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Research Papers

Flow Control of Annular Compressor Cascade by Synthetic Jets

[+] Author and Article Information
Xinqian Zheng

Department of Automotive Engineering, Tsinghua University, Beijing, 100084, China and National Key Laboratory of Aircraft Engine, Beihang University, Beijing, 100083, China

Sheng Zhou, Yajun Lu, Anping Hou, Qiushi Li

National Key Laboratory of Aircraft Engine,  Beihang University, Beijing, 100083, China

J. Turbomach 130(2), 021018 (Mar 24, 2008) (7 pages) doi:10.1115/1.2751147 History: Received August 29, 2006; Revised November 14, 2006; Published March 24, 2008

An experimental investigation conducted in a stationary annular cascade wind tunnel demonstrated that unsteady flow control using synthetic jets (zero mass flux) could effectively reduce flow separation in the axial compressor cascade. The synthetic jets driven by speaker were introduced through the casing radially into the flow-field just adjacent to the leading edge of the compressor cascade. The experimental results revealed that the aerodynamic performance of the compressor cascade could be improved amazingly by synthetic jets and the maximum relative reduction of loss coefficient was up to 27.5%. The optimal analysis of the excitation frequency, excitation location was investigated at different incidences. In order to obtain detailed information on flow-field structure, the digital particle image velocimetry (DPIV) technique was adopted. The experimental results indicated that the intensity of wake vortices became much weaker and streamlines became smoother and more uniform with synthetic jets.

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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 1

Photo of the annular cascade

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Figure 2

Sketch of excitation location

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Figure 3

Four stations for synthetic jets

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Figure 4

Arrangement of optical path

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Figure 5

(a) Relative reduction of loss coefficient and (b) jet velocity versus excitation frequency

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Figure 6

Relative reduction of loss coefficient versus incidence

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Figure 7

Total pressure loss along pitch distance with and without synthetic jet for the four station, i=10deg

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Figure 8

Introduction of the picture by DPIV: 1, profile of compressor cascade; 2, inaccessible region; 3, streamlines; 4, laser sheet after reflecting from planar mirror: (a)i=5deg, (b)i=10deg, and (c)i=16deg

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Figure 9

Instantaneous vorticity field and streamline without synthetic jet: (a)i=5deg, (b)i=10deg, and (c)i=16deg

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Figure 10

Instantaneous vorticity field and streamline with synthetic jet

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Figure 11

Time-averaged vorticity field without synthetic jet, i=10deg

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Figure 12

Time-averaged vorticity field with synthetic jet, i=10deg, fe=750Hz

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