0
TECHNICAL PAPERS

High-Resolution Film Cooling Effectiveness Comparison of Axial and Compound Angle Holes on the Suction Side of a Turbine Vane

[+] Author and Article Information
Scot K. Waye

Mechanical Engineering Department, University of Texas at Austin, Austin, TX 78712scotwaye@hotmail.com

David G. Bogard

Mechanical Engineering Department, University of Texas at Austin, Austin, TX 78712

J. Turbomach 129(2), 202-211 (Jul 14, 2006) (10 pages) doi:10.1115/1.2448016 History: Received July 12, 2006; Revised July 14, 2006

Film cooling adiabatic effectiveness for axial and compound angle holes on the suction side of a simulated turbine vane was investigated to determine the relative performance of these configurations. The effect of the surface curvature was also evaluated by comparing to previous curvature studies and flat plate film cooling results. Experiments were conducted for varying coolant density ratio, mainstream turbulence levels, and hole spacing. Results from these measurements showed that for mild curvature, 2rd160, flat plate results are sufficient to predict the cooling effectiveness. Furthermore, the compound angle injection improves adiabatic effectiveness for higher blowing ratios, similar to previous studies using flat plate facilities.

Copyright © 2007 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Schematic of the simulated turbine vane test section

Grahic Jump Location
Figure 2

Schematic of test vane details

Grahic Jump Location
Figure 3

Laterally averaged adiabatic effectiveness for axial holes for various M, p∕d=2.78, Tu∞=3.9%, DR=1.3

Grahic Jump Location
Figure 4

Spatially averaged adiabatic effectiveness versus momentum flux ratio for axial holes, p∕d=2.78, DR=1.3

Grahic Jump Location
Figure 5

Spatial plots of adiabatic effectiveness for axial holes at various M, p∕d=2.78, Tu∞=3.9%, DR=1.3

Grahic Jump Location
Figure 6

Comparison of DR for axial holes, p∕d=2.78

Grahic Jump Location
Figure 7

Laterally averaged adiabatic effectiveness for axial holes for various M, p∕d=5.55, Tu∞=3.9%, DR=1.3

Grahic Jump Location
Figure 8

Spatial plots of adiabatic effectiveness for axial holes at various M, p∕d=5.55, Tu∞=3.9%, DR=1.3

Grahic Jump Location
Figure 9

Comparison of mainstream turbulence for axial holes, p∕d=5.55, DR=1.3

Grahic Jump Location
Figure 10

Comparison of laterally averaged adiabatic effectiveness for two hole spacings, Tu∞=3.9%, DR=1.3

Grahic Jump Location
Figure 11

Additive effect of hole spacing for axial holes (adiabatic effectiveness of larger pitch multiplied by two added for easier comparison), DR=1.3

Grahic Jump Location
Figure 12

Effect of curvature on laterally averaged adiabatic effectiveness for M=0.5

Grahic Jump Location
Figure 13

Comparison of current study to flat plate data (1,22), p∕d∼3

Grahic Jump Location
Figure 14

Laterally averaged adiabatic effectiveness for compound angle holes for various M, p∕d=5.55, Tu∞=3.9%, DR=1.3

Grahic Jump Location
Figure 15

Spatial adiabatic effectiveness for compound angle holes, Tu∞=3.9%, DR=1.3

Grahic Jump Location
Figure 16

Mainstream turbulence comparison for compound angle holes, DR=1.3

Grahic Jump Location
Figure 17

Comparison of axial and compound angle holes, p∕d=5.55, Tu∞=1.0%, DR=1.3

Grahic Jump Location
Figure 18

Spatially averaged adiabatic effectiveness for axial and compound angle holes, p∕d=5.55

Grahic Jump Location
Figure 19

Axial and compound angle hole results compared to similar flat plate results in the literature (2) at low Tu∞

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