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Research Papers

Overall and Adiabatic Effectiveness Values on a Scaled Up, Simulated Gas Turbine Vane

[+] Author and Article Information
David G. Bogard

The University of Texas at Austin,
Austin, TX 78712

Gregory M. Laskowski

GE Global Research Center,
Niskayuna, NY 12309

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received April 29, 2012; final manuscript received November 12, 2012; published online June 28, 2013. Editor: David Wisler.

J. Turbomach 135(5), 051017 (Jun 28, 2013) (10 pages) Paper No: TURBO-12-1039; doi: 10.1115/1.4023105 History: Received April 29, 2012; Revised November 12, 2012

Recent advances in computational power have made conjugate heat transfer simulations of fully conducting, film cooled turbine components feasible. However, experimental data available with which to validate conjugate heat transfer simulations is limited. This paper presents experimental measurements of external surface temperature on the suction side of a scaled up, fully conducting, cooled gas turbine vane. The experimental model utilizes the matched Bi method, which produces nondimensional surface temperature measurements that are representative of engine conditions. Adiabatic effectiveness values were measured on an identical near adiabatic vane with an identical geometry and cooling configuration. In addition to providing a valuable data set for computational code validation, the data shows the effect of film cooling on the surface temperature of a film cooled part. As expected, in nearly all instances, the addition of film cooling was seen to decrease the overall surface temperature. However, due to the effect of film injection causing early boundary layer transition, film cooling at a high momentum flux ratio was shown to actually increase surface temperature over 0.35 < s/C < 0.45.

Copyright © 2013 by ASME
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References

Figures

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Fig. 5

Schematic of secondary flow loop

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Fig. 2

Test vane pressure distribution

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Fig. 1

Schematic of the simulated turbine vane test section

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Fig. 4

Suction side film cooling holes

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Fig. 3

Test airfoil schematic

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Fig. 11

Contours of adiabatic effectiveness measurements, Tu = 20%, (a) I = 0.34, (b) I = 0.75, (c) I = 1.41

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Fig. 12

Laterally averaged overall effectiveness measurements, Tu = 0.5%

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Fig. 13

Laterally averaged overall effectiveness measurements with nonfilm cooled overall effectiveness measurements, Tu = 0.5%

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Fig. 6

Laterally averaged adiabatic effectiveness measurements, Tu = 0.5%

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Fig. 7

Effect of surface curvature on laterally averaged adiabatic effectiveness, I = 0.34, Tu = 0.5%

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Fig. 8

Effect of surface curvature on laterally averaged adiabatic effectiveness, I = 0.34, Tu = 0.5%

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Fig. 9

Contours of adiabatic effectiveness measurements, Tu = 0.5%, (a) I = 0.34, (b) I = 0.75, (c) I = 1.41

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Fig. 10

Laterally averaged adiabatic effectiveness measurements, Tu = 0.5% and 20%

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Fig. 14

Measured and predicted laterally averaged overall effectiveness values, Tu = 0.5%

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Fig. 15

Contours of overall effectiveness measurements, Tu = 0.5%, (a) I = 0.34, (b) I = 0.75, (c) I = 1.41

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Fig. 16

Spanwise variation in wall temperature, x/d = 1, Tu = 0.5%

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Fig. 17

Spanwise variation in wall temperature, x/d = 10, Tu = 0.5%

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Fig. 18

Spanwise variation in wall temperature, x/d = 19, Tu = 0.5%

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