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Experiments in Fluids

, Volume 48, Issue 6, pp 1015–1023 | Cite as

Control of the corner separation in a compressor cascade by steady and unsteady plasma aerodynamic actuation

  • Ying-hong Li
  • Yun WuEmail author
  • Min Zhou
  • Chang-bing Su
  • Xiong-wei Zhang
  • Jun-qiang Zhu
Research Article

Abstract

This paper reports experimental results on using steady and unsteady plasma aerodynamic actuation to control the corner separation, which forms over the suction surface and end wall corner of a compressor cascade blade passage. Total pressure recovery coefficient distribution was adopted to evaluate the corner separation. Corner separation causes significant total pressure loss even when the angle of attack is 0°. Both steady and unsteady plasma aerodynamic actuations suppress the corner separation effectively. The control effect obtained by the electrode pair at 25% chord length is as effective as that obtained by all four electrode pairs. Increasing the applied voltage improves the control effect while it augments the power requirement. Increasing the Reynolds number or the angle of attack makes the corner separation more difficult to control. The unsteady actuation is much more effective and requires less power due to the coupling between the unsteady actuation and the separated flow. Duty cycle and excitation frequency are key parameters in unsteady plasma flow control. There are thresholds in both the duty cycle and the excitation frequency, above which the control effect saturates. The maximum relative reduction in total pressure loss coefficient achieved is up to 28% at 70% blade span. The obvious difference between steady and unsteady actuation may be that wall jet governs the flow control effect of steady actuation, while much more vortex induced by unsteady actuation is the reason for better control effect.

Keywords

Control Effect Chord Length Electrode Pair Total Pressure Loss Freestream Velocity 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

List of symbols

c

Chord length

t

Blade spacing

h

Blade height

β1

Inlet-air angle

β2

Outlet-air angle

βs

Blade stagger angle

i

Angle of attack

ν

Freestream velocity

Re

Reynolds number based on the axial chord length and the freestream velocity

T1

Static temperature at the cascade inlet

P1

Static pressure at the cascade inlet

P1*

Total pressure at the cascade inlet

P2

Static pressure at the cascade outlet

P2*

Total pressure at the cascade outlet

σ

Total pressure recovery coefficient

ω

Total pressure loss coefficient

ωbaseline

Total pressure loss coefficient without actuation

ωactuated

Total pressure loss coefficient with actuation

δ(ω)

Relative reduction in the total pressure loss coefficient

δ(ω)max

Relative reduction in the maximum total pressure loss coefficient

d1

Upper electrode width

d2

Lower electrode width

Δd

Inner space of an electrode pair

he

Electrode height

hd

Dielectric layer height

D

Space between adjacent electrode pairs

Tac

Period of the steady plasma aerodynamic actuation

F

Driving frequency of the high voltage sine wave

Tsignal

Period of the unsteady plasma aerodynamic actuation on duty

Tcontrol

Period of the unsteady plasma aerodynamic actuation

f

Excitation frequency of the unsteady plasma aerodynamic actuation

α

Duty cycle of the unsteady plasma aerodynamic actuation

C

Characteristic length of the axial separation region at the endwall

Sr

Strouhal number based on the characteristic length and the local freestream velocity

Notes

Acknowledgments

The authors thank Min JIA and Cheng-qin LI for the help in the experiment. This work was supported by the National Natural Science Foundation of China (50906100), China Postdoctoral Science Foundation (20090450373).

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Copyright information

© Springer-Verlag 2009

Authors and Affiliations

  • Ying-hong Li
    • 1
  • Yun Wu
    • 1
    Email author
  • Min Zhou
    • 1
  • Chang-bing Su
    • 1
  • Xiong-wei Zhang
    • 1
  • Jun-qiang Zhu
    • 2
  1. 1.Engineering CollegeAir Force Engineering UniversityXi’anChina
  2. 2.Institute of Engineering ThermophysicsChinese Academy of SciencesBeijingChina

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