Active Flow Control for Passage Vortex Reduction in a Linear Turbine Cascade with Various Tip Clearance Sizes Using a Dielectric Barrier Discharge Plasma Actuator

In an axial-flow turbine of a jet engine used for aircraft propulsion, the passage vortex (PV) and tip leakage (TLV) generated inside blade deteriorate aerodynamic performance. this study, dielectric barrier discharge plasma actuator (PA) was installed in upstream endwall cascade to suppress PV. The effects presence or absence clearance change size on structure at exit were observed by recording flow velocity distributions using particle image velocimetry. clearance, only PV existed completely suppressed PA. By contrast, TLV occurred addition When input voltage PA varied with various sizes, fields where interfered clarified. With as increased; however, increased considerably. At each size, changes center positions varying voltages increasing PA, position moved pressure surface side adjacent blade, toward middle passage. larger amount movement both increased.