DBD Plasma Actuators for Flow Control in Air Vehicles and Jet Engines-Simulation of Flight Conditions in Test Chambers by Density Matching

Ashpis, David E.; Thurman, Douglas R.

doi:10.2514/6.2011-3730

Cited by 4 publications

(1 citation statement)

References 24 publications

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“…However, actual gas turbine compressors and turbines operate under varying pressure conditions. Ashpis and Thurman [37] suggested that the pressure range where a PA might be used in gas turbine engines is 0.03-12.4 atm (3040-1,260,000 Pa). For low-pressure ranges, Benard et al [38] investigated the effect of the air pressure level on the PA-induced velocity from 1 to 0.2 atm (20,300 Pa).…”

Section: Linear Turbine Cascade (Ltc)mentioning

confidence: 99%

Effect of Plasma Actuator Layout on the Passage Vortex Reduction in a Linear Turbine Cascade for a Wide Range of Reynolds Numbers

Matsunuma,

Segawa

2023

Actuators

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This study examined how various plasma actuator (PA) configurations affect the passage vortex (PV) reduction in a linear turbine cascade (LTC) utilizing dielectric barrier discharge PAs. The experiments were carried out under three specific layout conditions: axial placement of the PA, slanted placement at the blade inlet, and slanted placement inside the blade. Particle image velocimetry was employed to measure the velocity distribution of the secondary flow at the LTC exit, followed by an analysis of the streamline patterns, turbulence intensity distribution, and vorticity distribution. At a Reynolds number of 3.7 × 104, the PA with an oblique orientation at the blade inlet provided the most effective PV suppression. The average value of the secondary flow velocity and the peak vorticity value at the LTC exit decreased by 59.0% and 68.8%, respectively, compared to the no-control case. Furthermore, the wind tunnel blower’s rotation speed was modified, adjustments were made to the LTC’s mainstream velocity, and the Reynolds number transitioned from 1.0 × 104 to 9.9 × 104, approximately 10 times. When the slanted PA was used at the blade inlet, the PV suppression effect was the highest. The peak vorticity value owing to the PV at the LTC exit decreased by 62.9% at the lowest Reynolds number of 1.0 × 104. The Reynolds number increased with a higher mainstream velocity and decreased flow induced by the PA, consequently reducing the PV suppression effect. However, the drive of the PA was effective even under the most severe conditions (9.9 × 104), and the peak vorticity value was reduced by 20.2%.

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Section: Linear Turbine Cascade (Ltc)mentioning

confidence: 99%

Effect of Plasma Actuator Layout on the Passage Vortex Reduction in a Linear Turbine Cascade for a Wide Range of Reynolds Numbers

Matsunuma,

Segawa

2023

Actuators

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A Nanosecond Surface Dielectric Barrier Discharge Operating Under Altitude Conditions for Aeronautics Applications

Bénard

Bayoda

Ndong

et al. 2016

IEEE Trans. Plasma Sci.

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Towards In-Flight Applications? A Review on Dielectric Barrier Discharge-Based Boundary-Layer Control

Kriegseis

Simon

Grundmann

2016

Applied Mechanics Reviews

152

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Active control of laminar boundary layers with dielectric barrier discharge (DBD) plasma actuators (PAs) has made considerable progress in the last 15 years. First pioneering experiments have motivated numerous researchers to gain a deeper insight into the underlying working principles and corresponding quantification of the actuator performance. These investigations clearly show the strengths but also the weaknesses of the PA as a flow control device. Presently, the boundary-layer control (BLC) with PAs experiences the transition from lab studies to real flight applications. However, the PA community still struggles with the poor fluid mechanic efficiency and the limited momentum flux of the actuator. This review therefore addresses the question how applicable the actuator is as an energy efficient flow control device for future in-flight applications. Since any successful flow control requires detailed knowledge of the actuator’s control authority, this discussion is built upon a careful and comprehensive summary of performance evaluation measures and the interplay with various changes of thermodynamic and kinematic environmental conditions. Consequently, this review for the first time provides a comprehensive discussion of all required steps for successful DBD-based in-flight flow control spanning from the power supply to the achieved flow-control success in one coherent document.

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DBD Plasma Actuators for Flow Control in Air Vehicles and Jet Engines-Simulation of Flight Conditions in Test Chambers by Density Matching

Cited by 4 publications

References 24 publications

Effect of Plasma Actuator Layout on the Passage Vortex Reduction in a Linear Turbine Cascade for a Wide Range of Reynolds Numbers

Effect of Plasma Actuator Layout on the Passage Vortex Reduction in a Linear Turbine Cascade for a Wide Range of Reynolds Numbers

A Nanosecond Surface Dielectric Barrier Discharge Operating Under Altitude Conditions for Aeronautics Applications

Towards In-Flight Applications? A Review on Dielectric Barrier Discharge-Based Boundary-Layer Control

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