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Research Papers: Forced Convection

Film Cooling Effectiveness Distribution on a Gas Turbine Blade Platform With Inclined Slot Leakage and Discrete Film Hole Flows

[+] Author and Article Information
Lesley M. Wright

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

Zhihong Gao, Huitao Yang

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

Je-Chin Han

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

J. Heat Transfer 130(7), 071702 (May 19, 2008) (11 pages) doi:10.1115/1.2907440 History: Received February 22, 2007; Revised June 11, 2007; Published May 19, 2008

A five-blade, linear cascade is used to experimentally investigate turbine blade platform cooling. A 30deg inclined slot upstream of the blades is used to model the seal between the stator and rotor, and 12 discrete film holes are located on the downstream half of the platform for additional cooling. The film cooling effectiveness is measured on the platform using pressure sensitive paint (PSP). Using PSP, it is clear that the film cooling effectiveness on the blade platform is strongly influenced by the platform secondary flow through the passage. Increasing the slot injection rate weakens the secondary flow and provides more uniform film coverage. Increasing the freestream turbulence level was shown to increase film cooling effectiveness on the endwall, as the increased turbulence also weakens the passage vortex. However, downstream, near the discrete film cooling holes, the increased turbulence decreases the film cooling effectiveness. Finally, combining upstream slot flow with downstream discrete film holes should be cautiously done to ensure coolant is not wasted by overcooling regions on the platform.

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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 1

Overview of the low speed wind tunnel used to study platform cooling

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Figure 2

Low speed wind tunnel and turbine blade details

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Figure 3

Platform film cooling configurations: (a) detailed view of cooled passage; (b) upstream slot injection details; (c) cross-sectional view of two discrete film holes

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Figure 4

PSP calibration curve

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Figure 5

Measured film cooling effectiveness with various slot injection rates (Tu=0.75%)

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Figure 6

Measured film cooling effectiveness with various slot injection rates (Tu=13.4%)

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Figure 7

Measured film cooling effectiveness with downstream discrete film cooling

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Figure 8

Measured film cooling effectiveness with combined slot cooling (1%) and downstream film cooling (Tu=0.75%)

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Figure 9

Measured film cooling effectiveness with combined slot cooling (2%) and downstream film cooling (Tu=0.75%)

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Figure 10

Laterally averaged film cooling effectiveness on the passage endwall with upstream slot injection

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Figure 11

Laterally averaged film cooling effectiveness on the passage endwall downstream discrete film hole cooling

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Figure 12

Laterally averaged film cooling effectiveness on the passage endwall with combined upstream slot injection and downstream discrete film hole cooling (Tu=0.75%)

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Figure 13

Comparison of the laterally averaged film cooling effectiveness on the passage endwall with upstream slot injection with correlations for discrete, inclined film cooling holes and tangential slot injection over a flat plate

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