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Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing 被引量:4
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作者 Zheng LI Zhiwei SHI +3 位作者 Hai DU Qijie SUN Chenyao WEI Xi GENG 《Plasma Science and Technology》 SCIE EI CAS CSCD 2018年第11期116-125,共10页
Dielectric barrier discharge (DBD) plasma is one of most promising flow control method for its several advantages. The present work investigates the control authority of nanosecond pulse DBD plasma actuators on a fl... Dielectric barrier discharge (DBD) plasma is one of most promising flow control method for its several advantages. The present work investigates the control authority of nanosecond pulse DBD plasma actuators on a flying wing model's aerodynamic characteristics. The aerodynamic forces and moments are studied by means of experiment and numerical simulation. The numerical simulation results are in good agreement with experiment results. Both results indicate that the NS-DBD plasma actuators have negligible effect on aerodynamic forces and moment at the angles of attack smaller than 16-. However, significant changes can be achieved with actuation when the model's angle of attack is larger than 16° where the flow separation occurs. The spatial flow field structure results from numerical simulation suggest that the volumetric heat produced by NS-DBD plasma actuator changes the local temperature and density and induces several vortex structures, which strengthen the mixing of the shear layer with the main flow and delay separation or even reattach the separated flow. 展开更多
关键词 nanosecond dielectric barrier discharge flying wing aircraft flow separation control
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Optimum Duty Cycle of Unsteady Plasma Aerodynamic Actuation for NACA0015 Airfoil Stall Separation Control
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作者 孙敏 杨波 +1 位作者 彭天祥 雷明凯 《Plasma Science and Technology》 SCIE EI CAS CSCD 2016年第6期680-685,共6页
Unsteady dielectric barrier discharge(DBD) plasma aerodynamic actuation technology is employed to suppress airfoil stall separation and the technical parameters are explored with wind tunnel experiments on an NACA00... Unsteady dielectric barrier discharge(DBD) plasma aerodynamic actuation technology is employed to suppress airfoil stall separation and the technical parameters are explored with wind tunnel experiments on an NACA0015 airfoil by measuring the surface pressure distribution of the airfoil.The performance of the DBD aerodynamic actuation for airfoil stall separation suppression is evaluated under DBD voltages from 2000 V to 4000 V and the duty cycles varied in the range of 0.1 to 1.0.It is found that higher lift coefficients and lower threshold voltages are achieved under the unsteady DBD aerodynamic actuation with the duty cycles less than 0.5as compared to that of the steady plasma actuation at the same free-stream speeds and attack angles,indicating a better flow control performance.By comparing the lift coefficients and the threshold voltages,an optimum duty cycle is determined as 0.25 by which the maximum lift coefficient and the minimum threshold voltage are obtained at the same free-stream speed and attack angle.The non-uniform DBD discharge with stronger discharge in the positive half cycle due to electrons deposition on the dielectric slabs and the suppression of opposite momentum transfer due to the intermittent discharge with cutoff of the negative half cycle are responsible for the observed optimum duty cycle. 展开更多
关键词 unsteady plasma aerodynamic actuation DBD duty cycle stall separation control electron deposition opposite momentum transfer suppression
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Experimental Investigation of Flow Separation Control Using Dielectric Barrier Discharge Plasma Actuators 被引量:1
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作者 李钢 聂超群 +2 位作者 李轶明 朱俊强 徐燕骥 《Plasma Science and Technology》 SCIE EI CAS CSCD 2008年第5期605-611,共7页
Influence of plasma actuators as a flow separation control device was investigated experimentally. Hump model was used to demonstrate the effect of plasma actuators on external flow separation, while for internal flow... Influence of plasma actuators as a flow separation control device was investigated experimentally. Hump model was used to demonstrate the effect of plasma actuators on external flow separation, while for internal flow separation a set of compressor cascade was adopted. In order to investigate the modification of the flow structure by the plasma actuator, the flow field was examined non-intrusively by particle image velocimetry measurements in the hump model experiment and by a hot film probe in the compressor cascade experiment. The results showed that the plasma actuator could be effective in controlling the flow separation both over the hump and in the compressor cascade when the incoming velocity was low. As the incoming velocity increased, the plasma actuator was less effective. It is urgent to enhance the intensity of the plasma actuator for its better application. Methods to increase the intensity of plasma actuator were also studied. 展开更多
关键词 dielectric barrier discharge PLASMA separation flow control hump model compressor cascade
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A Karman-Vortex Generator for passive separation control in a conical diffuser 被引量:7
