Abstract
The aim of this study is to investigate the performance of dielectric barrier discharge plasma actuators (DBD-PAs) applied to control the aeroelastic response of a compressor cascade in subsonic flow conditions. Simulations involve a cascade composed by 7-blade, 3 of which show a not-synchronous pitching behaviour. Two different inter blade phase angle (IBPA) have been tested and compared. Actuators capabilities in terms of load alleviation and instability control have been evaluated through the measurement of mean value, standard deviation and hysteresis area of the airfoil response in terms of lift and moment coefficients.
Highlights
Aeroelastic phenomena have been long investigated, since they represent severe issues for structural integrity of many aerospace applications [1]
Transient simulations of the compressor cascade equipped with DBD plasma actuators involve a subsonic flow with a freestream Mach number M = 0.057 and inlet velocity set to U∞=19.65 m/s, which gives a Reynolds number Re=200000
Numerical analyses were conducted to study the applicability of using plasma actuators to modify the local flow around the trailing edge of the compressor blades
Summary
Aeroelastic phenomena have been long investigated, since they represent severe issues for structural integrity of many aerospace applications [1]. Violently amplified and can no longer be compensated by the structural damping [3] [4]. This results in the immediate loss of the blade or in high cycle fatigue failure (HCF) in the long term. Different technologies are available to manipulate the flow [5], such as plasma actuators. These devices induce a local speed perturbation in a region next to the blade surface [6] [7]. The purpose of this paper is to evaluate the effects of these devices during critical conditions, in order to improve compressor efficiency
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