Research Papers

Controlling Corner Stall Separation With Plasma Actuators in a Compressor Cascade

[+] Author and Article Information
Eray Akcayoz

Pratt & Whitney Canada,
1000 Marie-Victorin Boulevard,
Longueuil, QC J4G 1A1 Canada
e-mail: eray.akcayoz@pwc.ca

Huu Duc Vo

Department of Mechanical Engineering,
École Polytechnique de Montréal,
2900 boulevard Edouard-Montpetit,
2500 chemin de Polytechnique,
Montreal, QC H3T 1J4, Canada
e-mail: huu-duc.vo@polymtl.ca

Ali Mahallati

Concepts NREC,
White River Junction, VT 05001
e-mail: amahallati@conceptsnrec.com

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received January 16, 2016; final manuscript received January 29, 2016; published online March 30, 2016. Editor: Kenneth C. Hall.

J. Turbomach 138(8), 081008 (Mar 30, 2016) (13 pages) Paper No: TURBO-16-1015; doi: 10.1115/1.4032675 History: Received January 16, 2016; Revised January 29, 2016

This paper presents a numerical and experimental assessment of a plasma actuation concept for controlling corner stall separation in a highly loaded compressor cascade. CFD simulations were first carried out to assess actuator effectiveness and determine the best actuation parameters. Subsequently, experiments were performed to demonstrate the concept and confirmed the CFD tool validity at a Reynolds number of 1.5 × 105. Finally, the validated CFD tool was used to simulate the concept at higher velocities, beyond the experimental capability of existing plasma actuators. These results were used to obtain a preliminary scaling law that would allow approximation of the plasma actuation requirements at realistic operating conditions. Several configurations were examined, but the most effective setup was found to be when plasma actuators were mounted upstream of the separation point on both the suction surface and the endwall. Most of the improvement in total pressure loss stemmed from the suction surface actuator. Comparison with experimental data showed that the CFD simulations could capture the flow features and the effect of plasma actuation reasonably well. Simulations at higher flow velocities indicated that the required plasma actuator strength scales approximately with the square of the Reynolds number.

Copyright © 2016 by ASME
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Kang, S. , and Hirsch, C. , 1991, “ Three Dimensional Flow in a Linear Compressor Cascade at Design Conditions,” ASME Paper No. 91-GT-114.
Hah, C. , and Loellbach, J. , 1999, “ Development of Hub Corner Stall and Its Influence on the Performance of Axial Compressor Blade Rows,” ASME J. Turbomach., 121(1), pp. 67–77. [CrossRef]
Lei, V. M. , Spakovszky, Z. S. , and Greitzer, E. M. , 2008, “ A Criterion for Axial Compressor Hub-Corner Stall,” ASME J. Turbomach., 130(3), p. 031006. [CrossRef]
Opaits, D. F. , Neretti, G. , Likhanskii, A. V. , Zaidi, S. , Shneider, M. N. , Miles, R. B. , and Macheret, S. O. , 2007, “ Experimental Investigation of DBD Plasma Actuators Driven by Repetitive High Voltage Nanosecond Pulses With DC or Low-Frequency Sinusoidal Bias,” AIAA Paper No. 2007-4532.
Post, M. L. , and Corke, T. C. , 2003, “ Separation Control on High Angle of Attack Airfoil Using Plasma Actuators,” AIAA Paper No. 2003-1024.
Huang, J. , Corke, T. C. , and Thomas, F. O. , 2006, “ Unsteady Plasma Actuators for Separation Control of Low-Pressure Turbine Blades,” AIAA J., 44(7), pp. 1477–1487. [CrossRef]
List, J. , Byerley, A. R. , McLaughlin, T. F. , and VanDyken, R. D. , 2003, “ Using a Plasma Actuator to Control Laminar Separation on a Linear Cascade Turbine Blade,” AIAA Paper No. 2003-1026.
Li, Y. , Wu, Y. , Zhou, M. , Su, C. , Zhang, X. , and Zhu, J. , 2010, “ Control of the Corner Separation in a Compressor Cascade by Steady and Unsteady Plasma Aerodynamic Actuation,” Exp. Fluids, 48(6), pp. 1015–1023. [CrossRef]
Wu, Y. , Zhao, X. , Li, Y. , and Li, J. , 2012, “ Corner Separation Control in a Highly Loaded Compressor Cascade Using Plasma Aerodynamic Actuation,” ASME Paper No. GT2012-69196.
Enloe, C. L. , McLaughlin, T. E. , VanDyken, R. D. , Kachner, K. D. , Jumper, E. J. , Corke, T. C. , Post, M. , and Haddad, O. , 2004, “ Mechanisms and Responses of a Single Dielectric Barrier Plasma Actuator: Geometric Effects,” AIAA J., 42(3), pp. 595–604. [CrossRef]
Orlov, D. M. , 2006, “ Modelling and Simulation of Single Dielectric Barrier Discharge Plasma Actuators,” Ph.D. thesis, University of Notre Dame, Notre Dame, IN.
Zierke, W. C. , and Deutsch, S. , 1989, “ The Measurement of Boundary Layers on a Compressor Blade in Cascade—Part 1: Experimental Technique, Analysis and Results,” NASA Lewis Research Center, Cleveland, OH, NASA Report No. CR-185118.
Bullock, R. O. , 1965, “ Aerodynamic Design of Axial-Flow Compressors,” NASA Lewis Research Center, Cleveland, OH, NASA Report No. NASA-SP-36.
Roth, J. R. , and Dai, X. , 2006, “ Optimization of the Aerodynamic Plasma Actuator as an Electrohydrodynamic (EHD) Electrical Device,” AIAA Paper No. 2006-1203.
Thomas, F. O. , Corke, T. C. , Iqbal, M. , Kozlov, A. , and Schatzman, D. , 2009, “ Optimization of Dielectric Barrier Discharge Plasma Actuators for Active Aerodynamic Flow Control,” AIAA J., 47(9), pp. 2169–2178. [CrossRef]
Akcayoz, E. , 2012, “ Performance Increase and Noise Reduction in Axial Compressor Cascades with Plasma Actuation,” Ph.D. thesis, Ecole Polytechnique de Montreal, Montreal, QC, Canada.
Langtry, R. B. , and Menter, F. R. , 2005, “ Transition Modeling for General CFD Applications in Aeronautics,” AIAA Paper No. 2005-522.
Langtry, R. B. , Menter, F. R. , Likki, S. R. , Suzen, Y. B. , Huang, P. G. , and Völker, S. , 2006, “ A Correlation-Based Transition Model Using Local Variables—Part II: Test Cases and Industrial Applications,” ASME J. Turbomach., 128(3), pp. 423–434. [CrossRef]
Lemire, S. , and Vo, H. D. , 2011, “ Reduction of Fan and Compressor Wake Defect Using Plasma Actuation for Tonal Noise Reduction,” ASME J. Turbomach., 133(1), p. 011017. [CrossRef]
Suzen, Y. B. , Huang, P. G. , Jacob, J. D. , and Ashpis, D. E. , 2005, “ Numerical Simulations of Plasma Based Flow Control Applications,” AIAA Paper No. 2005-4633.
Palmeiro, D. , and Lavoie, P. , 2011, “ Comparative Analysis on Single Dielectric Barrier Discharge Plasma Actuator Models,” Seventh International Symposium on Turbulence and Shear Flow Phenomena (TSFP-7), Ottawa, ON, Canada, July 28–31.
Clark, J. P. , and Grover, E. A. , 2007, “ Assessing Convergence in Predictions of Periodic-Unsteady Flowfields,” ASME J. Turbomach., 129(4), pp. 740–749. [CrossRef]
Gmelin, C. , Thiele, F. , Liesner, K. , and Meyer, R. , 2011, “ Investigations of Secondary Flow Suction in a High Speed Compressor Cascade,” ASME Paper No. GT2011-46479.
Akcayoz, E. , Vo, H. D. , Mahallati, A. , and Benner, M. W. , 2013, “ Laminar Separation Control of a Highly-Loaded Compressor Cascade Using Plasma Actuation,” 21st International Symposium of Air Breathing Engines (ISABE 2013), Busan, Korea, Sept. 9–13, Paper No. ISABE-2013-1106.


