Research Papers

Experimental Measurements and Computational Predictions for an Internally Cooled Simulated Turbine Vane

[+] Author and Article Information
Jason E. Dees, David G. Bogard, Gustavo A. Ledezma, Gregory M. Laskowski, Anil K. Tolpadi

 The University of Texas at Austin, Austin, TX 78712GE Global Research Center, Niskayuna, NY 12309GE Energy, Schenectady, NY 12345

J. Turbomach 134(6), 061003 (Aug 27, 2012) (9 pages) doi:10.1115/1.4006280 History: Received September 27, 2010; Revised May 23, 2011; Published August 27, 2012; Online August 27, 2012

In this study the conjugate heat transfer effects for an internally cooled vane were studied experimentally and computationally. Experimentally, a large scale model vane was used with an internal cooling configuration characteristic of real gas turbine airfoils. The cooling configuration employed consisted of a U-bend channel for cooling the leading edge region of the airfoil and a radial channel for cooling the middle third of the vane. The thermal conductivity of the solid was specially selected so that the Biot number for the model matched typical engine conditions. This ensured that scaled nondimensional surface temperatures for the model were representative of those in the first stage of a high pressure turbine. The performance of the internal cooling circuit was quantified experimentally for internal flow Reynolds numbers ranging from 10,000 to 40,000. The external surface temperature distribution was mapped over the entire vane surface. Additional measurements, including internal surface temperature measurements as well as coolant inlet and exit temperatures, were conducted. Comparisons between the experimental measurements and computational predictions of external heat transfer coefficient are presented.

Copyright © 2012 by by ASME
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Figure 1

Schematic of the simulated turbine vane test section

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Figure 2

Test airfoil schematic

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Figure 3

Schematic of secondary flow loop

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Figure 4

Location of pressure taps and internal thermocouples

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Figure 5

Computational domains and grid detail

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Figure 6

Pressure distribution around test airfoil

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Figure 7

Contours of the mean velocity at coolant inlets

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Figure 8

Laterally averaged external heat transfer coefficient: (a) experimental and (b) computational

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Figure 9

Laterally averaged external φ values at vane midspan

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Figure 10

Tripped and untripped external φ; ReU-bend  = Reradial  = 20,000

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Figure 11

Laterally averaged external φ(Re = 20,000) and he , midspan

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Figure 12

Internal φ values at vane midspan

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Figure 13

Internal and external φ, Re = 20,000, midspan

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Figure 14

External φ variation, Re = 20,000

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Figure 15

Spanwise internal and external φ, s/C = 0.27

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Figure 16

Spanwise internal and external φ, s/C = −0.24

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Figure 17

Normalized coolant temperature rise

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Figure 18

Total heat transfer rate




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