Numerical Investigation and Feasibility Study of a PZT-driven Micro-valve Pulsed-jet Actuator

Kudar, Karen; Carpenter, Peter W.

doi:10.1007/s10494-006-9057-z

Cited by 6 publications

(4 citation statements)

References 43 publications

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“…In terms of fl uid-structure coupling models, the velocity perturbation produced by the motion of the actuator depends greatly on its orientation and, in general, requires a non-trivial fl uid-structure interaction computation in which either fl uid loading or two-way coupling is considered (Kudar and Carpenter, 2007). Short of this general treatment, Cattafesta et al (2001) discuss a simple model for the sinusoidal free-cantilever beam case when fl uid loading is not signifi cant and when fd/U • 1.…”

Section: Fluidic Actuatorsmentioning

confidence: 99%

Fundamentals and Applications of Modern Flow Control

Joslin¹,

Miller²,

Miller³

2009

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Section: Fluidic Actuatorsmentioning

confidence: 99%

Fundamentals and Applications of Modern Flow Control

Joslin¹,

Miller²,

Miller³

2009

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“…Many active device types were then developed for which, depending on the control source used, the control is of different nature (acoustic actuators, plasma actuators, fluidic actuators, etc.). Moreover, within fluidic actuators, one can distinguish synthetic jets devices also called Zero-Net Mass Flux [15][16][17] and pulsed-jet actuators [18,19]. Indeed, for synthetic jets, contrary to pulsed-jets, there exists a suction phase.…”

Section: Active Vgsmentioning

confidence: 99%

The flow structure behind vortex generators embedded in a decelerating turbulent boundary layer

Cathalifaud

Godard

Braud³

et al. 2009

Journal of Turbulence

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The objective of the present work is to analyse the behaviour of a turbulent decelerating boundary layer under the effect of both passive and active jets vortex generators (VGs). The stereo PIV database of Godard and Stanislas [1,2] obtained in an adverse pressure gradient boundary layer is used for this study. After presenting the effect on the mean velocity field and the turbulent kinetic energy, the line of analysis is extended with two points spatial correlations and vortex detection in instantaneous velocity fields. It is shown that the actuators concentrate the boundary layer turbulence in the region of upward motion of the flow, and segregate the near-wall streamwise vortices of the boundary layer based on their vorticity sign.

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“…For this to be a valid approximation heat exchange between the actuator air and the surroundings would need to be negligible. The assumption of adiabatic flow would be a poor assumption for the flow through the orifice, because when the length is more than one or two diameters viscous dissipation is not negligible [28]. The situation we have in mind is that of a MEMSscale actuator embedded in the wing of a large aircraft.…”

Section: Theory For Helmholtz Resonancementioning

confidence: 99%

“…The design and application of such pulsed-jet microvalve actuators are discussed elsewhere in this special issue by Warsop et al [27] and Kudar and Carpenter [28]. The remainder of the paper is set out as follows.…”

Section: Introductionmentioning

confidence: 99%

Is Helmholtz Resonance a Problem for Micro-jet Actuators?

Lockerby

Carpenter

Davies

2007

Flow Turbulence Combust

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A theoretical analysis is described that determines the conditions for Helmholtz resonance for a popular class of self-contained microjet actuator used in both synthetic-and pressure-jump (pulse-jet) mode. It was previously shown that the conditions for Helmholtz resonance are identical to those for optimizing actuator performance for maximum mass flux. The methodology is described for numerical-simulation studies on how Helmholtz resonance affects the interaction of active and nominally inactive micro-jet actuators with a laminar boundary layer. Two sets of numerical simulations were carried out. The first set models the interaction of an active actuator with the boundary layer. These simulations confirm that our criterion for Helmholtz resonance is broadly correct. When it is satisfied we find that the actuator cannot be treated as a predetermined wall boundary condition because the interaction with the boundary layer changes the pressure difference across the exit orifice thereby affecting the outflow from the actuator. We further show that strong inflow cannot be avoided even when the actuator is used in pressurejump mode. In the second set of simulations two-dimensional Tollmien-Schlichting waves, with frequency comparable with, but not particularly close to, the Helmholtz resonant frequency, are incident on a nominally inactive micro-jet actuator. The simulations show that under these circumstances the actuators act as strong sources of 3D Tollmien-Schlichting waves. It is surmised that in the real-life aeronautical applications with turbulent boundary layers broadband disturbances of the pressure field, including acoustic waves, would cause nominally inactive actuators, possibly including pulsed jets, to act as strong disturbance sources. Should this be true it Flow Turbulence Combust (2007) 78:205-222 would probably be disastrous for engineering applications of such massless microjet actuators for flow control.

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Numerical Investigation and Feasibility Study of a PZT-driven Micro-valve Pulsed-jet Actuator

Cited by 6 publications

References 43 publications

Fundamentals and Applications of Modern Flow Control

Fundamentals and Applications of Modern Flow Control

The flow structure behind vortex generators embedded in a decelerating turbulent boundary layer

Is Helmholtz Resonance a Problem for Micro-jet Actuators?

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