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Research Papers

Control of Tip-Clearance Flow in a Low Speed Axial Compressor Rotor With Plasma Actuation

[+] Author and Article Information
Giridhar Jothiprasad1

 GE Global Research, Niskayuna, NY 12309jothipra@research.ge.com

Robert C. Murray, Katherine Essenhigh, Grover A. Bennett, Seyed Saddoughi

 GE Global Research, Niskayuna, NY 12309

Aspi Wadia, Andrew Breeze-Stringfellow

 GE Aviation, West Chester, OH 45069

1

Corresponding author.

J. Turbomach 134(2), 021019 (Jun 29, 2011) (9 pages) doi:10.1115/1.4003083 History: Received July 12, 2010; Revised August 22, 2010; Published June 29, 2011; Online June 29, 2011

This research investigates different dielectric barrier discharge (DBD) actuator configurations for affecting tip leakage flow and suppressing stall inception. Computational investigations were performed on a low speed rotor with a highly loaded tip region that was responsible for stall-onset. The actuator was mounted on the casing upstream of the rotor leading edge. Plasma injection had a significant impact on the predicted tip-gap flow and improved stall margin. The effect of changing the actuator forcing direction on stall margin was also studied. The reduction in stalling flow was closely correlated with a reduction in loading parameter that quantifies mechanisms responsible for end-wall blockage generation. The actuation reduced end-wall losses by increasing the static pressure of tip-gap flow emerging from blade suction-side. Lastly, an approximate speed scaling developed for the DBD force helped estimate force requirements for stall margin enhancement of transonic rotors.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Radial variation in normalized rotor exit pressures. Total pressure at midspan used for normalization.

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Figure 2

DBD actuator configuration for axial downstream force. (a) Circumferential electrodes (in brown) are axially offset. (b) Forcing region and direction in blue.

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Figure 3

Total pressure-rise coefficient as a function of flow coefficient for downstream axial force of 0.26 N/m in low speed rotor. Stalled operating points (from CFD) not connected by lines. Coefficients normalized by values at baseline stall flow.

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Figure 4

Contours of nondimensional relative total pressure loss with and without actuation. Comparison at baseline stall flow. Red denotes region of high loss. Actuation reduces loss by tip leakage flow.

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Figure 5

DBD actuator configuration for circumferential force. (a) Axial electrodes (in brown) are circumferentially offset. (b) Circumferential force in direction of blade rotation. (c) Circumferential force opposite to the direction of blade rotation. Forcing region and direction in blue.

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Figure 6

Spanwise variation of rotor inlet velocity in the blade-tip region of low speed rotor. Comparison at baseline stall flow. Velocities normalized by blade-tip speed.

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Figure 7

Effect of varying forcing angles on total pressure-rise characteristic of low speed rotor. 0.26 N/m of force applied. Stalled operating points (from CFD) not connected by lines. Coefficients normalized by values at baseline stall flow.

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Figure 8

Spanwise variation in rotor incidence angles in the blade-tip region of low speed rotor. Comparison at baseline stall flow.

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Figure 9

Spanwise variation in diffusion factor in the blade-tip region of low speed rotor. Comparison of DBD configurations at baseline stall flow. Favorable configurations unload blade-tip region.

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Figure 10

Spanwise variation in static-pressure-rise coefficient in the blade-tip region of low speed rotor. Comparison of DBD configurations at baseline stall. Static pressure rise across the blade is normalized by inlet relative velocity.

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Figure 11

Blocked region (in red) at exit plane of low speed rotor. Exit blockage due to wakes and tip vortex. Area-averages over end-wall blocked region is limited to 10% span near casing.

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Figure 12

Reduction in stalling flow Δϕst with loading parameter CPS−CPT at baseline stall flow. Different forcing angles and force/unit length are shown.

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Figure 13

Variation in radially averaged relative total pressure at the tip gap with axial distance. Total pressure nondimensionalized as: (⟨PTexit⟩r,m−PTref,1/PTref,1−PSref,1).

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Figure 14

Reduction in stalling flow Δϕst with (a) modified loading parameter CPS′−CPT′ at the baseline stall flow. (b) Static-pressure-rise CPS′ of tip flow. Different forcing angles and force/unit length are shown.

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Figure 15

Total pressure-rise coefficient as a function of flow coefficient for two levels of axial forcing in the transonic NASA rotor 37. Stalled operating points not connected by lines.

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