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Fig. 1

Schematic representation of a plasma actuator

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Fig. 4

Schematic of the experimental setup

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Fig. 3

An isometric view of the linear cascade test section

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Fig. 2

Cascade geometry and design parameters

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Fig. 6

Plasma formation for corner stall control configuration

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Fig. 5

Plasma actuator configuration for corner stall control: (a) placement of plasma actuators, (b) layout of suction side actuator, and (c) layout of endwall actuator

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Fig. 8

Experimental and CFD results at baseline: (a) experimental oil-flow visualization and (b) predicted skin-friction contours and streamlines

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Fig. 7

Mapping of spatial body force distribution: (a) body force on plasma actuator mesh and (b) body force mapped onto the blade suction surface

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Fig. 9

Predicted skin-friction coefficient and TKE contours with no actuation

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Fig. 10

Experimental and computational pressure coefficient distributions

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Fig. 13

Predicted total pressure loss coefficient (Cp0) contours at various chordwise planes for baseline

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Fig. 14

Predicted total pressure loss coefficient (Cp0) contours at various chordwise planes with plasma actuation: (a) Fact,1, (b) Fact,2, (c) Fact,3, and (d) Fact,1 and Fact,3

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Fig. 11

Contours of total pressure loss coefficient (Cp0) at 0.4Cx downstream plane for baseline: (a) experiment and (b) CFD

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Fig. 12

Plasma actuator locations for corner separation control

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Fig. 15

Predicted overall loss coefficient (ω0) distributions in chordwise direction

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Fig. 16

Measured and predicted pressure loss contours at 0.4Cx downstream of trailing edge subject to plasma actuation: (a) baseline (experiment), (b) baseline (CFD), (c) Fact = 65 mN/m (experiment), (d) Fact = 65 mN/m (CFD), (e) change in Cp0 (experiment), and (f) Change in Cp0 (CFD)

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Fig. 17

Effect of plasma actuation on predicted total pressure loss 0.4Cx downstream of the cascade TE: (a) baseline, Fact = 0 and (b) Fact = 300 mN/m

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Fig. 18

Reynolds number scaling for endwall corner separation control with plasma actuation



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