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Dielectric Barrier Discharge (DBD) Plasma Actuators for Flow Control in Turbine Engines: Simulation of Flight Conditions in the Laboratory by Density Matching

  • David E. Ashpis EMAIL logo and Douglas R. Thurman
Published/Copyright: July 31, 2018
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International Journal of Turbo & Jet-Engines
From the journal International Journal of Turbo & Jet-Engines Volume 36 Issue 2

Abstract

We address requirements for laboratory testing of AC Dielectric Barrier Discharge (AC-DBD) plasma actuators for active flow control in aviation gas turbine engines. The actuator performance depends on the gas discharge properties, which, in turn, depend on the pressure and temperature. It is technically challenging to simultaneously set test-chamber pressure and temperature to the flight conditions. We propose that the AC-DBD actuator performance depends mainly on the gas density, when considering ambient conditions effects. This enables greatly simplified testing at room temperature with only chamber pressure needing to be set to match the density at flight conditions. For turbine engines, we first constructed generic models of four engine thrust-classes; 300-, 150-, 50-passenger, and military fighter, and then calculated the densities along the engine at sea-level takeoff and altitude cruise conditions. The range of chamber pressures that covers all potential applications was found to be from 3 to 1256 kPa (0.03 to 12.4 atm), depending on engine-class, flight altitude, and actuator placement in the engine. The engine models are non-proprietary and can be used as reference data for evaluation requirements of other actuator types and for other purposes. We also provided examples for air vehicles applications up to 19,812 m (65,000 ft).

Keywords: DBD plasma; flow control; turbine-engine
PACS: (2010); 52.77.-j

Nomenclature

H, h

Altitude (m)

M

Mach number

P

Static pressure (Pa)

R

Gas constant (kg m2/s2/K)

Rey

Reynolds number

T

Static temperature (K)

V

Velocity (m/s)

X

Axial distance along the engine (m)

ρ

Density (kg/m3)

Subscripts

 

c

Conditions in chamber

∞

Freestream conditions

atm

Atmospheric conditions

Acronyms

 

DBD

Dielectric Barrier Discharge

HPC

High Pressure Compressor

HPT

High Pressure Turbine

LPC

Low Pressure Compressor

LPT

Low Pressure Turbine

PAX

Passengers

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Received: 2018-06-24
Accepted: 2018-07-12
Published Online: 2018-07-31
Published in Print: 2019-05-27

© 2019 Walter de Gruyter GmbH, Berlin/Boston

Articles in the same Issue

  1. Frontmatter
  2. Editorial
  3. Jet-Engines Revised Dictionary for the 6th-Generation-R&D in a New Era
  4. Original Research Articles
  5. Off-Design Analysis of Transonic Bypass Fan Systems Using Streamline Curvature Through-Flow Method
  7. Predicting Lean Blowout and Emissions of Aircraft Engine Combustion Chamber Based on CRN
  8. Dielectric Barrier Discharge (DBD) Plasma Actuators for Flow Control in Turbine Engines: Simulation of Flight Conditions in the Laboratory by Density Matching
  9. Application of the Proper Orthogonal Decomposition Method in Analyzing Active Separation Control With Periodic Vibration Wall
  10. Model Predictive Control and Controller Parameter Optimisation of Combustion Instabilities
  11. Quasi-One-Dimensional Modeling and Analysis of RBCC Dual-Mode Scramjet Engine
  12. Investigation on the Performance of Forward Bending Fan
https://doi.org/10.1515/tjj-2018-0021
Keywords for this article
DBD plasma; flow control; turbine-engine

Articles in the same Issue

  1. Frontmatter
  2. Editorial
  3. Jet-Engines Revised Dictionary for the 6th-Generation-R&D in a New Era
  4. Original Research Articles
  5. Off-Design Analysis of Transonic Bypass Fan Systems Using Streamline Curvature Through-Flow Method
  7. Predicting Lean Blowout and Emissions of Aircraft Engine Combustion Chamber Based on CRN
  8. Dielectric Barrier Discharge (DBD) Plasma Actuators for Flow Control in Turbine Engines: Simulation of Flight Conditions in the Laboratory by Density Matching
  9. Application of the Proper Orthogonal Decomposition Method in Analyzing Active Separation Control With Periodic Vibration Wall
  10. Model Predictive Control and Controller Parameter Optimisation of Combustion Instabilities
  11. Quasi-One-Dimensional Modeling and Analysis of RBCC Dual-Mode Scramjet Engine
  12. Investigation on the Performance of Forward Bending Fan
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