Rotor performance enhancement by alternating current dielectric barrier discharge plasma actuation

Zhao, Guiping; Wang, Chang; Yang, Yongdong; Li, Guoqiang; Shi, Zhe-Yu

doi:10.1088/2058-6272/ac803a

Cited by 1 publication

(2 citation statements)

References 15 publications

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“…Active mechanical methods, such as trailing-edge flaps and variable-droop leading edges, often cause significant changes to the center of gravity and load, while frequently requiring intricate mechanical elements and control systems. In this research, we employ pulse-modulated dielectric barrier discharge (DBD) plasma actuators, ideally suited to rotor application due to their lightweight and high-frequency bandwidth [15][16][17][18][19]. In the past, DBD plasma actuators have been employed to attenuate the tonal noise from cavities [20,21], to reduce slat aerodynamic noise [22], and to control flow noise generated by cylinders [23][24][25].…”

Section: Introductionmentioning

confidence: 99%

“…First, the collective angle of the blades is increased into the post-stall regime to achieve the maximum baseline thrust (but not Figure of Merit). Second, pulsed DBD plasma actuation is applied to attach the boundary layer and perfrom a simultaneous increase in thrust and decrease in rotor torque [17,19]. Third, the rotational speed is decreased to recover the original baseline thrust.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Noise Reduction on a Model Helicopter Rotor using DBD Plasma Actuators

Polonsky¹,

Stalnov²,

Greenblatt³

2022

Preprint

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Noise reduction was achieved on a model helicopter rotor using pulsed dielectric barrier discharge (DBD) plasma actuators mounted at the blades' leading edges. The rotor was mounted on a bi-axial balance in an anechoic chamber, and the following three-point noise-reduction strategy was adopted: first, the blades' collective (geometric) angle was increased into the post-stall regime to achieve maximum baseline thrust; second, actuation was applied, increasing thrust and decreasing torque; third, the rotational speed was decreased to recover the original baseline thrust. This strategy resulted in an increase in the maximum Figure of Merit and a decrease in broadband and tonal noise components. Broadband and loading noise reduction, up to 3 dB, was due to boundary layer attachment, resulting in smaller and weaker turbulent eddies in the wake and the tip-vortex and, therefore, more minor turbulent surface pressure fluctuations. Noise reduction directivity associated with the blade passing frequency of up to 3 dB was consistent with Lowson's theory. Surprisingly, at most of the observer angles, both the plasma pulsation and ionization frequencies were not visible in the spectra. This directional acoustic signature was assumed to be due to the geometric mounting of the actuator and its effect on the boundary layer.

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