Comparison of different plasma actuation strategies for aeroelastic control on a linear compressor cascade

Giorgi, Maria Grazia De; Motta, Valentina; Suma, Antonio; Laforì, Alessia

doi:10.1016/j.ast.2021.106902

Cited by 16 publications

(2 citation statements)

References 32 publications

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“…Due to the extremely important role of the status, extremely demanding working environment, and extremely strict performance and safety requirements, flow control for axial flow compressors, expanding their stable working range, and improving their aerodynamic performance have always been one of the hot research topics in this field. Common flow control strategies include boundary layer suction [1,2], plasma excitation [3,4], casing treatment [5][6][7], or air injection [8][9][10]. These methods either require complex external piping systems or significantly reduce the efficiency of the compressor.…”

Section: Introductionmentioning

confidence: 99%

Influence of Active Flow Control of Synthetic Jet at Suction Surface on the Performance of a Subsonic Axial Compressor Rotor

Wang,

Wu,

Liao

et al. 2024

Applied Sciences

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In order to investigate the effect of a synthetic jet arranged at the suction surface on the aerodynamic performance of an axial flow compressor, a high-speed subsonic axial flow compressor rotor was numerically simulated in this paper. The results showed that after being excited by the synthetic jet, the flow margin of the compressor decreased by 1.3%, but the peak efficiency increased by 0.47%. After analyzing the internal flow field, it was found that although the alternating blowing and suction effect of the synthetic jet can reduce the separation loss of the suction surface, the radial velocity of the flow is higher when stimulated and converges towards the blade tip, resulting in more severe blockage at the blade tip than in the prototype compressor, leading to a slight decrease in stability margin. To balance the stability margin of the compressor, a coupled flow control numerical simulation combining passive control of the casing treatment and active control of the suction surface synthetic jet was subsequently carried out. The results showed that the coupled flow control could exert their respective advantages, resulting in an increase of 17.84% in the compressor flow margin and a decrease of only 0.2% in peak efficiency.

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Section: Introductionmentioning

confidence: 99%

Influence of Active Flow Control of Synthetic Jet at Suction Surface on the Performance of a Subsonic Axial Compressor Rotor

Wang,

Wu,

Liao

et al. 2024

Applied Sciences

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“…Plasma flow control is a novel flow control method developed in recent years, which plays an important role in improving the performance of various fluid machinery [3], including controlling boundary layer [4], delaying airflow separation [5], which usually leads to the augmentation of lift and the decreasing drag, suppression of aerodynamic noise [6], aeroelastic control [7], and controlling wingtip vortex [8]. Popular plasma actuators include plasma synthetic jet actuator and dielectric barrier discharge (DBD) plasma actuator (PA) and this paper focuses on the latter.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of virtual control surfaces for lift control on NACA0015 airfoil

Fu,

Lyu,

Shi

2023

Phys. Scr.

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The plasma actuators as virtual control surfaces are assessed numerically as a means to control the lift of NACA0015 airfoil at the full angle of attack (without stall). The virtual control surface for increasing lift is realized by the pressure side (PS) plasma actuators that induce an upstream jet and the suction side (SS) plasma actuators that induce a downstream jet (SSD plasma actuator), while the one for reducing lift is realized by the SS plasma actuators that induce an upstream jet (SSU plasma actuator). Numerical simulation is achieved by solving the two-dimensional Reynolds averaged Navier-Stokes using the finite volume method. The plasma actuator adopts the empirical model proposed by the author before. The simulation of the air flow was performed for the freestream velocity of 20 m/s (Re=$1.03\times 10^6$) and the induced jet momentum coefficient between 0.0846\% and 0.9027\%. The calculation results show that the optimal number of DBD actuators for increasing the lift is related to the angle of attack. The SS flow separation of the high angle of attack greatly reduces the control effect of the PS actuator, which can be eliminated by arranging the actuators in front of the separation point. Finally, a virtual control surfaces configuration containing three groups of seven plasma actuators is obtained.

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Empirical Model of Single Dielectric Barrier Discharge Plasma Actuator for Flow Control

Lyu

Shi

et al. 2023

Lecture Notes in Electrical Engineering

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Comparison of different plasma actuation strategies for aeroelastic control on a linear compressor cascade

Cited by 16 publications

References 32 publications

Influence of Active Flow Control of Synthetic Jet at Suction Surface on the Performance of a Subsonic Axial Compressor Rotor

Influence of Active Flow Control of Synthetic Jet at Suction Surface on the Performance of a Subsonic Axial Compressor Rotor

Numerical investigation of virtual control surfaces for lift control on NACA0015 airfoil

Empirical Model of Single Dielectric Barrier Discharge Plasma Actuator for Flow Control

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