Plasma Actuators for Separation Control of Low-Pressure Turbine Blades

By Junhui Huang, Thomas C. Corke, F. Thomas. 2006

389 citations recorded by the source corpus.

Subfields: Aerospace Engineering, Computational Mechanics

View Paper: https://www.semanticscholar.org/paper/4601411f81a432042f28e7ae1693b0143cb1300e

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In Aerospace Engineering

In Computational Mechanics

Citations in the corpus

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 ”
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.”
Simulations of Flow Separation Control using Plasma Actuators (2006, positive): “The effectiveness of plasma actuators in controlling flow separation has been demonstrated by several researchers [1-9].”
Measurement of the body force field of plasma actuators (2011, methodology): “Plasma actuators have been used in several studies aiming at separation control [1], turbulent drag reduction [2], boundary layer control [3, 4, 5], noise reduction [6] and laminar-turbulent transition delay [7].”
High-lift airfoil trailing edge separation control using a single dielectric barrier discharge plasma actuator (2010, background): “…with voice coils or piezo-ceramic disks, the exact location at which the plasma actuator accomplishes control is not immediately obvious, but actuators placed at or slightly upstream of the separation location give favorable results (Huang et al. 2006; Sosa et al. 2007; Jolibois et al. 2008).”
Single dielectric barrier discharge plasma enhanced aerodynamics: physics, modeling and applications (2009, methodology): “A partial list of these includes exciting boundary layer instabilities on a sharp cone at Mach 3.5 (Kosinov et al. 1990; Corke et al. 2001; Matlis 2004), lift augmentation on a wing section (Corke et al. 2002, 2006b; Nelson et al. 2006a; Patel et al. 2006; Goeksel et al. 2006, Goeksel and Rechenberg”
Plasma Flaps and Slats: An Application of Weakly Ionized Plasma Actuators (2004, methodology): “Other recent experiments have used SDBD plasma actuators for separation control in turbine-blade simulations [17–20].”