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Research Papers

Investigation of Secondary Flow Behavior in a Radial Turbine Nozzle

[+] Author and Article Information
Mohammad Alexin Putra

Assistant Scientist
Helmut-Schmidt-University,
University of the Armed Forces Hamburg,
Power Engineering,
Holstenhofweg 85,
Hamburg D-22043, Germany
e-mail: alex.putra@gmail.com

Franz Joos

Professor
Helmut-Schmidt-University,
University of the Armed Forces Hamburg,
Power Engineering,
Laboratory of Turbomachinery,
Holstenhofweg 85,
Hamburg D-22043, Germany
e-mail: joos@hsu-hh.de

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received May 26, 2006; final manuscript received April 19, 2013; published online September 13, 2013. Assoc. Editor: Michael Casey.

J. Turbomach 135(6), 061003 (Sep 13, 2013) (11 pages) Paper No: TURBO-06-1072; doi: 10.1115/1.4024627 History: Received May 26, 2006; Revised April 19, 2013

Fundamental investigation of secondary flow phenomena in a radial turbine nozzle are presented. Laser two focus (L2F) measurements have been used for validation of numerical computational fluid dynamics (CFD) calculations. Having a good agreement by using the Reynolds stress turbulence model (RSM), the numerical results have been further used to analyze the structure of secondary vortices. Contour plots of the flow angle with typical isoline pattern, as well as the vorticity, have been evaluated. It is shown that the channel of the radial nozzle similar secondary vorticity systems generates as known from the axial turbine nozzles. The formation and the development of the horseshoe vortex and the corner vortex are discussed. The well known passage vortex of the axial turbines could not been found because of the small curvature of the streamlines. Instead of these, an additional single vortex can be observed, called the “inflow” vortex caused by the unsymmetrical flow into the radial cascade from the upstream scroll.

Copyright © 2013 by ASME
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References

Figures

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Fig. 4

Grid of the one vane sector

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Fig. 3

Meshed geometries of the whole turbine casing as well as of the single vane sector

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Fig. 2

L2F measurement points in a midplane of the meridian flow

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Fig. 5

Measured Mach-number distribution of the meridian flow in the midplane at Ma2is = 0.73 (vane position 100%)

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Fig. 6

Calculated Mach-number distribution of the meridian flow in the midplane at Ma2is = 0.73 (vane position 100%)

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Fig. 7

Circumferential Mach number and flow angle distribution at vane exit midplane (vane position 80%)

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Fig. 8

Secondary flow structures and planes of investigation of the flow behavior

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Fig. 9

Mach number and flow angle α distribution in plane 5 at Ma2is = 0.73 (vane position 80%)

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Fig. 10

Flow angle distribution of line 5 in plane 1 at Ma2is = 0.73 (vane position 80%)

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Fig. 11

Mach number and flow angle distribution in plane 3 at Ma2is = 0.73 (vane position 80%)

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Fig. 12

Flow angle at position line 3A and 3B in plane 3 at Ma2is = 0.73 (vane position 80%)

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Fig. 20

Evaluation planes for the inflow vortex

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Fig. 21

Inflow vortex (plane I1)

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Fig. 22

(a) and (b) Inflow vortex (plane I4). (c) Inflow vortex (plane I4).

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Fig. 23

Evaluation planes of the corner vortex

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Fig. 13

Evaluation planes for the horseshoe vortex

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Fig. 14

Horseshoe vortex at the pressure side (plane P1)

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Fig. 15

(a) and (b) Horseshoe vortex at the pressure side (plane P2). (c) Horseshoe vortex at the pressure side (plane P2).

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Fig. 16

Horseshoe vortex at the pressure side (plane P3)

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Fig. 17

Velocity distribution of the secondary flow of the horseshoe vortex at the pressure side

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Fig. 18

Horseshoe vortex at the suction side (plane S1)

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Fig. 19

Horseshoe vortex at the suction side (plane S2)

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Fig. 24

Corner vortex (plane C1)

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Fig. 25

Corner vortex (plane C2)

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Fig. 26

Calculated pressure loss coefficient in the midplan (PS pressure side, SS suction side) at Ma2is = 0.73 (vane position 80%)

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Fig. 27

Calculated pressure loss coefficient ζloss at several planes behind the vane at Ma2is = 0.73 at vane position 80%

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