0
Research Papers

Effect of Upstream Wake With Vortex on Turbine Blade Platform Film Cooling With Simulated Stator-Rotor Purge Flow

[+] Author and Article Information
Lesley M. Wright

Department of Aerospace and Mechanical Engineering, The University of Arizona, Tucson, AZ 85721-0119

Sarah A. Blake

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123

Dong-Ho Rhee

 Korea Aerospace Research Institute, Daejeon, 305-333 Korea

Je-Chin Han

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123jc-han@tamu.edu

J. Turbomach 131(2), 021017 (Feb 03, 2009) (10 pages) doi:10.1115/1.2952365 History: Received August 05, 2007; Revised August 30, 2007; Published February 03, 2009

Detailed film cooling effectiveness distributions were experimentally obtained on a turbine blade platform within a linear cascade. The film cooling effectiveness distributions were obtained on the platform with upstream disturbances used to simulate the passing vanes. Cylindrical rods, placed upstream of the blades, simulated the wake created by the trailing edge of the stator vanes. The rods were placed at four locations to show how the film cooling effectiveness was affected relative to the vane location. In addition, delta wings were placed upstream of the blades to model the effect of the passage vortex (generated in the vane passage) on the platform film cooling effectiveness. The delta wings create a vortex similar to the passage vortex as it exits the upstream vane passage. The film cooling effectiveness was measured with the delta wings placed at four location, to investigate the effect of the passing vanes. Finally, the delta wings were coupled with the cylindrical rods to examine the combined effect of the upstream wake and passage vortex on the platform film cooling effectiveness. The detailed film cooling effectiveness distributions were obtained using pressure sensitive paint in the five blade linear cascade. An advanced labyrinth seal was placed upstream of the blades to simulate purge flow from a stator-rotor seal. The coolant flow rate varied from 0.5% to 2.0% of the mainstream flow, while the Reynolds number of the mainstream flow remained constant at 3.1×105 (based on the inlet velocity and chord length of the blade). The film cooling effectiveness was not significantly affected with the upstream rod. However, the vortex generated by the delta wings had a profound impact on the film cooling effectiveness. The vortex created more turbulent mixing within the blade passage, and the result is reduced film cooling effectiveness through the entire passage. When the vane induced secondary flow is included, the need for additional platform cooling becomes very obvious.

Copyright © 2009 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 4

Rod and delta wing positions in reference to stagnation lines

Grahic Jump Location
Figure 6

Film cooling effectiveness on platform with freestream turbulence of 5% and various seal injection rates

Grahic Jump Location
Figure 7

Film cooling effectiveness on platform with wake rod in four positions (ms=1.0%)

Grahic Jump Location
Figure 8

Film cooling effectiveness on platform with delta wing in four positions (ms=1.0%, θ=30deg)

Grahic Jump Location
Figure 10

Film cooling effectiveness on platform with wake rod and delta wing in four positions (ms=1.0%, θ=45deg)

Grahic Jump Location
Figure 11

Film cooling effectiveness on platform with wake rod and delta wing in position 4 (θ=45deg)

Grahic Jump Location
Figure 12

Comparison of laterally averaged film cooling effectiveness on the platform for various upstream conditions (ms=0.5%)

Grahic Jump Location
Figure 13

Comparison of laterally averaged film cooling effectiveness on the platform for various upstream conditions (ms=1.0%)

Grahic Jump Location
Figure 14

Comparison of laterally averaged film cooling effectiveness on the platform for various upstream conditions (ms=1.5%)

Grahic Jump Location
Figure 1

Rod and delta wing conceptual flows: (a) unsteady wake, (b) rod generated unsteady wake, (c) passage vortex in vane (6), and (d) vortex generated by delta wing

Grahic Jump Location
Figure 2

Low speed wind tunnel with turbine blade details

Grahic Jump Location
Figure 3

Platform film cooling configuration (dimensions in centimeters): (a) detail of cooled platform with rod and delta wing, (b) detail of labyrinthlike stator-rotor seal, and (c) detail of rod and delta wing

Grahic Jump Location
Figure 5

Path lines seeded near the platform (colored by velocity magnitude)

Grahic Jump Location
Figure 9

Film cooling effectiveness on platform with delta wing in four positions (ms=1.0%, θ=45deg)

Grahic Jump Location
Figure 15

Comparison of laterally averaged film cooling effectiveness on the platform for various upstream conditions (ms=2.0%)

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