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作者 ZHANG YuFei CHEN HaiXin FU Song 《Science China(Physics,Mechanics & Astronomy)》 SCIE EI CAS 2012年第5期828-836,共9页
Flow separation in a conical diffuser with large divergence angle (29.14°) and large area ratio (3.533) is eliminated by a novel passive flow control device called Karman-Vortex Generator (KVG). The effect ... Flow separation in a conical diffuser with large divergence angle (29.14°) and large area ratio (3.533) is eliminated by a novel passive flow control device called Karman-Vortex Generator (KVG). The effect of the KVG is verified and investigated by the URANS, DES and DDES methods based on the SST model. CFD results show that the performance coefficient of the diffuser can be doubled by the KVG, and the total pressure recovery coefficient can be improved by about 1.2%. DES and DDES re- suits show that the KVG can introduce a Karman-vortex street frequency in the diffuser. This frequency decays rapidly, and could not be detected in the ending plane of the expansion section, Different KVG configurations with different locations and dimensions are numerically simulated and compared. Some suggestions are provided. 展开更多
关键词 conical diffuser Karman-Vortex Generator separation control DES
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Shock Wave Induced Separation Control By Streamwise Vortices 被引量:3
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作者 Ryszard SZWABA 《Journal of Thermal Science》 SCIE EI CAS CSCD 2005年第3期249-253,共5页
Control of shock wave and boundary layer interaction finds still a lot of attention. Methods of this interaction control have been especially investigated in recent decade. This research was mostly concerned with flow... Control of shock wave and boundary layer interaction finds still a lot of attention. Methods of this interaction control have been especially investigated in recent decade. This research was mostly concerned with flows without separation. However, in many applications shock waves induce separation often leads to strong unsteady effects. In this context it is proposed to use streamwise vortices for the interaction control. The results of experimental investigations are presented here. The very promising results were obtained, meaning that the incipient separation was postponed and the separation size was reduced for the higher Mach numbers. The decrease of the RMS of average shock wave oscillation was also achieved. 展开更多
关键词 streamwise vortices separation control boundary layer shock wave
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An Experimental Study of Separation Control on Ultra-Highly-Loaded Low Pressure Turbine Blade by Surface Roughness 被引量:1
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作者 SUN Shuang LEI Zhijun +2 位作者 LU Xingen ZHAO Shengfeng ZHU Junqiang 《Journal of Thermal Science》 SCIE EI CAS CSCD 2015年第3期229-238,共10页
An experimental study is conducted to improve an aft-loaded ultra-high-lift low pressure turbine(LPT) blade at low Reynolds number(Re) in steady state. The objective is to investigate the effect of blade roughness on ... An experimental study is conducted to improve an aft-loaded ultra-high-lift low pressure turbine(LPT) blade at low Reynolds number(Re) in steady state. The objective is to investigate the effect of blade roughness on the performance of LPT blade. The roughness is used as a passive flow control method which is to reduce total pressure loss and expand LPT operating margin. The experiment is performed on a low-speed cascade facility. 3 roughness heights and 3 deposit positions are investigated in the experiment which forms a large test matrix. A three-hole probe is used to detect flow aerodynamic performance and a hotwire probe is used to detect the characteristic of suction boundary layer. Regional roughness can suppress separation loss and bring fairly low turbulent dissipation loss. Detailed surveys near the blade surface shows that the loss reduction is due to the disappearance of separation bubble from the early transition onset. 展开更多
关键词 separation control Turbine blade Surface roughness
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Experimental Investigation on Aerodynamic Control of a Wing with Distributed Plasma Actuators 被引量:3
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作者 韩孟虎 李军 +2 位作者 梁华 牛中国 赵光银 《Plasma Science and Technology》 SCIE EI CAS CSCD 2015年第6期502-509,共8页
Experimental investigation of active flow control on the aerodynamic performance of a flying wing is conducted. Subsonic wind tunnel tests are performed using a model of a 35° swept flying wing with an nanosecond... Experimental investigation of active flow control on the aerodynamic performance of a flying wing is conducted. Subsonic wind tunnel tests are performed using a model of a 35° swept flying wing with an nanosecond dielectric barrier discharge (NS-DBD) plasma actuator, which is installed symmetrically on the wing leading edge. The lift and drag coefficient, lift-to- drag ratio and pitching moment coefficient are tested by a six-component force balance for a range of angles of attack. The results indicate that a 44.5% increase in the lift coefficient, a 34.2% decrease in the drag coefficient and a 22.4% increase in the maximum lift-to-drag ratio can be achieved as compared with the baseline case. The effects of several actuation parameters are also investigated, and the results show that control efficiency demonstrates a strong dependence on actuation location and frequency. Furthermore, we highlight the use of distributed plasma actuators at the leading edge to enhance the aerodynamic performance, giving insight into the different mechanism of separation control and vortex control, which shows tremendous potential in practical flow control for a broad range of angles of attack. 展开更多
