Effects of Pulsed-D.C. Discharge Plasma Actuators in a Separated Low Pressure Turbine Boundary Layer (Postprint)
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 2007
- Accession Number
- ADA482200
Entities
People
- I. C. Boxx
- J. D. Wall
- M. E. Franke
- R. B. Rivir
Organizations
- Air Force Institute of Technology