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检索条件"主题词=Active Flow Control"

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Cavity Effect of Synthetic Jet Actuators based on Piezoelectric Diaphragm

Cavity Effect of Synthetic Jet Actuators based on Piezoelect...

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AEROTECH 4 - Conference on Recent Advances in Aerospace Technologies

作者： Dahalan, Md Nizam Mansor, Shuhaimi Ali, Airi Univ Teknol Malaysia Dept Aeronaut Engn Fac Mech Engn Skudai 81310 Johor Malaysia

ISBN: (纸本)9783037855065

An active flow control technology known as synthetic jet actuator (SJA) is a zero-net mass-flux device to create pulsed jet that produces momentum to its surroundings and uses a vibrating diaphragm inside the cavity to generate an oscillatory flow through a small orifice. The performance of SJA depends on the design of an orifice and cavity, and oscillating membrane. SJA design based on piezoelectric diaphragm used in this project because of their size, lightweight, no need for external air supply, without the pipe complex, fast response time and low power consumption. This paper describes the cavity effect to SJA designs and experiments were performed to determine the air jet velocity produced through the orifice using a hot-wire anemometer at a different cavity thickness. The results demonstrate that the jet velocity increase would be better if the cavity thickness is reduced. However, more studies are needed to optimize the size of cavity and orifice for appropriate applications.

关键词： synthetic jet actuator piezoelectric diaphragm active flow control

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Airfoil optimisation for DBD plasma actuator in a wind energy environment: Design and experimental study 55

Airfoil optimisation for DBD plasma actuator in a wind energ...

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55th AIAA Aerospace Sciences Meeting

作者： Carbonell Batlle, E. Pereira, R. Kotsonis, M. de Oliveira, G. Terrassa School of Industrial Aerospace and Audiovisual Engineering Polytechnic University of Catalonia Colom 11 Terrassa08222 Spain Faculty of Aerospace Engineering Delft University of Technology Kluyverweg 1 Delft2629 HS Netherlands

ISBN: (数字)9781624104473

ISBN: (纸本)9781624104473

This article describes and experimentally evaluates an airfoil design methodology, in which airfoils are designed to be simultaneously suited for wind energy applications and to employ Dielectric Barrier Discharge Plasma Actuators (DBD PA) as active flow control (AFC) devices. The design process is carried out using a multi-objective optimizer solved with a genetic algorithm, which evaluates 150 airfoil candidates along 30 generations to optimize their performance. The airfoil candidate evaluation is done with two cost functions: the wind energy suitability cost function compares the non-actuated airfoil performance with a reference group of airfoils, while the AFC suitability cost function assesses the changes in the CL(named CLauthority) caused by the DBD PA actuation. From the generated airfoils, a candidate is selected and tested experimentally at design and off-design conditions. The parametric study on the experimental airfoil performance includes different wind speeds, DBD voltage amplitude and actuation direction. From multiple off-design condition tests it is possible to observe a maximum actuation efficiency at design condition, since higher voltages applied do not lead to a significant increase of the CLauthority and different wind speeds and actuation direction reduce the actuation efficiency. Additionally, the experimental angle of attack range at which DBD actuation induces lift variations compares well with simulated data, and the predicted trends of the actuator impact are confirmed, even though the experimental dCl is smaller than simulated results. The present article demonstrates the potential of the studied airfoil design process to create the future generation of plasma actuated wind energy airfoils. © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Wind Energy Plasma Actuator Airfoil Dielectric Barrier Discharge Aerodynamic Performance active flow control Multi Objective Genetic Algorithm Wind Turbine Laminar Turbulent Transition Wind Tunnel Tests

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Study on forebody vortex cores under plasma actuations

Study on forebody vortex cores under plasma actuations

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2010 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2010

作者： Wang, Jianlei Li, Huaxing Meng, Xuanshi Feng, Liu Shijun, Luo National Key Laboratory of Aerodynamics Design and Research Northwestern Polytechnical University Xi'an China Department of Mechanical and Aerospace Engineering University of California IrvineCA United States

ISBN: (纸本)9787561228999

The characteristics of the vortex cores over a 20o circular-cone forebody under plasma actuation are studied at 45o angle of attack. Section velocity distribution and pressure distribution are measured in a low-turbulence 3. 0m×1. 6m low-speed open-circuit wind tunnel. The Reynolds number based on the base diameter of the circular cone is 50,000. Pressure distribution, local side force, vortex core center position, axial vorticity are studied. Achieve to control the side force of the circular-cone under the plasma actuations. The results show that the separation shear layer and rolled-up vortex core move out on the same side and close in on the other side. In repetition wind tunnel runs of the same model, the flow asymmetry pattern remains unchanged for port-on and starboard-on, but may be changed for plasma-off.

