Unsteady Plasma Actuators for Separation Control of Low-Pressure Turbine Blades
By Junhui Huang, Thomas C. Corke, F. Thomas. 2006
179 citations recorded by the source corpus.
Subfields: Aerospace Engineering, Computational Mechanics
View Paper: https://www.semanticscholar.org/paper/224ee92f120bdce1b235dac66913efa31ea60ea1
How researchers see this paper
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In Aerospace Engineering
In Computational Mechanics
- Thomas C. Corke
- Martiqua L. Post
- D. Orlov
- A. Kozlov
- F. Thomas
- M. O. Iqbal
- D. Schatzman
- Mehul P. Patel
Citations in the corpus
- Single dielectric barrier discharge plasma enhanced aerodynamics: physics, modeling and applications (2009, background): “,[38] for laminar boundary layer separation verified that there was an optimum frequency corresponding to a dimensionless frequency, F = fLsep/Uo = 1, that would produce the maximum pressure recovery.”
- Plasma Actuators for Cylinder Flow Control and Noise Reduction (2008, background): “[13,14] found unsteady actuation at St 1 optimum for separation control on a low-pressure turbine blade.”
- Optimization of Dielectric Barrier Discharge Plasma Actuators for Active Aerodynamic Flow Control (2009, background): “The diverse applications are too numerous to list here but include, for example, active airfoil leading edge separation control [1,2], control of airfoil dynamic stall [3], bluff body flow control [4–8], boundary layer flow control [9–11], highlift applications [12], and turbomachinery flow control ”