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

[+] 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
Copyright © 2003 by ASME
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Grahic Jump Location
Endwall Stanton number contours, LT, Tu=0.007,Rec=500,000
Grahic Jump Location
Endwall Stanton number contours, AC, Tu=0.131,Lu=7.2 cm,Rec=500,000
Grahic Jump Location
Endwall flow visualization using lampblack and oil showing the separation saddle point and pressure and suction surface separation lines 5
Grahic Jump Location
Comparison of 95% span pressure distributions with midspan values, Rec=2,000,000
Grahic Jump Location
Comparison of 95% span pressure distributions with midspan values, Rec=1,000,000
Grahic Jump Location
Comparison of 95% span pressure distributions with midspan values, Rec=500,000
Grahic Jump Location
Cascade Inlet Velocity Profile Compared with nonequilibrium FD channel flow, ATM, top position, Rec=2,000,000
Grahic Jump Location
Comparison between measured and predicted vane midspan pressure distribution
Grahic Jump Location
Schematic of mock aeroderivative combustor turbulence generator
Grahic Jump Location
Schematic of UND linear cascade facility
Grahic Jump Location
Endwall Stanton number contours, LT, Tu=0.007,Rec=1,000,000
Grahic Jump Location
Endwall Stanton number contours, AC, Tu=0.140,Lu=6.4 cm,Rec=1,000,000
Grahic Jump Location
Endwall Stanton number contours, LT, Tu=0.007,Rec=2,000,000
Grahic Jump Location
Endwall Stanton number contours, AC, Tu=0.134,Lu=7.3 cm,Rec=2,000,000




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