关键词： active flow control Asymmetric separation vortex High angle of attack Particle image velocimetry Plasma Single-dielectric barrier discharge

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Design of membrane actuators based on ferromagnetic shape memory alloy composfte for the synthetic jet actuator

Design of membrane actuators based on ferromagnetic shape me...

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Smart Structures and Materials 2004 Conference

作者： Liang, YC Taya, M Kuga, Y Univ Washington Dept Engn Mech Ctr Intelligent Mat & Syst Seattle WA 98195 USA

ISBN: (纸本)0819453072

A new membrane actuator based on our previous diaphrapm actuator was designed and constructed to improve the dynamic performance. The finite element analysis was used to estimate the frequency response of the composite membrane which will be driven close to its resonance to obtain a large stroke. The membrane is made of ferromagnetic shape memory alloy (FSMA) composite including a ferromagnetic soft iron pad and a superelastic grade of NiTi shape memory alloy (SMA). The actuation mechanism for the FSMA composite membrane of the actuator is the hybrid mechanism that we proposed previously. This membrane actuator is designed for a new synthetic jet actuator package that will be used for active flow control technology on airplane wings. Based on the FEM results, the new membrane actuator system was assembled and its static and dynamic performance was experimentally evaluated including the dynamic magnetic response of the hybrid magnet.

关键词： shape memory alloy active flow control ferromagnetic synthetic jet superelasticity martensitic transformation hybrid mechanism composite hybrid magnet

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Numerical Investigation of Strategies Aimed at Reduction of Low-Pressure Turbine Endwall Losses

Numerical Investigation of Strategies Aimed at Reduction of ...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Romero, S. Gross, A. New Mexico State Univ Dept Mech & Aerosp Engn Las Cruces NM 88003 USA

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

The endwall flow for a highly loaded linear low-pressure turbine cascade was investigated numerically for a chord-based Reynolds number of 10(5). Both an active and a passive flow control strategy were investigated. For the former, pulsed disturbances were introduced at the endwall near the leading edge. For the latter, the blade was contoured near the endwall. Both strategies were found to weaken the passage vortex and lower the mass-averaged total pressure losses. The proper orthogonal decomposition was employed to investigate the flow response to the unsteady forcing. With active flow control, the most energetic modes capture an unsteady response of the passage vortex that is synchronized with the unsteady blowing. The second part of the paper is concerned with the development of a sliding mesh technique for cascade simulations with upstream wake generator.

关键词： Low Pressure Turbine active flow control Leading Edges Horseshoe Vortex Adverse Pressure Gradient Incompressible flow Laminar Separation Bubble Air Force Research Laboratory Rotor Blades Particle Image Velocimetry

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Improving Efficiency of Co-flow Jet Micro-Compressor Actuator Outlet Guide Vanes and Nozzle

Improving Efficiency of Co-Flow Jet Micro-Compressor Actuato...

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AIAA Aviation Forum and Exposition

作者： Xu, Kewei Zha, Gecheng Univ Miami Dept Mech & Aerosp Engn Coral Gables FL 33124 USA

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

This paper conducts the numerical design of the outlet guide vanes (OGV) and nozzle for a Co-flow Jet (CFJ) micro-compressor actuator to maximize the efficiency. For CFJ active flow control, the embedded microcompressor actuator is required to produce the static pressure ratio (pi(s-t)) lower than 1 to match the low pressure of CFJ airfoil leading edge suction peak. Therefore, a high efficiency outlet guide vane with a nozzle designed to deswirl the flow and decrease the outlet static pressure. Parametric studies of the OGV deswirl angle and flow path geometrical parameters are studied including: the flow path diverging location and diverging angle for the OGV, the flow path converging location and converging angle for the nozzle. The numerical results show that for the OGV, a flow path with a 7 degrees front diverging (33%) is beneficial to decrease the OGV outlet Mach number. For the nozzle downstream of the OGV, a 10 degrees rear converging location at 80% streamwise length is able to achieve the targeted static pressure ratio of 0.987 with a minimum loss. It is also found that deswirling by the vanes with a converging nozzle helps to reduce the vane loading and loss. The final optimized compressor has outlet swirl angle of 5.45 degrees, total pressure recovery of 98.7% and compressor efficiency of 75.05%. The efficiency analysis of a low pressure ratio compressor is conducted. In addition to the stage efficiency and total pressure recovery of OGV and nozzle, it is found that a higher stage total pressure ratio is beneficial to achieve a higher full compressor efficiency. The full compressor efficiency is sensitive to the total pressure recovery of the OGV and outlet duct. For the present design with the stage pressure ratio of 1.13, if the total pressure recovery drops from 0.99 to 0.98 by one point, it costs the full compressor efficiency loss by 8 points from 77% to 69%. It is hence crucial to have an efficient design of the OGV and outlet duct. The penalty is