关键词 PLASMA flow separation control NS-DBD flying wing sequence
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Influence of separator control on the characteristics of severe slugging flow 被引量:4
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作者 Luo Xiaoming He Limin +1 位作者 Liu Xinye Lü Yuling 《Petroleum Science》 SCIE CAS CSCD 2014年第2期300-307,共8页
Due to the special structure of offshore multiphase pipes, it is easy for severe slugging to occur in the riser at low gas-liquid velocity. Violent pressure fluctuations and dramatic changes of flow rate are the main ... Due to the special structure of offshore multiphase pipes, it is easy for severe slugging to occur in the riser at low gas-liquid velocity. Violent pressure fluctuations and dramatic changes of flow rate are the main characteristics of severe slugging, leading to the risk of serious damage. In this paper, the separator control is adopted to accurately control the separator liquid level and pressure under severe slugging flow conditions. This indicates that the separator liquid level control alone does not have a significant impact on the upstream flow, but it is beneficial for normal operation and pressure control of the separator. As the separator pressure increases, the peak pressure in the riser apparently diminishes, and the amplitude of pressure fluctuation gradually decreases, which means that severe slugging is inhibited. During the slug blowing out, the gas/liquid slipping in the riser intensifies. The long gas plug quickly flows through the riser, and then tends to morph into short and slowly flowing gas bubbles. The elimination effect of the pressure control strategy on severe slugging is related to the relative rate of the superficial gas/liquid flow. 展开更多
关键词 Multiphase flow severe slugging separator control RISER
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Co-Simulation Research of the Mechanical-Hydraulic-Control Coupling System of ITER Tractor 被引量:1
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作者 杨秀清 骆敏舟 +1 位作者 梅涛 姚达毛 《Plasma Science and Technology》 SCIE EI CAS CSCD 2009年第3期334-340,共7页
The virtual prototyping models of the mechanical, hydraulic and control system of the ITER tractor were built with CATIA, ADAMS and MATLAB/Simulink respectively according to its heavy load and high precision character... The virtual prototyping models of the mechanical, hydraulic and control system of the ITER tractor were built with CATIA, ADAMS and MATLAB/Simulink respectively according to its heavy load and high precision characteristics, and the data transfer between the different models was accomplished by the integration interface between different software. Consequently the virtual experimental platform for the multi-disciplinary co-simulation was established. A co-simulation study of the mechanical-hydraulic-control coupling system of the ITER tractor was carried out. The synchronization servo control of parallel hydraulic cylinders was implemented, and the tracking control of the preconcerted trajectory of the hydraulic cylinders was realized on the established experimental platform. This paper presents the optimization design and technology rebuilding for the complicated coupling system with its theoretic foundation and co-simulation virtual experimental platform. 展开更多
关键词 CO-SIMULATION mechanical-hydraulic coupling PID control of integral separation hydraulic synchronization servo system
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Application of the dividing wall column to olefin separation in fluidization methanol to propylene(FMTP) process 被引量:1
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作者 Xiaolong Ge Botong Liu +2 位作者 Xigang Yuan Yiqing Luo Kuo-Ksong Yu 《Chinese Journal of Chemical Engineering》 SCIE EI CAS CSCD 2017年第8期1069-1078,共10页
Dividing wall column(DWC)is shown to be energy efficient compared to conventional column sequence for multi components separation,which is used for olefin separation in fluidization methanol to propylene process in th... Dividing wall column(DWC)is shown to be energy efficient compared to conventional column sequence for multi components separation,which is used for olefin separation in fluidization methanol to propylene process in the present work.Detailed design for pilot DWC was performed and five control structures,i.e.composition control(CC),temperature control(TC),composition-temperature control(CC-TC),temperature difference control(TDC),double temperature difference control(DTDC)were proposed to circumvent feed disturbance.Sensitivity analysis and singular value decomposition(SVD)were used as criterion to select the controlled temperature locations in TC,CC-TC,TDC and DTDC control loops.The steady simulation result demonstrates that 25.7% and 30.2% duty can be saved for condenser and reboiler by substituting conventional column sequence with DWC,respectively.As for control structure selection,TC and TDC perform better than other three control schemes with smaller maximum deviation and shorter settling time. 展开更多
