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TECHNICAL PAPERS

Unsteady Flow Field of an Axial-Flow Turbine Rotor at a Low Reynolds Number

[+] Author and Article Information
Takayuki Matsunuma

 National Institute of Advanced Industrial Science and Technology (AIST) 1-2-1 Namiki, Tsukuba, Ibaraki 305-8564, Japant-matsunuma@aist.go.jp

J. Turbomach 129(2), 360-371 (Jul 18, 2006) (12 pages) doi:10.1115/1.2464143 History: Received July 13, 2006; Revised July 18, 2006

The unsteady flow field of an annular turbine rotor was investigated experimentally using a laser Doppler velocimetry (LDV) system. Detailed measurements of the time-averaged and time-resolved distributions of the velocity, flow angle, turbulence intensity, etc., were carried out at a very low Reynolds number condition, Reout=3.5×104. The data obtained were analyzed from the viewpoints of both an absolute (stationary) frame of reference and a relative (rotating) frame of reference. The effect of the turbine nozzle wake and secondary vortices on the flow field inside the rotor passage was clearly captured. It was found that the nozzle wake and secondary vortices are suddenly distorted at the rotor inlet, because of the rotating potential field of the rotor. The nozzle flow (wake and passage vortices) and the rotor flow (boundary layer, wake, tip leakage vortex, and passage vortices) interact intensively inside the rotor passage.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Velocity triangles (absolute flow and relative flow)

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Figure 2

Annular turbine wind tunnel

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Figure 3

Geometry of turbine nozzle

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Figure 4

Geometry of turbine rotor

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Figure 5

LDV measurement locations

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Figure 6

Data analysis method in absolute frame of reference

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Figure 7

Data analysis method in relative frame of reference

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Figure 8

Example of instantaneous data and ensemble-averaged data at rotor exit (ZRT∕Cax,RT=1.096, Y∕H=0.5 midspan)

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Figure 9

Total pressure loss at rotor exit midspan

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Figure 10

Spanwise distributions of total pressure loss, static pressure, and velocity at nozzle inlet (axial position ZNZ∕Cax,NZ=−0.706)

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Figure 11

Oil-film visualization of nozzle suction surface flow (view from downstream looking back up passages)

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Figure 12

Distributions of total pressure loss, secondary flow, absolute velocity, and static pressure at nozzle exit (at rotor inlet) measured with a five-hole pressure probe (axial position ZNZ∕Cax,NZ=1.154)

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Figure 13

Time-averaged absolute velocity and turbulence intensity at nozzle exit measured by LDV (ZNZ∕Cax,NZ=1.154, absolute frame of reference)

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Figure 14

Time-averaged absolute velocity and turbulence intensity at nozzle exit (two different axial positions)

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Figure 15

Time-resolved absolute velocity at nozzle exit (ZNZ∕Cax,NZ=1.435, ZRT∕Cax,RT=−0.220, absolute frame of reference)

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Figure 16

Time-resolved turbulence intensity at nozzle exit (ZNZ∕Cax,NZ=1.435, ZRT∕Cax,RT=−0.220, absolute frame of reference)

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Figure 17

Time-resolved relative velocity at nozzle exit (ZNZ∕Cax,NZ=1.435, ZRT∕Cax,RT=−0.220, relative frame of reference)

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Figure 18

Velocity triangles at marks H, F, I, J, and G

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Figure 19

Time-resolved relative velocity at rotor front (ZRT∕Cax,RT=0.121, relative frame of reference)

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Figure 20

Time-resolved turbulence intensity at rotor front (ZRT∕Cax,RT=0.121, relative frame of reference)

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Figure 21

Time-resolved turbulence intensity at X-Y plane and six Z-Y planes (time index t=1∕32TNZ)

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Figure 22

Time-resolved turbulence intensity at three spanwise locations (time index t=1∕32TNZ)

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Figure 23

Time-resolved relative velocity at rotor rear (ZRT∕Cax,RT=0.853, relative frame of reference)

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Figure 24

Time-resolved turbulence intensity at rotor rear (ZRT∕Cax,RT=0.853, relative frame of reference)

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Figure 25

Time-resolved turbulence intensity at rotor rear (time index t=1∕32TNZ, ZRT∕Cax,RT=0.853)

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Figure 26

Time-resolved relative velocity at rotor exit (ZRT∕Cax,RT=1.145, relative frame of reference)

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Figure 27

Time-resolved turbulence intensity at rotor exit (ZRT∕Cax,RT=1.145, relative frame of reference)

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Figure 28

Time-resolved turbulence intensity at rotor exit (time index t=1∕32TNZ, ZRT∕Cax,RT=1.145)

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Figure 29

Time-resolved turbulence intensity at rotor passage (time index t=1∕32TNZ)

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Figure 30

Time-averaged, pitchwise-averaged spanwise distributions of velocity and flow angle at rotor exit in relative frame of reference (ZRT∕Cax,RT=1.145)

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Figure 31

Time-averaged flow on rotor suction surface

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Figure 32

Time-resolved relative velocity on rotor suction surface

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Figure 33

Time-resolved turbulence intensity on rotor suction surface

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