediately downstream of the film cooling configuration. In general, the presence of deposits reduced the film cooling performance on the surface of the TBC. However, the additional thermal insulation provided by the deposits improved the cooling performance at the interface of the TBC and vane wall.
Sponsorship	International Gas Turbine Institute
Starting Page	1769
Ending Page	1780
Page Count	12
File Format	PDF
ISBN	9780791844700
DOI	10.1115/GT2012-70033
Volume Number	Volume 4: Heat Transfer, Parts A and B
Conference Proceedings	ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
Language	English
Publisher Date	2012-06-11
Publisher Place	Copenhagen, Denmark
Access Restriction	Subscribed
Subject Keyword	Cooling Wind tunnels Thermal insulation Fuels Flow (dynamics) Pressure Engines Convection Syngas Materials degradation Gas turbines Particulate matter Thermal barrier coatings Trajectories (physics) Thermal conductivity Film cooling Turbines Turbine components Paraffin wax
Content Type	Text
Resource Type	Article

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