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Research Papers

Film Cooling Effectiveness Distributions on a Turbine Blade Cascade Platform With Stator-Rotor Purge 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

Sarah A. Blake

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. Turbomach 130(3), 031015 (May 05, 2008) (10 pages) doi:10.1115/1.2777186 History: Received February 10, 2007; Revised February 28, 2007; Published May 05, 2008

An experimental investigation to obtain detailed film cooling effectiveness distributions on a cooled turbine blade platform within a linear cascade has been completed. The Reynolds number of the freestream flow is 3.1×105, and the platform has a labyrinthlike seal upstream of the blades to model a realistic stator-rotor seal configuration. An additional coolant is supplied to the downstream half of the platform via discrete film cooling holes. The coolant flow rate through the upstream seal varies from 0.5% to 2.0% of the mainstream flow, while the blowing ratio of the coolant through the discrete holes varies from 0.5 to 2.0 (based on the mainstream velocity at the exit of the cascade). Detailed film cooling effectiveness distributions are obtained using the pressure sensitive paint (PSP) technique under a wide range of coolant flow conditions and various freestream turbulence levels (0.75% or 13.4%). The PSP technique clearly shows how adversely the coolant is affected by the passage induced flow. With only purge flow from the upstream seal, the coolant flow rate must exceed 1.5% of the mainstream flow in order to adequately cover the entire passage. However, if discrete film holes are used on the downstream half of the passage, the platform can be protected while using less coolant (i.e., the seal flow rate can be reduced).

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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 9

Film cooling effectiveness with downstream discrete film cooling

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Figure 10

Laterally averaged film cooling effectiveness on the passage end wall with downstream discrete film cooling

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Figure 11

Film cooling effectiveness with combined seal cooling (1%) and downstream film cooling (Tu=0.75%)

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Figure 12

Film cooling effectiveness with combined seal cooling (2%) and downstream film cooling (Tu=0.75%)

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Figure 13

Laterally averaged film cooling effectiveness on the passage end wall with combined upstream seal injection and downstream discrete film cooling (Tu=0.75%)

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Figure 7

Laterally averaged film cooling effectiveness on the passage end wall with upstream seal injection

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Figure 8

Comparison of the laterally averaged film cooling effectiveness on the passage end wall with upstream seal injection and tangential slot injection over a flat plate

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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 details: (a) detailed view of the cooled passage, (b) labyrinthlike stator-rotor seal, (c) cross-sectional view of two discrete film holes

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Figure 4

PSP calibration curve

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Figure 5

Film cooling effectiveness with various seal injection rates (Tu=0.75%)

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Figure 6

Film cooling effectiveness with various seal injection rates (Tu=13.4%)

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