A Numerical Study of Secondary Flow in Axial Turbines With Application to Radial Transport of Hot Streaks

[+] Author and Article Information
Dilip Prasad

United Technologies Research Center, East Hartford, CT 06108

Gavin J. Hendricks

Pratt & Whitney, East Hartford, CT 06108

J. Turbomach 122(4), 667-673 (Feb 01, 2000) (7 pages) doi:10.1115/1.1313817 History: Received February 01, 2000
Copyright © 2000 by ASME
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Grahic Jump Location
(a) Illustration of vane exit geometry and nomenclature; (b) view of the vane trailing edge looking upstream; solid line represents the trailing edge
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Schematic illustration of the secondary flow in the rotor passage. The direction of the primary flow is out of the plane. Note that in the upper part of the blade passage, the radial velocity contribution from the secondary flow (solid line) reinforces that from the relative eddy (broken line) near the pressure surface.
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Variation of the vane exit flow angle at midpassage as a function of span. The solid line illustrates the vane exit flow angle for the baseline geometry, while ––– and ⋅–⋅ represent positive and reverse twist (see “Secondary Flow Control”), respectively.
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Contours of total temperature at the inlet boundary; values range from 1.05 to 1.3 in steps of 0.05
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Spanwise variation of pitch angle at three circumferential locations. The solid lines represent the results of the steady run, while the broken lines represent those for the time-averaged unsteady run.
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Temperature distribution in blade at 33 percent chord: (a) steady computation, (b) time-averaged unsteady computation. The segregation of the hot fluid toward pressure surface (on the right side) is evident.
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Velocity triangle at vane exit
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Illustration of (a) positive, (b) nominal, and (c) reverse twist
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Steady-state temperature distribution close to the pressure surface of the blade passage for vanes with: (a) positive twist, (b) nominal twist, and (c) reverse twist
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Pitch angle at a streamwise distance of 0.33 chord downstream of the leading edge of the rotor blade, along a radial line close to the pressure surface; the nominal case is represented by –⋅⋅–, while ––– and — represent the positive and reverse twist cases, respectively
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Instantaneous view of temperature contours in four successive blade passages for vanes with: (a) positive twist, and (b) reverse twist




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