0
Research Papers

Film Cooling With a Thermal Barrier Coating: Round Holes, Craters, and Trenches

[+] Author and Article Information
F. Todd Davidson

e-mail: davidsonft@gmail.com

David A. KistenMacher

e-mail: dkistenmacher@gmail.com

David G. Bogard

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

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received May 14, 2013; final manuscript received June 6, 2013; published online September 26, 2013. Editor: Ronald Bunker.

J. Turbomach 136(4), 041007 (Sep 26, 2013) (11 pages) Paper No: TURBO-13-1075; doi: 10.1115/1.4024883 History: Received May 14, 2013; Revised June 06, 2013

Little work has been done to understand the interconnected nature of film cooling and thermal barrier coatings (TBCs) on protecting high temperature turbine components. With increasing demands for improved engine performance it is vital that a greater understanding of the thermal behavior of turbine components is achieved. The purpose of this study was to investigate how various film cooling geometries affect the cooling performance of a thermally conducting turbine vane with a 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 along with the thermal conductivity of the vane wall. This allowed for the measurement of temperatures at the interface of the TBC and vane wall which, when nondimensionalized, are representative of the temperatures present for actual engine vanes. This study found that the addition of a TBC on the surface of an internally cooled vane produced a near constant cooling performance despite significant changes in the blowing ratio. The craters, trench, and modified trench of this study were found to provide much better film cooling coverage than round holes; however, the improved film cooling coverage led to only slight improvements in temperature at the interface of the TBC and vane wall. These results suggest that there is minimal advantage in using more complicated cooling configurations, particularly since they may be more susceptible to TBC spallation. However, the improved film coverage from the trench and crater designs may increase the life of the TBC, which would be greatly beneficial to the long-term thermal protection of the vane.

Copyright © 2014 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Fig. 1

Schematic of turbine vane test section

Grahic Jump Location
Fig. 2

Schematic of secondary flow loop

Grahic Jump Location
Fig. 3

Test airfoil schematic

Grahic Jump Location
Fig. 4

Vane cross-section and s/d locations

Grahic Jump Location
Fig. 5

Schematics of the various pressure side cooling hole designs

Grahic Jump Location
Fig. 6

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

Grahic Jump Location
Fig. 7

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

Grahic Jump Location
Fig. 8

Comparison of ϕ with and without the TBC for round holes with an active showerhead (M listed here is for only the pressure side holes)

Grahic Jump Location
Fig. 9

Comparison of laterally averaged τ for round holes with an active showerhead at varying blowing ratios

Grahic Jump Location
Fig. 10

Contour plots of τ for round holes with an active showerhead

Grahic Jump Location
Fig. 11

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

Grahic Jump Location
Fig. 12

Effect of the cooling design on ϕ for varying blowing ratios

Grahic Jump Location
Fig. 13

Effect of the cooling design on ϕ for varying blowing ratios

Grahic Jump Location
Fig. 14

Effect of the blowing ratio on τ for varying film cooling designs

Grahic Jump Location
Fig. 15

Effect of the blowing ratio on τ for varying film cooling designs

Grahic Jump Location
Fig. 16

Contour plots of τ for varying film cooling designs at M = 0.5 and M = 1.0

Grahic Jump Location
Fig. 17

Contour plots of τ for varying film cooling designs at M = 2.0 and M = 5.0

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In