Research Papers

Heat Transfer Measurements and Predictions for a Modern, High-Pressure, Transonic Turbine, Including Endwalls

[+] Author and Article Information
James A. Tallman, Anil K. Tolpadi

 General Electric Global Research Center, Niskayuna, NY 12309

Charles W. Haldeman, Michael G. Dunn

Gas Turbine Laboratory, The Ohio State University, Columbus, OH 43220

Robert F. Bergholz

 General Electric Transportation, Cincinnati, OH 45215

J. Turbomach 131(2), 021001 (Jan 22, 2009) (14 pages) doi:10.1115/1.2985072 History: Received July 14, 2006; Revised August 18, 2008; Published January 22, 2009

This paper presents both measurements and predictions of the hot-gas-side heat transfer to a modern, 112 stage high-pressure, transonic turbine. Comparisons of the predicted and measured heat transfer are presented for each airfoil at three locations, as well as on the various endwalls and rotor tip. The measurements were performed using the Ohio State University Gas Turbine Laboratory Test Facility (TTF). The research program utilized an uncooled turbine stage at a range of operating conditions representative of the engine: in terms of corrected speed, flow function, stage pressure ratio, and gas-to-metal temperature ratio. All three airfoils were heavily instrumented for both pressure and heat transfer measurements at multiple locations. A 3D, compressible, Reynolds-averaged Navier–Stokes computational fluid dynamics (CFD) solver with k-ω turbulence modeling was used for the CFD predictions. The entire 112 stage turbine was solved using a single computation, at two different Reynolds numbers. The CFD solutions were steady, with tangentially mass-averaged inlet/exit boundary condition profiles exchanged between adjacent airfoil-rows. Overall, the CFD heat transfer predictions compared very favorably with both the global operation of the turbine and with the local measurements of heat transfer. A discussion of the features of the turbine heat transfer distributions, and their association with the corresponding flow-physics, has been included.

Copyright © 2009 by American Society of Mechanical Engineers
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Figure 1

Rig schematic drawing (stretched image)

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Figure 7

Measurements and CFD predictions of airfoil heat transfer: low-pressure vane

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Figure 2

Measurements and CFD predictions of airfoil pressures (measurements at Re∕L=6.1×106)

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Figure 3

Measurements and CFD predictions of airfoil heat transfer: high-pressure vane

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Figure 4

Measurements and CFD predictions of endwall heat transfer: high-pressure vane

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Figure 5

Measurements and CFD predictions of airfoil heat transfer: high-pressure blade

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Figure 6

Measurements and CFD predictions of endwall and tip heat transfer: high-pressure blade



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