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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Fig. 1

Schematic representation of a plasma actuator

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Fig. 2

Cascade geometry and design parameters

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Fig. 3

An isometric view of the linear cascade test section

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Fig. 4

Schematic of the experimental setup

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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. 6

Plasma formation for corner stall control configuration

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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. 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. 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. 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. 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. 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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