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Research Papers

Simplified Approach to Predicting Rough Surface Transition

[+] Author and Article Information
R. J. Boyle

 NASA Glenn Research Center, Cleveland, OH 44135robert.j.boyle@grc.nasa.gov

M. Stripf

 Universität Karlsruhe, 76128 Karlsruhe, Germanymatthias.stripf@its.uni-karlsruhe.de

J. Turbomach 131(4), 041020 (Jul 13, 2009) (11 pages) doi:10.1115/1.3072521 History: Received September 12, 2008; Revised October 28, 2008; Published July 13, 2009

Turbine vane heat transfer predictions are given for smooth and rough vanes where the experimental data show transition moving forward on the vane as the surface roughness physical height increases. Consistent with smooth vane heat transfer, the transition moves forward for a fixed roughness height as the Reynolds number increases. Comparisons are presented with published experimental data. Some of the data are for a regular roughness geometry with a range of roughness heights, Reynolds numbers, and inlet turbulence intensities. The approach taken in this analysis is to treat the roughness in a statistical sense, consistent with what would be obtained from blades measured after exposure to actual engine environments. An approach is given to determine the equivalent sand grain roughness from the statistics of the regular geometry. This approach is guided by the experimental data. A roughness transition criterion is developed, and comparisons are made with experimental data over the entire range of experimental test conditions. Additional comparisons are made with experimental heat transfer data, where the roughness geometries are both regular and statistical. Using the developed analysis, heat transfer calculations are presented for the second stage vane of a high pressure turbine at hypothetical engine conditions.

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Copyright © 2009 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Arrangement of truncated cone roughness elements

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Figure 2

Heat transfer coefficients, Rein=2.5×105, Tu=8%

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Figure 3

Comparison of fully turbulent calculations with data Rein=250,000, Tu=8%

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Figure 4

Transition modeling predictions, Rein=250,000

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Figure 5

Transition modeling predictions, Rein=1.4×105

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Figure 6

Transition modeling predictions, Rein=0.9×105, Tuin=8%

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Figure 7

Comparison with rotor data of Blair (43)

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Figure 8

Comparison with vane data of Boyle and Senyitko (44)

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Figure 9

Comparison with LPT blade data of Stripf (45)

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Figure 10

Effect of roughness spacing on heat transfer

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Figure 11

Mach number distributions

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Figure 12

Nusselt numbers at Re1=300,000 cm−1, Tu=8%

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Figure 13

Calculated losses at Re1=300,000 cm−1

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