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TECHNICAL PAPERS

Experimental Investigation of Secondary Flow Structure in a Blade Passage With and Without Leading Edge Fillets

[+] Author and Article Information
G. I. Mahmood

Turbine Innovation and Energy Research (TIER) Center, Louisiana State University, Baton Rouge, LA 70803

S. Acharya1

Turbine Innovation and Energy Research (TIER) Center, Louisiana State University, Baton Rouge, LA 70803acharya@me.lsu.edu

1

Corresponding author.

J. Fluids Eng 129(3), 253-262 (Jun 08, 2006) (10 pages) doi:10.1115/1.2427075 History: Received January 09, 2005; Revised June 08, 2006

Velocity and pressure measurements are presented for a blade passage with and without leading edge contouring in a low speed linear cascade. The contouring is achieved through fillets placed at the junction of the leading edge and the endwall. Two fillet shapes, one with a linear streamwise cross-section (fillet 1) and the other with a parabolic cross-section (fillet 2), are examined. Measurements are taken at a constant Reynolds number of 233,000 based on the blade chord and the inlet velocity. Data presented at different axial planes include the pressure loss coefficient, axial vorticity, velocity vectors, and yaw and pitch angles. In the early stages of the development of the secondary flows, the fillets are seen to reduce the size and strength of the suction-side leg of the horseshoe vortex with associated reductions in the pressure loss coefficients and pitch angles. Further downstream, the total pressure loss coefficients and vorticity show that the fillets lift the passage vortex higher above the endwall and move it closer to the suction side in the passage. Near the trailing edge of the passage, the size and strength of the passage vortex is smaller with the fillets, and the corresponding reductions in pressure loss coefficients extend beyond the mid-span of the blade. While both fillets reduce pressure loss coefficients and vorticity, fillet 1 (linear fillet profile) appears to exhibit greater reductions in pressure loss coefficients and pitch angles.

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Copyright © 2007 by American Society of Mechanical Engineers
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Figures

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Figure 1

(a) Schematic of the blade cascade test facility. (b) Profiles and geometric parameters of the two fillets.

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Figure 2

Coordinate systems and measurement locations in the test section

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Figure 3

Static pressure coefficients on the three blade surfaces in the two passages at spanwise location Y∕S=0.33

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Figure 4

Total pressure loss coefficient Cpt,loss in pitchwise normal plane at XG∕Cax=0.085 for baseline, fillet 1, and fillet 2

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Figure 5

Total pressure loss coefficient Cpt,loss in pitchwise normal plane at XG∕Cax=0.424 for baseline, fillet 1, and fillet 2

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Figure 6

Total pressure loss coefficient Cpt,loss in pitchwise normal plane at XG∕Cax=0.916 for baseline, fillet 1, and fillet 2

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Figure 7

Normalized axial vorticity ωx*C∕Uref contours at (a)XG∕Cax=0.424 and (b)XG∕Cax=0.916 for baseline, fillet 1, and fillet 2

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Figure 8

Normalized axial vorticity ωx*C∕Uref in two pitchwise locations at XG∕Cax=0.916 for baseline, fillet 1, and fillet 2

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Figure 9

Normalized velocity vectors from velocity components normal to streamwise direction at (a)XG∕Cax=0.085 and (b)XG∕Cax=0.916 for baseline, fillet 1, and fillet 2

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Figure 10

Flow angles at XG∕Cax=0.916 for baseline, fillet 1, and fillet 2

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Figure 11

Pitchwise-averaged total pressure loss coefficient for baseline, fillet 1, and fillet 2 in different axial locations

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Figure 12

Pitchwise-averaged flow angles for baseline and fillets

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