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TECHNICAL PAPERS

The Influence of Turbulence on Wake Dispersion and Blade Row Interaction in an Axial Compressor

[+] Author and Article Information
Alan D. Henderson

School of Engineering, University of Tasmania, Hobart 7001, AustraliaAlan.Henderson@utas.edu.au

Gregory J. Walker

School of Engineering, University of Tasmania, Hobart 7001, Australiagreg.walker@utas.edu.au

Jeremy D. Hughes

 Rolls-Royce plc, Derby DE24 8BJ, UKjeremy.hughes@rolls-royce.com

J. Turbomach 128(1), 150-157 (Feb 01, 2005) (8 pages) doi:10.1115/1.2098809 History: Received October 01, 2004; Revised February 01, 2005

The influence of free-stream turbulence on wake dispersion and boundary layer transition processes has been studied in a 1.5-stage axial compressor. An inlet grid was used to produce turbulence characteristics typical of an embedded stage in a multistage machine. The grid turbulence strongly enhanced the dispersion of inlet guide vane (IGV) wakes. This modified the interaction of IGV and rotor wakes, leading to a significant decrease in periodic unsteadiness experienced by the downstream stator. These observations have important implications for the prediction of clocking effects in multistage machines. Boundary layer transition characteristics on the outlet stator were studied with a surface hot-film array. Observations with grid turbulence were compared with those for the natural low turbulence inflow to the machine. The transition behavior under low turbulence inflow conditions with the stator blade element immersed in the dispersed IGV wakes closely resembled the behavior with elevated grid turbulence. It is concluded that with appropriate alignment, the blade element behavior in a 1.5-stage axial machine can reliably indicate the blade element behavior of an embedded row in a multistage machine.

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Copyright © 2006 by American Society of Mechanical Engineers
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Figures

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Figure 1

University of Tasmania research compressor facility

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Figure 2

Cross section of the research compressor showing the mid-passage turbulence grid and blade row configuration and a typical instantaneous wake dispersion pattern: S=suction surface, P=pressure surface

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Figure 3

Measured stator blade surface velocity distribution for the the three load cases without turbulence grid (from Walker (4)): SS=suction surface; PS=pressure surface

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Figure 4

View looking upstream showing path of probe traverse relative to inlet guide vanes. The origin for circumferential position (w) is arbitrary.

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Figure 5

Stator inlet flow field for low turbulence case (without grid). The line contours show ensemble-averaged disturbance level ⟨Tu⟩ in 1% intervals. The color contours show ensemble-averaged velocity ⟨u⟩∕u¯s.

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Figure 6

Stator inlet flow field for high turbulence case (with grid). The line contours show ensemble-averaged disturbance level ⟨Tu⟩ in 1% intervals. The color contours show ensemble-averaged velocity ⟨u⟩∕u¯s.

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Figure 7

Circumferential variation of turbulence properties at stator inlet for low loading (high turbulence case)

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Figure 8

Stator surface intermittency for high load cases

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Figure 9

Stator surface intermittency for medium load cases

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Figure 10

Stator surface intermittency for low load cases

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