Research Papers

Reduction of Fan and Compressor Wake Defect Using Plasma Actuation for Tonal Noise Reduction

[+] Author and Article Information
Sébastien Lemire, Huu Duc Vo

Department of Mechanical Engineering, École Polytechnique de Montréal, Montreal, QC H3T 1J4, Canada

J. Turbomach 133(1), 011017 (Sep 22, 2010) (11 pages) doi:10.1115/1.4000540 History: Received June 20, 2009; Revised July 18, 2009; Published September 22, 2010; Online September 22, 2010

This paper proposes a new technique to reduce the noise generated by rotor-stator interaction (tonal noise) in fans and compressors. The method involves the use of single dielectric barrier discharge (plasma) actuators near the blade trailing edge to reduce blade wakes. Plasma actuators are a new and simple type of active flow control device consisting of two parallel and offset electrodes separated by a layer of dielectric material. The application of a high ac voltage at high frequency to the electrodes generates a body force on the flow in the vicinity of the electrodes to inject momentum without mass addition. A preliminary assessment of the proposed concept is performed with a computational study on modern low-speed compressor rotor geometry. A plasma actuator model is implemented in an established turbomachinery CFD code. Simulations are carried out to evaluate the effect of the actuator strength, location, and actuation method (continuous versus pulsed) on the rotor wake. Results show that plasma actuators operated in continuous mode near the trailing edge can significantly influence the wake of the rotor with relatively little power consumption. The effectiveness of the actuation is proportional to actuator strength (induced body force). The exact position of the actuator in the trailing edge region has little effect on the effectiveness of the actuation. The results from simulations with pulsed actuation show very low time-averaged influence on the wake and are not fully conclusive, due possibly to the frequencies simulated and the limitations of the RANS CFD tool.

Copyright © 2011 by American Society of Mechanical Engineers
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Figure 1

Upwash velocity from wake

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Figure 2

SDBD (plasma) actuator

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Figure 3

SDBD actuator position

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Figure 4

Summary of equations and boundary conditions for the hybrid model: Eq. 1 (solid box) and Eq. 2 (dashed box)

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Figure 5

Subdivision of the domain over the covered electrode into N volumes

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Figure 6

Time average spatial distribution of the force generated by plasma actuator from hybrid model

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Figure 7

Mapping of actuator mesh onto blade surface

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Figure 8

Mesh superposition

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Figure 9

Wake assessment location

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Figure 10

Velocity profile for the cases in Table 1

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Figure 11

Influence of continuous actuation force on momentum thickness

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Figure 12

Harmonic amplitude for the continuous actuation cases (first five harmonics)

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Figure 13

Analysis of the velocity profiles and momentum thickness at several times in the duty-cycle for case 7

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Figure 14

Wake modification for tip Mach number at 0.4 and the actuator strength at 3.6 N/m




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