关键词： Axial Centrifugal Compressor Actuators Nozzles active flow control Static Pressure Airfoil Leading Edges Shear Stress Mass flow Rate Mixed flow Compressor

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Simulation of In-Flight Anti-Icing based AC-SDBD Plasma Actuation

Simulation of In-Flight Anti-Icing based AC-SDBD Plasma Actu...

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AIAA Aviation Forum

作者： Ran, Zhuoling Meng, Xuanshi Yi, Xian Liu, Senyun Northwestern Polytech Univ Sch Aeronaut Xian 710072 Shaanxi Peoples R China China Aerodynam Res & Dev Ctr Key Lab Icing & Anti Deicing Mianyang 621000 Sichuan Peoples R China

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

Aircraft icing is a major concern in aviation safety, as it affects the aerodynamic performance of the aircraft and jeopardizes its operation. Surface dielectric barrier discharge (SDBD) plasma actuation is a promising active flow control technology that can generate both aerodynamic and thermal effects, and has potential for anti-icing application. An important aspect in plasma actuation for anti-icing is to investigate its mechanism. In this paper, the present study utilizes numerical simulations to investigate the ice accretion on a NACA0012 airfoil without plasma actuation, and then analyzes the effect of AC-SDBD plasma actuation on the anti-icing of the same airfoil. The present study additionally focuses on analyzing the mechanism of anti-icing using AC-SDBD plasma actuation. Firstly, the numerical simulation calculates the icing shape of the NACA0012 airfoil without plasma actuation, in agreement with experimental results. The results indicate that the upper surface of the airfoil exhibited the most severe icing, with 44% of the chord length covered in glaze ice at an angle of attack of -5 degrees. Next, the present study investigates the aerodynamic and thermal effects of plasma actuation under static atmospheric condition. The findings indicate that the plasma actuator can induce airflow acceleration by injecting momentum and increase the surrounding temperature by injecting energy. Lastly, the study examines the effects of combined aerodynamic and thermal plasma actuation on anti-icing under inflow conditions. The results show that the aerodynamic effect of the plasma actuator modifies the local flow field, influencing the movement of supercooled water drops on the airfoil surface and impacting icing. In contrast, the thermal effect raises the local temperature, creating a film of supercooled water on the surface of the airfoil and inhibiting ice growth. The findings suggest that the thermal effect plays a significant role in anti-icing and the plasma actu

关键词： Anti Icing Airfoil Surface Thermal Effects Aerodynamic Performance Plasma Actuator Numerical Simulation Supercooling Surface Dielectric Barrier Discharge Atmospheric Conditions active flow control

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Aggressively-Offset Inlet flow Facility Design and Characterization

Aggressively-Offset Inlet Flow Facility Design and Character...

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AIAA Science and Technology Forum and Exposition (AIAA SciTech)

作者： Webb, N. O'Neill, C. Samimy, M. Ohio State Univ Aerosp Res Ctr Gas Dynam & Turbulence Lab Columbus OH 43235 USA

ISBN: (数字)9781624105951

ISBN: (纸本)9781624105951

Balancing aircraft capability and cost is becoming increasingly important and naturally suggests the incorporation of a compact inlet system with an aggressively-offset diffuser and relatively short length. The flow through such an inlet requires aerodynamic treatment to avoid separation and strong secondary vortices which can significantly degrade the propulsion system performance and service life. Significant research and development efforts have sought to understand and control this very complex, three-dimensional flow field. The ultimate objective of this work is to mitigate the flow non-uniformity at the aerodynamic interface plane (AIP) using active flow control. A new, aggressively-offset inlet/diffuser facility capable of throat Mach numbers up to 0.85 has been designed and built. Current experimental diagnostics include time-averaged and (limited) time-resolved AIP total pressure, centerline static pressure, and oil-flow visualization. As expected, the flow quality (total-pressure loss and non-uniformity at the AIP) degrades as the throat Mach number increases. As in literature, the crossflows are observed to be the dominant flow features. Modifications of the internal contour (made to provide optical access) are seen to have a significant effect on the flow. Preliminary analysis of time-resolved pressure measurements of the centerline and AIP provides insight into the region of influence of the separation and associated phenomena.

