A Novel Plasma-Based Compressor Stall Control System
National Aeronautics and Space Administration
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NH, Hanover, NH, 03755-3116
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AbstractModern aircraft gas turbine engines utilize highly loaded airfoils in both the compressor and turbine to maximize performance while minimizing weight, cost, and complexity. However, high airfoil loading increases the likelihood of flow separation at lower mass flow rates. Dielectric Barrier Discharge (DBD) plasma actuators have been shown to be a very promising technique for compressor stall control. DBD devices can either be installed directly on rotor/stator surfaces or the compressor end walls to control rotor tip flow. A fundamental challenge in driving DBD actuators is providing appropriate electrical waveforms to the devices. Creare proposes the development of an innovative DBD actuator charging circuit topology which enables (1) low voltage DC power distribution, (2) a modular approach to achieving total power delivery, (3) use of commercial-off-the-shelf (COTS) components, and (4) resolution of impedance matching issues associated with other DBD charging circuit topologies.
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