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Research Papers

Realistic Trench Film Cooling With a Thermal Barrier Coating and Deposition

[+] Author and Article Information
David A. Kistenmacher

Chevron U.S.A., Inc.,
Houston, TX 77210
e-mail: DKistenmacher@Gmail.com

F. Todd Davidson

Graphene Materials, LLC,
Austin, TX 78712
e-mail: DavidsonFT@Gmail.com

David G. Bogard

The University of Texas at Austin,
Austin, TX 78712
e-mail: DBogard@mail.utexas.edu

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 22, 2013; final manuscript received January 5, 2014; published online February 27, 2014. Editor: Ronald Bunker.

J. Turbomach 136(9), 091002 (Feb 27, 2014) (12 pages) Paper No: TURBO-13-1166; doi: 10.1115/1.4026613 History: Received July 22, 2013; Revised January 05, 2014

Thermal barrier coatings (TBC) see extensive use in high-temperature gas turbines. However, little work has been done to experimentally characterize the combination of TBC and film cooling. The purpose of this study is to investigate the cooling performance of a thermally conducting turbine vane with a realistic film-cooling trench geometry embedded in TBC. Additionally, the effect of contaminant deposition on the realistic trench was studied. The trench is termed realistic because it takes into account probable manufacturing limitations. The vane model and TBC used for this study were designed to match the thermal behavior of an actual gas turbine vane with TBC by properly scaling their convective heat-transfer coefficients, thermal conductivities, and characteristic length scales. This study built upon previously published results with various film-cooling geometries consisting of round holes, craters, an ideal trench, and a novel trench. The previous study showed that large changes in blowing ratio resulted in negligible effects on cooling performance. Changes to film-cooling geometry also resulted in minor effects on cooling performance. This study found that the realistic trench and an idealized trench perform similarly. However, the width of the realistic trench left the vane wall more exposed to mainstream temperatures, especially at lower film-coolant flow rates. This study also found that the trench designs helped to mitigate deposition formation better than round holes; however, the realistic trench was more prone to deposition within the trench. The overall cooling effectiveness was similar for both trench designs and relatively unchanged from the predeposition performance, while the overall cooling effectiveness for round holes increased due to the additional thermal insulation offered by the unmitigated deposition.

Copyright © 2014 by ASME
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References

Figures

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Fig. 1

Schematic of turbine vane test section

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Fig. 2

Schematic of secondary flow loop

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Fig. 3

Test airfoil schematic

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Fig. 4

Vane cross section and s/d locations

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Fig. 5

Schematics of the various pressure-side cooling-hole designs

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Fig. 6

Wax spray system schematic [15]

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Fig. 7

Wax particle sizing micrograph [15]

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Fig. 8

Photographs of interface thermocouples prior to applying simulated TBC to the vane surface

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Fig. 9

Vane wall cross section with TBC and relative location of measurements of interest

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Fig. 10

Effect of blowing ratio on ϕ for varying film-cooling designs

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Fig. 11

Effect of cooling design on ϕ for varying blowing ratio

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Fig. 12

Contour plots of τ for varying film-cooling designs and blowing ratios

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Fig. 13

Photographs before and after deposition for an ideal trench at M = 2.0

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Fig. 14

Contour plots of τ for an ideal trench at M = 2.0 before and after deposition

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Fig. 15

Photographs before and after deposition for a realistic trench at M = 2.0

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Fig. 16

Contour plots of τ for a realistic trench at M = 2.0 before and after deposition

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Fig. 17

Effect of deposition on τ for varying film-cooling designs at M = 2.0

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Fig. 18

Effect of deposition on ϕ for varying film-cooling designs at M = 2.0

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