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Research Papers

Three-Component LDV Measurements in the Wake of a Compressor Cascade With Flow Separation

[+] Author and Article Information
G. V. Hobson, T. M. Caruso, J. R. Carlson

Department of Aeronautics and Astronautics, Turbopropulsion Laboratory, Naval Postgraduate School, Monterey, CA 93943

J. Turbomach 130(1), 011008 (Jan 14, 2008) (8 pages) doi:10.1115/1.2364883 History: Received October 01, 2001; Revised March 01, 2002; Published January 14, 2008

Measurements were taken of the vortex system and turbulent flow that resulted from the interaction between a stator blade and the approaching endwall boundary layer in a linear cascade of compressor blades. Data were taken at a Reynolds number based on blade chord of 640,000. Five-hole pressure measurements were conducted upstream and downstream of the blade row. The approaching boundary layer was also characterized with the laser-Doppler velocimeter. Downstream three-component laser-Doppler velocimetry surveys were conducted at three streamwise stations to map the location and velocity characteristics of the wake and vortex system. Results clearly showed the extent of the vortex emanating from the separation of the boundary layer on the suction side of the blade. Finally, all components of mean flow velocity and turbulence are documented for the last survey station. These data will form a challenging test case for numerical code validation.

Copyright © 2008 by American Society of Mechanical Engineers
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References

Figures

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Figure 24

Reynolds stress (u′v′¯) distribution

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Figure 25

Reynolds stress (u′w′¯) distribution

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Figure 23

Spanwise turbulence intensity distribution at station 13

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Figure 22

Station 13 pitchwise turbulence intensity distribution

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Figure 21

Streamwise turbulence intensity distribution (30% of an axial chord downstream of the trailing edge (station 13))

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Figure 20

Turbulent kinetic energy distribution at stations 11, 12, and 13

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Figure 19

Wake nondimensional turbulent kinetic energy distribution at station 13

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Figure 18

Secondary flow development downstream of the trailing edges at 5%, 10%, and 20% axial chord

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Figure 17

Wake nondimensional velocity distribution at station 13

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Figure 16

Wake nondimensional velocity distribution at station 12

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Figure 15

Wake nondimensional velocity distribution at station 11

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Figure 14

Mass average spanwise inlet velocity and turbulent kinetic energy profiles 30% ahead of the leading edges

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Figure 13

Inlet nondimensional turbulent kinetic energy distribution at station 1 (30% of an axial chord upstream of the leading edges)

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Figure 12

Inlet nondimensional velocity distribution (30% of an axial chord upstream of the leading edge)

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Figure 11

Spanwise total pressure loss distribution

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Figure 10

Exit nondimensional velocity distribution (2.78 axial chords downstream of the leading edge)

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Figure 9

Exit total pressure distribution over blade passages (2.78 axial chords downstream from leading edge)

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Figure 8

Inlet nondimensional velocity distribution (two axial chords upstream)

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Figure 7

Inlet total pressure distribution (two axial chords upstream)

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Figure 6

Mid-span blade surface pressure distribution

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Figure 5

Schematic flow topology proposed by Delery and Meauze (13)

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Figure 4

Suction side surface flow visualization

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Figure 3

LDV measurement grid and traverse mechanism coordinate system

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Figure 2

Three-component LDV setup and plan view of the optical arrangement

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Figure 1

Schematic of the low-speed cascade tunnel

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Figure 26

Reynolds stress (v′w′¯) distribution

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