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Journal of Turbomachinery | Volume 133 | Issue 4 | Research Paper
Research Papers

Separation Control of Axial Compressor Cascade by Fluidic-Based Excitations

[+] Author and Article Information
Xinqian Zheng

State Key Laboratory of Automotive Safety and Energy, Tsinghua University, Beijing 100084, China

Yangjun Zhang

State Key Laboratory of Automotive Safety and Energy, Tsinghua University, Beijing 100084, Chinazhengxq@tsinghua.edu.cn

Weidong Xing, Junyue Zhang

 National Key Laboratory of Diesel Engine Turbocharging Technology, Datong, Shanxi 037036, China

J. Turbomach 133(4), 041016 (Apr 21, 2011) (7 pages) doi:10.1115/1.4002407 History: Received October 03, 2007; Revised February 12, 2010; Published April 21, 2011; Online April 21, 2011
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Flow separation control was investigated on a compressor cascade using three types of fluidic-based excitations: steady suction, steady blowing, and synthetic jet. By solving unsteady Reynolds–averaged Navier–Stokes equations, the effect of excitation parameters (amplitude, angle, and location) on performance was addressed. The results show that the separated flow can be controlled by the fluidic-based actuators effectively and the time-averaged performance of the flow field can be improved remarkably. Generally, the improvement can be enhanced when the amplitude of excitation is increased. The optimal direction varies with each type of excitations and is related to physical mechanisms underlying the separation control. For two types of steady excitations, the most effective jet location is at a distance upstream of the time-averaged separation point and the synthetic jet is just at the separation point.
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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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+Comparisons of static pressure distribution on profile surface between the measurements and the simulation results
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Comparisons of static pressure distribution on profile surface between the measurements and the simulation results
Figure 1

Comparisons of static pressure distribution on profile surface between the measurements and the simulation results

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+Cascade geometry and excitations parameters
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Cascade geometry and excitations parameters
Figure 2

Cascade geometry and excitations parameters

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+The loss coefficient for different relative steady suction amplitude (α=−90 deg, l¯=15.6%)
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The loss coefficient for different relative steady suction amplitude (α=−90 deg, l¯=15.6%)
Figure 3

The loss coefficient for different relative steady suction amplitude (α=−90 deg, l¯=15.6%)

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+Instantaneous contour plots for Ma, and vorticity plus streamlines. Steady suction (A¯=8%, α=90 deg, l¯=15.6%).
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Instantaneous contour plots for Ma, and vorticity plus streamlines. Steady suction (A¯=8%, α=90 deg, l¯=15.6%).
Figure 13

Instantaneous contour plots for Ma, and vorticity plus streamlines. Steady suction (A¯=8%, α=90 deg, l¯=15.6%).

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+Instantaneous contour plots for Ma, and vorticity plus streamlines. Steady blowing for (A¯=75%, α=2 deg, l¯=15.6%).
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Instantaneous contour plots for Ma, and vorticity plus streamlines. Steady blowing for (A¯=75%, α=2 deg, l¯=15.6%).
Figure 14

Instantaneous contour plots for Ma, and vorticity plus streamlines. Steady blowing for (A¯=75%, α=2 deg, l¯=15.6%).

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+The loss coefficient for different steady suction direction (A¯=8%)
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The loss coefficient for different steady suction direction (A¯=8%)
Figure 4

The loss coefficient for different steady suction direction (A¯=8%)

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+Loss coefficient for different steady suction location (A¯=8%, α=−90 deg)
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Loss coefficient for different steady suction location (A¯=8%, α=−90 deg)
Figure 5

Loss coefficient for different steady suction location (A¯=8%, α=−90 deg)

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+Loss coefficient for different relative steady blowing amplitude at three locations (α=2 deg)
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Loss coefficient for different relative steady blowing amplitude at three locations (α=2 deg)
Figure 6

Loss coefficient for different relative steady blowing amplitude at three locations (α=2 deg)

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+Loss coefficient for steady blowing direction (A¯=90%, l¯=26.2%)
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Loss coefficient for steady blowing direction (A¯=90%, l¯=26.2%)
Figure 7

Loss coefficient for steady blowing direction (A¯=90%, l¯=26.2%)

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+Loss coefficient for different steady blowing location (A¯=90%, α=2 deg)
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Loss coefficient for different steady blowing location (A¯=90%, α=2 deg)
Figure 8

Loss coefficient for different steady blowing location (A¯=90%, α=2 deg)

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+Loss coefficient for different synthetic jet amplitude (f¯=1, α=90 deg, l¯=26.2%)
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Loss coefficient for different synthetic jet amplitude (f¯=1, α=90 deg, l¯=26.2%)
Figure 9

Loss coefficient for different synthetic jet amplitude (f¯=1, α=90 deg, l¯=26.2%)

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+Loss coefficient for different synthetic jet direction (f¯=1, l¯=26.2%, A¯=40%)
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Loss coefficient for different synthetic jet direction (f¯=1, l¯=26.2%, A¯=40%)
Figure 10

Loss coefficient for different synthetic jet direction (f¯=1, l¯=26.2%, A¯=40%)

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+Loss coefficient versus synthetic jet location (f¯=1, A¯=30%, α=90 deg)
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Loss coefficient versus synthetic jet location (f¯=1, A¯=30%, α=90 deg)
Figure 11

Loss coefficient versus synthetic jet location (f¯=1, A¯=30%, α=90 deg)

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+Instantaneous contour plots for Ma, and total pressure plus streamlines. Baseline flow.
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Instantaneous contour plots for Ma, and total pressure plus streamlines. Baseline flow.
Figure 12

Instantaneous contour plots for Ma, and total pressure plus streamlines. Baseline flow.

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