Effects of Pulsed-D.C. Discharge Plasma Actuators in a Separated Low Pressure Turbine Boundary Layer (Postprint)
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
Pagination or Media Count:
A pulsed DC dielectric barrier discharge plasma actuator is investigated to reattach the simulated separated flow of a highly loaded turbine blade suction surface. Pulse rates of 25, 50, 75, and 100 pulses per second were investigated at a nominal constant pulse power of 8.5 kW for a constant pulse width of 250 ns. The separation of the flat plate boundary layer is induced with an adverse free stream pressure gradient distribution from an upper wall. Phase-locked particle image velocimetry PIV was used to obtain two-dimensional velocity field measurements at 6 to 24 equally spaced phase-angles, depending on the pulse rate. At a pulse rate of 100 pulses per second the 70 velocity contour in the boundary layer was moved closer to the wall by 39, compared to the unforced case, 15 mm downstream of the actuator.
- Machinery and Tools
- Test Facilities, Equipment and Methods
- Fluid Mechanics
- Plasma Physics and Magnetohydrodynamics