Effects of Aeroderivative Combustor Turbulence on Endwall Heat Transfer Distributions Acquired in a Linear Vane Cascade

Forrest E. Ames; Pierre A. Barbot; Chao Wang

doi:10.1115/1.1559897

Journal of Turbomachinery | Volume 125 | Issue 2 | TECHNICAL PAPERS

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TECHNICAL PAPERS

Effects of Aeroderivative Combustor Turbulence on Endwall Heat Transfer Distributions Acquired in a Linear Vane Cascade

Forrest E. Ames, Mem. ASME, Pierre A. Barbot and Chao Wang

[+] Author and Article Information

Forrest E. Ames, Pierre A. Barbot, Chao Wang

Mechanical Engineering Department, University of North Dakota, Grand Forks, ND 58202

J. Turbomach 125(2), 210-220 (Apr 23, 2003) (11 pages) doi:10.1115/1.1559897 History: Received December 04, 2001; Online April 23, 2003

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References

Figures

Cascade Inlet Velocity Profile Compared with nonequilibrium FD channel flow, ATM, top position, Re_c=2,000,000

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Comparison of 95% span pressure distributions with midspan values, Re_c=500,000

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Comparison of 95% span pressure distributions with midspan values, Re_c=1,000,000

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Comparison of 95% span pressure distributions with midspan values, Re_c=2,000,000

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Endwall flow visualization using lampblack and oil showing the separation saddle point and pressure and suction surface separation lines 5

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Endwall Stanton number contours, LT, Tu=0.007,Re_c=500,000

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Endwall Stanton number contours, AC, Tu=0.131,Lu=7.2 cm,Re_c=500,000

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Endwall Stanton number contours, LT, Tu=0.007,Re_c=1,000,000

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Endwall Stanton number contours, AC, Tu=0.140,Lu=6.4 cm,Re_c=1,000,000

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Endwall Stanton number contours, LT, Tu=0.007,Re_c=2,000,000

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Endwall Stanton number contours, AC, Tu=0.134,Lu=7.3 cm,Re_c=2,000,000

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Ames FE, Barbot PA, Wang C. Effects of Aeroderivative Combustor Turbulence on Endwall Heat Transfer Distributions Acquired in a Linear Vane Cascade. ASME. J. Turbomach. 2003;125(2):210-220. doi:10.1115/1.1559897.

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Effects of Aeroderivative Combustor Turbulence on Endwall Heat Transfer Distributions Acquired in a Linear Vane Cascade

References

Figures

Schematic of UND linear cascade facility

Schematic of mock aeroderivative combustor turbulence generator

Comparison between measured and predicted vane midspan pressure distribution

Cascade Inlet Velocity Profile Compared with nonequilibrium FD channel flow, ATM, top position, Re_c=2,000,000

Comparison of 95% span pressure distributions with midspan values, Re_c=500,000

Comparison of 95% span pressure distributions with midspan values, Re_c=1,000,000

Comparison of 95% span pressure distributions with midspan values, Re_c=2,000,000

Endwall flow visualization using lampblack and oil showing the separation saddle point and pressure and suction surface separation lines 5

Endwall Stanton number contours, LT, Tu=0.007,Re_c=500,000

Endwall Stanton number contours, AC, Tu=0.131,Lu=7.2 cm,Re_c=500,000

Endwall Stanton number contours, LT, Tu=0.007,Re_c=1,000,000

Endwall Stanton number contours, AC, Tu=0.140,Lu=6.4 cm,Re_c=1,000,000

Endwall Stanton number contours, LT, Tu=0.007,Re_c=2,000,000

Endwall Stanton number contours, AC, Tu=0.134,Lu=7.3 cm,Re_c=2,000,000

Tables

Errata

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Effects of Aeroderivative Combustor Turbulence on Endwall Heat Transfer Distributions Acquired in a Linear Vane Cascade

References

Figures

Schematic of UND linear cascade facility

Schematic of mock aeroderivative combustor turbulence generator

Comparison between measured and predicted vane midspan pressure distribution

Cascade Inlet Velocity Profile Compared with nonequilibrium FD channel flow, ATM, top position, Rec=2,000,000

Comparison of 95% span pressure distributions with midspan values, Rec=500,000

Comparison of 95% span pressure distributions with midspan values, Rec=1,000,000

Comparison of 95% span pressure distributions with midspan values, Rec=2,000,000

Endwall flow visualization using lampblack and oil showing the separation saddle point and pressure and suction surface separation lines 5

Endwall Stanton number contours, LT, Tu=0.007,Rec=500,000

Endwall Stanton number contours, AC, Tu=0.131,Lu=7.2 cm,Rec=500,000

Endwall Stanton number contours, LT, Tu=0.007,Rec=1,000,000

Endwall Stanton number contours, AC, Tu=0.140,Lu=6.4 cm,Rec=1,000,000

Endwall Stanton number contours, LT, Tu=0.007,Rec=2,000,000

Endwall Stanton number contours, AC, Tu=0.134,Lu=7.3 cm,Rec=2,000,000

Tables

Errata

Discussions

Related Content

Journals

Conference Proceedings

eBooks

Cascade Inlet Velocity Profile Compared with nonequilibrium FD channel flow, ATM, top position, Re_c=2,000,000

Comparison of 95% span pressure distributions with midspan values, Re_c=500,000

Comparison of 95% span pressure distributions with midspan values, Re_c=1,000,000

Comparison of 95% span pressure distributions with midspan values, Re_c=2,000,000

Endwall Stanton number contours, LT, Tu=0.007,Re_c=500,000

Endwall Stanton number contours, AC, Tu=0.131,Lu=7.2 cm,Re_c=500,000

Endwall Stanton number contours, LT, Tu=0.007,Re_c=1,000,000

Endwall Stanton number contours, AC, Tu=0.140,Lu=6.4 cm,Re_c=1,000,000

Endwall Stanton number contours, LT, Tu=0.007,Re_c=2,000,000

Endwall Stanton number contours, AC, Tu=0.134,Lu=7.3 cm,Re_c=2,000,000