关键词： flow Conditions active flow control Adverse Pressure Gradient Strouhal Number Offset Diffusers Static Pressure Propulsion System flow Separation Plasma Actuator Particle Image Velocimetry

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Reduced order modeling of a dynamically pitching NACA 0018 airfoil 55

Reduced order modeling of a dynamically pitching NACA 0018 a...

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55th AIAA Aerospace Sciences Meeting

作者： Niel, Fabien Fagley, Casey Seidel, Jürgen McLaughlin, Thomas Laboratory for Analysis and Architecture of Systems Methods and Algorithms for Control CNRS 7 avenue du Colonel Roche BP 54200 Toulouse cedex 431031 France French Air Force Laboratory for Analysis and Architecture of Systems Methods and Algorithms for Control CNRS 7 avenue du Colonel Roche BP 54200 cedex 4 Toulouse31031 France Department of Aeronautics U.S. Air Force Academy CO80840 United States Aeronautics Research Center Department of Aeronautics U.S. Air Force Academy CO80840 United States

ISBN: (数字)9781624104473

ISBN: (纸本)9781624104473

active flow control for flutter relies on accurate dynamic models of the unsteady aerodynamic forces and moments, capturing the nonlinear behavior at high angles of attack. This paper presents a model of a dynamically pitching NACA 0018 airfoil capturing dynamic hysteresis and vortex shedding influence on the moment coefficient about mid-chord. This model provides an extension to the model proposed by Goman-Khrabrov, and modified by Williams, using the ONERA BH model to include the vortex shedding. Dynamic pitching experiments about mid chord are performed for different reduced frequencies and amplitudes on a 2-D NACA 0018 Airfoil at low speed (M = 0:068) with a Reynolds number Rec= 190;000. The results from model calculations are compared to experimental data and discussed. © 2017 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Thin Airfoil Theory Critical Angle of Attack Strouhal Number active flow control Hysteresis Separated flows United States Air Force Wind Tunnels Adverse Pressure Gradient State Space Representation

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Numerical study on the flow field generated by a double-orifice synthetic jet device 24th

Numerical study on the flow field generated by a double-orif...

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24th Conference of the Italian Association of Theoretical and Applied Mechanics, AIMETA 2019

作者： Palumbo, Andrea Della Pia, Alessandro Chiatto, Matteo de Luca, Luigi Department of Industrial Engineering Università degli Studi di Napoli "Federico II" P.le Tecchio 80 Naples80125 Italy

ISBN: (纸本)9783030410568

The application of synthetic jet actuators to control aerodynamic flows has been widely investigated in the last years. In many situations, arrays of synthetic jet actuators or multiple-orifice (or multi-slot) devices are preferred to single-orifice/single-slot actuators, especially in separation control and cooling applications. However, the behaviour of the flow field generated by such actuators is still the object of ongoing research, both in quiescent conditions and in presence of a crossflow. A numerical study on synthetic jets issuing from a double-orifice, single-cavity device is presented in the present work. A series of direct numerical simulations is carried out using the open-source code Open-FOAM. The study focuses on the behaviour of the jets in the near-field: time-averaged velocity profiles and phase-averaged velocity fields are investigated. After validating the computational setup against previous experimental data, the spacing between the orifices is gradually decreased. Scaling laws for the merging point and the combined point are derived and compared qualitatively with previous literature results about round, continuous twinjets. It is shown that the time-averaged merging point streamwise position is linearly dependent on the jet spacing. The analysis of the phase-averaged velocity shows that for low spacings the trajectory of the vortex arising from the orifice lips is inclined, whereas for high spacings the near-field behaviour is similar to a isolated jet. © Springer Nature Switzerland AG 2020.

关键词： active flow control Synthetic jet actuators Twinjets

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