Numerical Simulation of Combustion Enhancement Through a Repetitive Pulsed Plasma Actuator

2016 ◽  
Vol 30 (1) ◽  
pp. 219-225 ◽  
Author(s):  
Chin-Cheng Wang
Keyword(s):  
Numerical Simulation ◽  
Plasma Actuator ◽  
Pulsed Plasma ◽  
Combustion Enhancement

Turbine Cascade Flow Control Using a “Wake Filling” Pulsed Plasma Actuator

2005 ◽  
Author(s):  
H. Perez-Blanco ◽  
Robert Van Dyken ◽  
Aaron Byerley ◽  
Tom McLaughlin
Keyword(s):  
Boundary Layer ◽  
Pressure Gradient ◽  
Laminar Boundary Layer ◽  
Separation Bubble ◽  
Adverse Pressure Gradient ◽  
Suction Side ◽  
Plasma Actuator ◽  
Pulsed Plasma ◽  
Power Cost ◽  
Hot Film

Separation bubbles in high-camber blades under part-load conditions have been addressed via continuous and pulsed jets, and also via plasma actuators. Numerous passive techniques have been employed as well. In this type of blades, the laminar boundary layer cannot overcome the adverse pressure gradient arising along the suction side, resulting on a separation bubble. When separation is abated, a common explanation is that kinetic energy added to the laminar boundary layer speeds up its transition to turbulent. In the present study, a plasma actuator installed in the trailing edge (i.e. “wake filling configuration”) of a cascade blade is used to excite the flow in pulsed and continuous ways. The pulsed excitation can be directed to the frequencies of the large coherent structures (LCS) of the flow, as obtained via a hot-film anemometer, or to much higher frequencies present in the suction-side boundary layer, as given in the literature. It is found that pulsed frequencies much higher than that of LCS reduce losses and improve turning angles further than frequencies close to those of LCS. With the plasma actuator 50% on time, good loss abatement is obtained. Larger “on time” values yield improvements, but with decreasing returns. Continuous high-frequency activation results in the largest loss reduction, at increased power cost. The effectiveness of high frequencies may be due to separation abatement via boundary layer excitation into transition, or may simply be due to the creation of a favorable pressure gradient that averts separation as the actuator ejects fluid downstream. Both possibilities are discussed in light of the experimental evidence.

scholarly journals S052042 Optimal design for the drive conditions of pulsed plasma actuator for separation control

2013 ◽  
Vol 2013 (0) ◽  
pp. _S052042-1-_S052042-5
Author(s):  
Kengo MAEDA ◽  
Kenichi HARUNA ◽  
Takashi MATSUNO ◽  
Masahiro KANAZAKI
Keyword(s):  
Optimal Design ◽  
Plasma Actuator ◽  
Separation Control ◽  
Pulsed Plasma

1197 ON THE MECHANISM OF BLUFF BODY FLOW CONTROL BY PULSED PLASMA ACTUATOR

2013 ◽  
Vol 2013.4 (0) ◽  
pp. _1197-1_-_1197-6_
Author(s):  
Matsuno Takashi ◽  
Maeda Kengo ◽  
Fujita Noboru ◽  
Haruna Kenichi ◽  
Baba Teruaki ◽  
...  
Keyword(s):  
Flow Control ◽  
Bluff Body ◽  
Plasma Actuator ◽  
Pulsed Plasma ◽  
Bluff Body Flow

Study of the combustion enhancement using a coaxial DBD plasma actuator

2017 ◽  
Vol 2017.23 (0) ◽  
pp. 404
Author(s):  
Hiroshi TSUCHIDA ◽  
Yousuke SHIKINAMI ◽  
Tatsuro HORI ◽  
Masaki MAEKAWA ◽  
Motoaki KIMURA
Keyword(s):  
Plasma Actuator ◽  
Dbd Plasma ◽  
Combustion Enhancement

On the boundary flow using pulsed nanosecond DBD plasma actuators

2018 ◽  
Vol 32 (12n13) ◽  
pp. 1840035
Author(s):  
Zi-Jie Zhao ◽  
Y. D. Cui ◽  
Jiun-Ming Li ◽  
Jian-Guo Zheng ◽  
B. C. Khoo
Keyword(s):  
Flat Plate ◽  
Stable State ◽  
Single Pulse ◽  
Plasma Actuator ◽  
Plasma Actuators ◽  
Pulsed Plasma ◽  
Dbd Plasma ◽  
Narrow Region ◽  
Layer Flow ◽  
Induced Velocity

Our previous studies in quiescent air environment [Z. J. Zhao et al., AIAA J. 53(5) (2015) 1336; J. G. Zheng et al., Phys. Fluids 26(3) (2014) 036102] reveal experimentally and numerically that the shock wave generated by the nanosecond pulsed plasma is fundamentally a microblast wave. The shock-induced burst perturbations (overpressure and induced velocity) are found to be restricted to a very narrow region (about 1 mm) behind the shock front and last only for a few microseconds. These results indicate that the pulsed nanosecond dielectric barrier discharge (DBD) plasma actuator has stronger local effects in time and spatial domain. In this paper, we further investigate the effects of pulsed plasma on the boundary layer flow over a flat plate. The present investigation reveals that the nanosecond pulsed plasma actuator generates intense perturbations and tends to promote the laminar boundary over a flat plate to turbulent flow. The heat effect after the pulsed plasma discharge was observed in the external flow, lasting a few milliseconds for a single pulse and reaching a quasi-stable state for multi-pulses.

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