Control of leading edge separation on airfoil using DBD plasma actuator with signal amplitude modulation

A wind tunnel study is conducted toward hybrid flow control of a full scale transport truck side mirror at ReD=3.2×105. A slim guide vane is employed for redirecting high-momentum flow toward the mirror wake region. Leading edge separation from the guide vane is reduced or eliminated by means of an alternating current -dielectric barrier discharge (AC-DBD) plasma actuator. Particle image velocimetry (PIV) measurements are performed at a range of velocities from 15 to 25 m/s and from windward to leeward angles from -5deg to 5deg. Time-averaged velocity fields are obtained at the center of the mirror for three scenarios: (a) reference case lacking any control elements, (b) guide vane only, and (c) combination of the guide vane and the AC-DBD plasma actuator. The comparison of cases demonstrates that at 25 m/s windward conditions (-5deg) the guide vane is capable of recovering 17% momentum with respect to the reference case. No significant change is observed by activating the AC-DBD plasma actuator. In contrast, at leeward conditions (5deg), the guide vane results in a −20% momentum loss that is rectified to a 6% recovery with actuation. The above implies that for a truck with two mirrors, 23% of momentum may be recovered.

Download Full-text

Control of leading edge separation on airfoil using DBD plasma actuator

Journal of Fluid Science and Technology ◽

10.1299/jfst.2014jfst0049 ◽

2014 ◽

Vol 9 (3) ◽

pp. JFST0049-JFST0049 ◽

Cited By ~ 3

Author(s):

Nazri MD DAUD ◽

Yasuaki KOZATO ◽

Satoshi KIKUCHI ◽

Shigeki IMAO

Keyword(s):

Leading Edge ◽

Plasma Actuator ◽

Dbd Plasma ◽

Edge Separation

Download Full-text

105 Flow Control of Around Airfoil Using DBD Plasma Actuator : Effect of Signal Amplitude Modulation

The Proceedings of Conference of Tokai Branch ◽

10.1299/jsmetokai.2015.64._105-1_ ◽

2015 ◽

Vol 2015.64 (0) ◽

pp. _105-1_-_105-2_

Author(s):

Kazuma YUMIKURA ◽

Yasuaki KOZATO ◽

Satoshi KIKUCHI ◽

Shigeki IMAO

Keyword(s):

Flow Control ◽

Amplitude Modulation ◽

Signal Amplitude ◽

Plasma Actuator ◽

Dbd Plasma

Download Full-text

Flow control of leading edge separation using DBD plasma actuator

Transactions of the JSME (in Japanese) ◽

10.1299/transjsme.2014fe0118 ◽

2014 ◽

Vol 80 (813) ◽

pp. FE0118-FE0118 ◽

Cited By ~ 2

Author(s):

Yasuaki KOZATO ◽

Yuta HIROSE ◽

Satoshi KIKUCHI ◽

Shigeki IMAO

Keyword(s):

Flow Control ◽

Leading Edge ◽

Plasma Actuator ◽

Dbd Plasma ◽

Edge Separation

Download Full-text

1107 CONTROL OF LEADING EDGE SEPARATION ON AIRFOIL USING DBD PLASMA ACTUATOR

The Proceedings of the International Conference on Jets Wakes and Separated Flows (ICJWSF) ◽

10.1299/jsmeicjwsf.2013.4._1107-1_ ◽

2013 ◽

Vol 2013.4 (0) ◽

pp. _1107-1_-_1107-6_ ◽

Cited By ~ 1

Author(s):

DAUD N. MD ◽

HIROSE Yuta ◽

KUNIEDA Takahito ◽

KOZATO Yasuaki ◽

KIKUCHI Satoshi ◽

...

Keyword(s):

Leading Edge ◽

Plasma Actuator ◽

Dbd Plasma ◽

Edge Separation

Download Full-text

Experimental Study of Separation Control Over a Wide Range of Reynolds Numbers Using Dielectric Barrier Discharge Plasma Actuator on Airfoil

Volume 1C, Symposia: Gas-Liquid Two-Phase Flows; Gas and Liquid-Solid Two-Phase Flows; Numerical Methods for Multiphase Flow; Turbulent Flows: Issues and Perspectives; Flow Applications in Aerospace; Fluid Power; Bio-Inspired Fluid Mechanics; Flow Manipulation and Active Control; Fundamental Issues and Perspectives in Fluid Mechanics; Transport Phenomena in Energy Conversion From Clean and Sustainable Resources; Transport Phenomena in Materials Processing and Manufacturing Processes ◽

10.1115/fedsm2017-69226 ◽

2017 ◽

Author(s):

Satoshi Sekimoto ◽

Kozo Fujii ◽

Masayuki Anyoji ◽

Yuma Miyakawa ◽

Shinichiro Ito ◽

...