关键词 Distillation Dividing wall column Olefin separation Detailed design Process control
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DOUBLE LOOP ACTIVE VIBRATION CONTROL OF PNEUMATIC ISOLATOR WITH TWO SEPARATE CHAMBERS
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作者 YANG Qingjun LI Jun WANG Zuwen 《Chinese Journal of Mechanical Engineering》 SCIE EI CAS CSCD 2006年第4期610-613,共4页
A newly designed pneumatic spring with two separate chambers is promoted and double-loop active control is introduced to overcome the following drawbacks of passive pneumatic isolation: ① The low frequency resonance... A newly designed pneumatic spring with two separate chambers is promoted and double-loop active control is introduced to overcome the following drawbacks of passive pneumatic isolation: ① The low frequency resonances introduced into the system; ② Conflict between lower isolation frequency and stiffness high enough to limit quasi-static stroke;③ Inconsistent isolation level with different force load. The design of two separate chambers is for the purpose of tuning support frequency and force independently and each chamber is controlled by a different valve. The inner one of double-loop structure is pressure control, and in order to obtain good performance, nonlinearities compensation and motion flow rate compensation (MFRC) are added besides the basic cascade compensation, and the influence of tube length is studied. The outer loop has two functions: one is to eliminate the resonance caused by isolation support and to broaden the isolation frequency band by payload velocity feedback and base velocity feed forward, and the other is to tune support force and support stiffness simultaneously and independently, which means the support force will have no effect on support stiffness. Theoretical analysis and experiment results show that the three drawbacks are overcome simultaneously. 展开更多
关键词 Pneumatic isolator Active vibration control Double-loop control Two separate chambers Mass flow rate compensation (MFRC)
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Investigation of the interaction between NS-DBD plasma-induced vortexes and separated flow over a swept wing
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作者 刘备 梁华 郑博睿 《Plasma Science and Technology》 SCIE EI CAS CSCD 2023年第1期88-99,共12页
The effect of nanosecond pulsed dielectric barrier discharge(NS-DBD) plasma flow separation control is closely related to the actuation frequency,because it involves the interaction between plasma-induced vortexes and... The effect of nanosecond pulsed dielectric barrier discharge(NS-DBD) plasma flow separation control is closely related to the actuation frequency,because it involves the interaction between plasma-induced vortexes and separated flow.In order to study the mechanism of NS-DBD plasma flow separation control over a swept wing,especially the influence of the actuation frequency,at first,experimental studies of the actuation frequencies at 100 Hz are conducted to validate the numerical simulation method.Then,numerical studies of different actuation frequencies which are 50 Hz,100 Hz,160 Hz,200 Hz,500 Hz,and 1000 Hz,respectively are conducted.The interaction between the plasma-induced vortexes and the separated flow is analyzed.Results show that there is a range of the actuation frequency which includes the frequency(160 Hz) calculated by the average aerodynamic chord length to make the control effect good,but when the actuation frequencies are too low(50 Hz) or too high(1000 Hz),the control effect will get worse.The former is because plasmainduced vortexes disappear in a period within an actuation cycle;the latter is because plasma-induced vortexes cannot develop completely,resulting in a weak vortex intensity. 展开更多
关键词 plasma-induced vortex flow separation control NS-DBD LES
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Parametric analyses for synthetic jet control on separation and stall over rotor airfoil 被引量:11
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作者 Zhao Guoqing Zhao Qijun 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2014年第5期1051-1061,共11页
Numerical simulations are performed to investigate the effects of synthetic jet control on separation and stall over rotor airfoils. The preconditioned and unsteady Reynolds-averaged Navier–Stokes equations coupled w... Numerical simulations are performed to investigate the effects of synthetic jet control on separation and stall over rotor airfoils. The preconditioned and unsteady Reynolds-averaged Navier–Stokes equations coupled with a k x shear stream transport turbulence model are employed to accomplish the flowfield simulation of rotor airfoils under jet control. Additionally,a velocity boundary condition modeled by a sinusoidal function is developed to fulfill the perturbation effect of periodic jets. The validity of the present CFD procedure is evaluated by the simulated results of an isolated synthetic jet and the jet control case for airfoil NACA0015. Then, parametric analyses are conducted specifically for an OA213 rotor airfoil to investigate the effects of jet parameters(forcing frequency, jet location and momentum coefficient, jet direction, and distribution of jet arrays) on the control effect of the aerodynamic characteristics of a rotor airfoil. Preliminary results indicate that the efficiency of jet control can be improved with specific frequencies(the best lift-drag ratio at F+= 2.0) and jet angles(40 or 75) when the jets are located near the separation point of the rotor airfoil. Furthermore, as a result of a suitable combination of jet arrays, the lift coefficient of the airfoil can be improved by nearly 100%, and the corresponding drag coefficient decreased by26.5% in comparison with the single point control case. 展开更多
