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RESEARCH PAPERS: Forced Convection

Film Cooling Effectiveness on the Leading Edge Region of a Rotating Turbine Blade With Two Rows of Film Cooling Holes Using Pressure Sensitive Paint

[+] Author and Article Information
Jaeyong Ahn, M. T. Schobeiri

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

Je-Chin Han

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

Hee-Koo Moon

 Solar Turbines Incorporated, 2200 Pacific Highway, San Diego, CA 92101

J. Heat Transfer 128(9), 879-888 (Apr 22, 2006) (10 pages) doi:10.1115/1.2241945 History: Received October 30, 2005; Revised April 22, 2006

Detailed film cooling effectiveness distributions are measured on the leading edge of a rotating gas turbine blade with two rows (pressure-side row and suction-side row from the stagnation line) of holes aligned to the radial axis using the pressure sensitive paint (PSP) technique. Film cooling effectiveness distributions are obtained by comparing the difference of the measured oxygen concentration distributions with air and nitrogen as film cooling gas respectively and by applying the mass transfer analogy. Measurements are conducted on the first-stage rotor blade of a three-stage axial turbine at 2400rpm (positive off-design), 2550rpm (design), and 3000rpm (negative off-design), respectively. The effect of three blowing ratios is also studied. The blade Reynolds number based on the axial chord length and the exit velocity is 200,000 and the total to exit pressure ratio was 1.12 for the first-stage rotor blade. The corresponding rotor blade inlet and outlet Mach numbers are 0.1 and 0.3, respectively. The film cooling effectiveness distributions are presented along with discussions on the influence of rotational speed (off design incidence angle), blowing ratio, and upstream nozzle wakes around the leading edge region. Results show that rotation has a significant impact on the leading edge film cooling distributions with the average film cooling effectiveness in the leading edge region decreasing with an increase in the rotational speed (negative incidence angle).

Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Overall layout of TPFL-research turbine facility, from Schobeiri (30)

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Figure 2

Three-stage research turbine components, from Schobeiri (30)

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Figure 3

Conceptual view of the three-stage turbine, from Schobeiri (31)

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Figure 4

Flow path of the coolant gas

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Figure 6

Modified film cooling blade

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Figure 9

Calibration curve of the PSP

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Figure 10

Flow path inside and outside the blade for (a) positive off-design, (b) design, and (c) negative off-design conditions

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Figure 11

Leading edge region film cooling effectiveness distribution at 2400rpm, (a)M=0.5, (b)M=1.0, and (c)M=2.0

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Figure 12

Leading edge region film cooling effectiveness distribution at 2550rpm, (a)M=0.5, (b)M=1.0, and (c)M=2.0

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Figure 14

Coolant path lines colored by particle number (Yang (34))

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Figure 15

Span-wise averaged film cooling effectiveness

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Figure 5

Coolant path inside the blade

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Figure 7

Schematic drawing of the optical components

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Figure 8

Schematic calibration setup

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Figure 13

Leading edge region film cooling effectiveness distribution at 3000rpm(a)M=0.5, (b)M=1.0, and (c)M=2.0

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