Keyword(s):

Dielectric Barrier Discharge ◽

Barrier Discharge ◽

Leading Edge ◽

Reynolds Numbers ◽

Plasma Actuator ◽

Chord Length ◽

Separation Control ◽

Dielectric Barrier ◽

Wide Range ◽

Edge Separation

This study proposes separation control investigation using a Dielectric Barrier Discharge (DBD) plasma actuator on a NACA0015 airfoil over a wide range of Reynolds numbers. The airfoil was a two dimensional NACA0015 wing model with chord length of 200mm. Reynolds numbers based on the chord length were ranged from 252,000 to 1,008,000. A plasma actuator was installed at the leading edge and driven with AC voltage. Burst mode (duty cycle) actuations, in which nondimensional burst frequency F+ was ranged in 0.1–30, were applied. Time-averaged pressure measurements were conducted with angles of attack from 14deg to 22deg. The results show that initial flow fields without an actuation can be classified into three types; 1) leading edge separation, 2) trailing edge separation, and 3) hysteresis condition between 1) and 2), and the effect of burst actuation is different for each above initial condition.

Download Full-text

Delay of Rotating Stall in Compressors Using Plasma Actuators

Journal of Turbomachinery ◽

10.1115/1.4032840 ◽

2016 ◽

Vol 138 (9) ◽

Cited By ~ 8

Author(s):

Farzad Ashrafi ◽

Mathias Michaud ◽

Huu Duc Vo

Keyword(s):

Centrifugal Compressor ◽

Leading Edge ◽

Plasma Actuator ◽

Rotating Stall ◽

Tip Clearance ◽

Compressor Stage ◽

Dbd Plasma ◽

Two Stage ◽

Stall Inception ◽

Flow Acceleration

Rotating stall is a well-known aerodynamic instability in compressors that limits the operating envelope of aircraft gas turbine engines. An innovative method for delaying the most common form of rotating stall inception using an annular dielectric barrier discharge (DBD) plasma actuator had been proposed. A DBD plasma actuator is a simple solid-state device that converts electricity directly into flow acceleration through partial air ionization. However, the proposed concept had only been preliminarily evaluated with numerical simulations on an isolated axial rotor using a relatively basic CFD code. This paper provides both an experimental and a numerical assessment of this concept for an axial compressor stage as well as a centrifugal compressor stage, with both stages being part of a low-speed two-stage axial-centrifugal compressor test rig. The two configurations studied are the two-stage configuration with a 100 mN/m annular casing plasma actuator placed just upstream of the axial rotor leading edge (LE) and the single-stage centrifugal compressor with the same actuator placed upstream of the impeller LE. The tested configurations were simulated with a commercial RANS CFD code (ansys cfx) in which was implemented the latest engineering DBD plasma model and dynamic throttle boundary condition, using single-passage multiple blade row computational domains. The computational fluid dynamics (CFD) simulations indicate that in both types of compressors, the actuator delays the stall inception by pushing the incoming/tip clearance flow interface downstream into the blade passage. In each case, the predicted reduction in stalling mass flow matches the experimental value reasonably well.

Download Full-text

Delay of Rotating Stall in Compressors Using Plasma Actuators

Volume 2C: Turbomachinery ◽

10.1115/gt2015-42559 ◽

2015 ◽

Cited By ~ 2

Author(s):

Farzad Ashrafi ◽

Mathias Michaud ◽

Huu Duc Vo

Keyword(s):

Centrifugal Compressor ◽

Leading Edge ◽

Plasma Actuator ◽

Rotating Stall ◽

Tip Clearance ◽

Compressor Stage ◽

Dbd Plasma ◽

Two Stage ◽

Stall Inception ◽

Flow Acceleration

Rotating stall is a well-known aerodynamic instability in compressors that limits the operating envelope of aircraft gas turbine engines. An innovative method for delaying the most common form of rotating stall inception using an annular DBD (Dielectric Barrier Discharge) plasma actuator had been proposed. A DBD plasma actuator is a simple solid-state device that converts electricity directly into flow acceleration through partial air ionization. However, the proposed concept had only been preliminarily evaluated with numerical simulations on an isolated axial rotor using a relatively basic CFD code. This paper provides both an experimental and a numerical assessment of this concept for an axial compressor stage as well as a centrifugal compressor stage, with both stages being part of a low-speed two-stage axial-centrifugal compressor test rig. The two configurations studied are the two-stage configuration with a 100 mN/m annular casing plasma actuator placed just upstream of the axial rotor leading edge, and the single-stage centrifugal compressor with the same actuator placed upstream of the impeller leading edge. The tested configurations were simulated with a commercial RANS CFD code (ANSYS CFX) in which was implemented the latest engineering DBD plasma model and dynamic throttle boundary condition, using single-passage multiple blade row computational domains. The CFD simulations indicate that in both types of compressors the actuator delays the stall inception by pushing the incoming/tip clearance flow interface downstream into the blade passage. In each case, the predicted reduction in stalling mass flow matches the experimental value reasonably well.

Download Full-text