0
Research Papers

Turbine Blade Platform Film Cooling With Typical Stator-Rotor Purge Flow and Discrete-Hole Film Cooling

[+] Author and Article Information
Zhihong Gao, Diganta Narzary

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

Je-Chin Han

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

J. Turbomach 131(4), 041004 (Jul 01, 2009) (11 pages) doi:10.1115/1.3068327 History: Received August 18, 2008; Revised August 29, 2008; Published July 01, 2009

This paper is focused on the effect of film-hole configurations on platform film cooling. The platform is cooled by purge flow from a simulated stator-rotor seal combined with discrete-hole film cooling within the blade passage. The cylindrical holes and laidback fan-shaped holes are assessed in terms of film-cooling effectiveness and total pressure loss. Lined up with the freestream streamwise direction, the film holes are arranged on the platform with two different layouts. In one layout, the film-cooling holes are divided into two rows and more concentrated on the pressure side of the passage. In the other layout, the film-cooling holes are divided into four rows and loosely distributed on the platform. Four film-cooling hole configurations are investigated totally. Testing was done in a five-blade cascade with medium high Mach number condition (0.27 and 0.44 at the inlet and the exit, respectively). The detailed film-cooling effectiveness distributions on the platform were obtained using pressure sensitive paint technique. Results show that the combined cooling scheme (slot purge flow cooling combined with discrete-hole film cooling) is able to provide full film coverage on the platform. The shaped holes present higher film-cooling effectiveness and wider film coverage than the cylindrical holes, particularly at higher blowing ratios. The hole layout affects the local film-cooling effectiveness. The shaped holes also show the advantage over the cylindrical holes with lower total pressure loss.

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 1

(a) Schematic of the cascade blade platform with upstream slot purge flow cooling and downstream discrete-hole film cooling. (b) Definition of platform coordinates.

Grahic Jump Location
Figure 2

Configuration of upstream labyrinthlike stator-rotor seal in Ref. (29)

Grahic Jump Location
Figure 3

Discrete hole configuration on platform

Grahic Jump Location
Figure 4

(a) PSP calibration at single reference temperature, and (b) PSP calibration at corresponding reference temperature

Grahic Jump Location
Figure 5

Pressure and Mach number distribution without coolant injection. (a) Pressure distribution and (b) Mach number distribution.

Grahic Jump Location
Figure 6

(a) Local coolant mass flow rate distribution along the purge slot (29), (b) discharge coefficient distribution, (c) local blowing ratio distribution for Configuration A, and (d) local blowing ratio distribution for Configuration B

Grahic Jump Location
Figure 7

Film-cooling effectiveness distribution on platform with discrete holes. (a) Configuration A and (b) Configuration C.

Grahic Jump Location
Figure 8

Film-cooling effectiveness on platform with combined slot film cooling and discrete-hole film cooling (Configuration A)

Grahic Jump Location
Figure 9

Film-cooling effectiveness on platform with combined slot film cooling and discrete-hole film cooling (Configuration B)

Grahic Jump Location
Figure 10

Film-cooling effectiveness on platform with combined slot film cooling and discrete-hole film cooling (Configuration C)

Grahic Jump Location
Figure 11

Film-cooling effectiveness on platform with combined slot film cooling and discrete-hole film cooling (Configuration D)

Grahic Jump Location
Figure 12

Laterally averaged film-cooling effectiveness (effect of blowing ratio)

Grahic Jump Location
Figure 13

Laterally averaged film-cooling effectiveness (effect of hole configuration)

Grahic Jump Location
Figure 14

Traversing plane for total pressure measurement

Grahic Jump Location
Figure 15

Total pressure distribution at the cascade exit. (a) No coolant ejection. (b) Coolant ejection from purge slot.

Grahic Jump Location
Figure 16

Total pressure distribution at the cascade exit for coolant ejection with purge flow combined with discrete holes. (a) Configuration A and (b) Configuration C.

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