关键词 Flow control Flow separation Parametric analysis Rotor Synthetic jet
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NUMERICAL STUDY ON THE FLOW AROUND A CIRCULAR CYLINDER WITH SURFACE SUCTION OR BLOWING USING VORTICITY-VELOCITY METHOD 被引量:2
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作者 LING Guo-ping(凌国平) +1 位作者 FANG Jian-wen(方健雯) 《Applied Mathematics and Mechanics(English Edition)》 SCIE EI 2002年第9期1089-1096,共8页
A vorticity-velocity method was used to study the incompressible viscous fluid flow around a circular cylinder with surface suction or blowing. The resulted high order implicit difference equations were effeciently so... A vorticity-velocity method was used to study the incompressible viscous fluid flow around a circular cylinder with surface suction or blowing. The resulted high order implicit difference equations were effeciently solved by the modified incomplete LU decomposition conjugate gradient scheme ( MILU-CG). The effects of surface suction or blowing' s position and strength on the vortex structures in the cylinder wake, as well as on the drag and lift forces at Reynoldes number Re = 100 were investigated numerically. The results show that the suction on the shoulder of the cylinder or the blowing on the rear of the cylinder can effeciently suppress the asymmetry of the vortex wake in the transverse direction and greatly reduce the lift force; the suction on the shoulder of the cylinder, when its strength is properly chosen, can reduce the drag force significantly, too. 展开更多
关键词 circular cylinder with surface suction or blowing separated vortex flow around bluff body and its control vorticity-velocity method preconditioned conjugate gradient method
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A survey of safety separation management and collision avoidance approaches of civil UAS operating in integration national airspace system 被引量:11
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作者 Xiangmin GUAN Renli LYU +1 位作者 Hongxia SHI Jun CHEN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2020年第11期2851-2863,共13页
Recent years have witnessed a booming of the industry of civil Unmanned Aircraft System(UAS).As an emerging industry,the UAS industry has been attracting great attention from governments of all countries and the aviat... Recent years have witnessed a booming of the industry of civil Unmanned Aircraft System(UAS).As an emerging industry,the UAS industry has been attracting great attention from governments of all countries and the aviation industry.UAS are highly digitalized,informationized,and intelligent;therefore,their integration into the national airspace system has become an important trend in the development of civil aviation.However,the complexity of UAS operation poses great challenges to the traditional aviation regulatory system and technical means.How to prevent collisions between UASs and between UAS and manned aircraft to achieve safe and efficient operation in the integrated operating airspace has become a common challenge for industry and academia around the world.In recent years,the international community has carried out a great amount of work and experiments in the air traffic management of UAS and some of the key technologies.This paper attempts to make a review of the UAS separation management and key technologies in collision avoidance in the integrated airspace,mainly focusing on the current situation of UAS Traffic Management(UTM),safety separation standards,detection system,collision risk prediction,collision avoidance,safety risk assessment,etc.,as well as an analysis of the bottlenecks that the current researches encountered and their development trends,so as to provide some insights and references for further research in this regard.Finally,this paper makes a further summary of some of the research highlights and challenges. 展开更多
关键词 Air transportation Collision avoidance SAFETY separation control Unmanned aircraft system
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Novel lift enhancement method based on zero-mass-flux jets and its adaptive controlling laws design 被引量:5
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作者 Zhijie Zhao Zhenbing Luo +4 位作者 Bin Xu Xiong Deng Yuyan Guo Wenqiang Peng Shiqing Li 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2021年第10期1567-1579,I0003,共14页
For lessening the weight and volume of flow control system,enlarging the circulation control applying area of angle of attack(AOA),and achieving nice controlling characteristics,a novel lift enhancement method based o... For lessening the weight and volume of flow control system,enlarging the circulation control applying area of angle of attack(AOA),and achieving nice controlling characteristics,a novel lift enhancement method based on dual synthetic jet actuators(DSJAs)and synthetic jet actuator(SJA),and an adaptive proportional integral and differential(PID)algorithm based on radial basis function neural network are introduced.DSJAs are uniformly located along the chord to suppress the separation and trailing-edge SJA is applied to achieve the high circulation.Velocities of actuators are modulated to realize the real speed profile and on–off controlling laws of DSJAs are designed.Numerical simulations show that DSJAs and SJA could suppress the separation completely and move leading-edge stagnation point and trailing-edge separation point downstream even at AOA of 19°,hence achieve the highest lift and nose-down moment augmentation(ΔCl_(max)=0.92,ΔCm_(max)=0.02534),andΔL/D can reach 11.39 at AOA of 18°.Stalling is delayed to more than 19°.Linear lift area and pitch-break angle are both increased to 16°.ΔCl/C_(μ) can reach 76.7,indicating the greatest control efficiency.The results of adaptive PID control,whose controlling effects are proved better than PID,indicate that lift could track the objective with the rise time of 0.0325 s and finally keep steady,suggesting the nice stability and rapidness. 展开更多
关键词 Lift enhancement Circulation control separation control Synthetic jet Adaptive control
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Influence of Air-Jet Vortex Generator Diameter on Separation Region 被引量:3
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作者 Ryszard Szwaba 《Journal of Thermal Science》 SCIE EI CAS CSCD 2013年第4期294-303,共10页
Control of shock wave and boundary layer interaction continues to attract a lot of attention. In recent decades several methods of interaction control have been investigated. The research has mostly concerned solid (v... Control of shock wave and boundary layer interaction continues to attract a lot of attention. In recent decades several methods of interaction control have been investigated. The research has mostly concerned solid (vane type) vortex generators and transpiration methods of suction and blowing. This investigation concerns interaction control using air-jets to generate streamwise vortices. The effectiveness of air-jet vortex generators in controlling separation has been proved in a previous research. The present paper focuses on the influence of the vortex generator diameter on the separation region. It presents the results of experimental investigations and provides new guidelines for the design of air-jet vortex generators to obtain more effective separation control. 展开更多
关键词 shock wave boundary layer separation control streamwise vortices air-jet vortex generator
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PARTIAL STABILIZATION OF A CLASS OF CONTINUOUS NONLINEAR CONTROL SYSTEMS WITH SEPARATED VARIABLES 被引量:1
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作者 JiguiJIAN XiaoxinLIAO 《Journal of Systems Science and Systems Engineering》 SCIE EI CSCD 2005年第2期177-186,共10页
关键词 Nonlinear control system separated variables partial stability stabilizing controller M-matrix
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Comparison of aerodynamic characteristics between a novel highly loaded injected blade with curvature induced pressure-recovery concept and one with conventional design 被引量:6
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作者 Zhiyuan CAO Chao ZHOU Zhili SUN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2017年第3期939-950,共12页
This paper introduces a novel design method of highly loaded compressor blades with air injection.CFD methods were firstly validated with existing data and then used to develop and investigate the new method based on ... This paper introduces a novel design method of highly loaded compressor blades with air injection.CFD methods were firstly validated with existing data and then used to develop and investigate the new method based on a compressor cascade.A compressor blade is designed with a curvature induced pressure-recovery concept.A rapid drop of the local curvature on the blade suction surface results in a sudden increase in the local pressure,which is referred to as a curvature induced ‘Shock'.An injection slot downstream from the ‘Shock' is used to prevent ‘Shock' induced separation,thus reducing the loss.As a result,the compressor blade achieves high loading with acceptable loss.First,the design concept based on a 2D compressor blade profile is introduced.Then,a 3D cascade model is investigated with uniform air injection along the span.The effects of the incidence are also investigated on emphasis in the current study.The mid-span flow field of the 3D injected cascade shows excellent agreement with the 2D designed flow field.For the highly loaded cascade without injection,the flow separates immediately downstream from the ‘Shock';the initial location of separation shows little change in a large incidence range.Thus air injection with the same injection configuration effectively removes the flow separation downstream from the curvature induced ‘Shock' and reduces the size of the separation zone at different incidences.Near the endwall,the flow within the incoming passage vortex mixes with the injected flow.As a result,the size of the passage vortex reduces significantly downstream from the injection slot.After air injection,the loss coefficient along spanwise reduces significantly and the flow turning angle increases. 展开更多
关键词 Axial compressor Air injection Curvature induced ‘Shock’ Flow control separation
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