2007 Vol. 22, No. 9

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Performance experiment of a reflection flow annular combustor with slinger
SONG Shuang-wen, JIANG Rong-wei, CHEN Jian, LIANG De-wang
2007, 22(9): 1401-1404.
Abstract PDF(1164KB) icon1619 icon490
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An experimental study on performance of a slinger annular combustor was performed at various slinger rotary speeds.The experimental results show that it has a higher total pressure recovery coefficient and a narrow lean blowoff limit.The outlet temperature distribution factor is less than 0.3,and combustion efficiency is above 0.99.The experimental results provide technical support for this kinds of combustor design and development.
Numerical analysis of single-phase gaseous flow characteristics in microchannels
ZHANG Tian-tian, JIA Li, WU Li-yuan, FENG Wu-jun
2007, 22(9): 1405-1411.
Abstract PDF(751KB) icon1569 icon467
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The microchannel is an integral part of various micro systems.The flow characteristics of nitrogen in three different microchannels(hydraulic diameter of 30～3000 μm) were numerically investigated with consideration of the effect of compressibility and viscosity heating.The effects of size and Reynolds number(Re) on pressure drop,friction factor and friction constant were investigated.Especially,the priority of the research was placed on the effect of ratio of length,entrance/exit,compressibility and viscosity heating.The calculated results show that transition Re is brought forward to about 1 200 in 300 μm microchannels.
Experimental study of the effects of tabs on jet impingement heat transfer
YU Ye-zhen, ZHANG Jing-zhou, YANG Wei-hua
2007, 22(9): 1412-1416.
Abstract PDF(1265KB) icon1792 icon477
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The impingement characteristics of a circular jet with vortex-generating tabs were investigated experimentally.This experiment was focused on the effects of blockage ratio,shape and installation angle of tabs on impingement heat transfer,revealing that the shapes and installation angle of tabs have great influence upon the convective heat transfer of impingement.According to the pattern of influence,beneficial reference opinions were raised on the structural designs of tabs.
Experimental study of the heat transfer characteristics of combined cooling of impingement+reversed convection+film
SONG Shuang-wen, YANG Wei-hua, HU Hao-sheng, ZHANG Jing-zhou
2007, 22(9): 1417-1422.
Abstract PDF(1760KB) icon1975 icon459
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In order to study the heat transfer characteristics of combined cooling of impingement +reversed convection +film on a flame tube wall,6 test pieces of different geometry were designed.The heat transfer characteristics of the combined cooling were studied by the experimental method using infrared cameras.The experimental results shows that the cooling effectiveness increases with the increase of blowing ratio;between the impingement position and film exit,the cooling effectiveness increases in the direction of main flow,and at a given position the cooling effectiveness decreases with the increase of distance between impingement position and the film exit;beyond the impingement position,the cooling effectiveness decreases in the direction of main flow.At the same wall position,the cooling effectiveness increases with the decrease of the impingement distance.
Research on measurement method of mid-IR spectral radiant intensity of exhaust system with FTIR spectrometer
LUO Ming-dong, JI Hong-hu, HUANG Wei, CAI Xu, GAO Chao
2007, 22(9): 1423-1429.
Abstract PDF(2319KB) icon1949 icon564
Abstract:
The reasons of error occurred in measuring Mid-IR spectral radiant intensity of exhaust system with Fourier transform infrared(FTIR) spectrometer was discussed through theoretical analysis and experimental research.A simple and efficient measurement method was also planned to measure the spectral radiant intensity of a blackbody and a hot plume.The results show that Mid-IR spectral radiant intensity of exhaust system could be measured effectively by this method,thus offering a high value of engineering practicability.
Influence of density ratio and velocity ratio upon the cooling effect of flat panel film
LI Li, PENG Xiao-feng, WANG Bu-xuan
2007, 22(9): 1430-1434.
Abstract PDF(844KB) icon1713 icon424
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An investigation was conducted to explore the influence of density ratio and velocity ratio of mainstream/injectant upon the cooling effect of flat plane film using heat-mass transfer analogy.The injectant is air in the case of density ratio of 1.0,or heterogeneous gas in the case of density ratio of 1.5 and 2.0.The inclined angle between injectant and mainstream is 35° and the hole spacing is 3 times film hole diameter.The results indicate that,the spreading of injectant is controlled through the protected wall surface for a low velocity ratio,and controlled by convection for a high velocity ratio.With the increase of mass flux ratio,the transverse and longitudinal spreading could be expanded,thus increasing effectively the protective range;the reattachment point will move towards the downstream with the increase of momentum ratio under high velocity ratio.
Computational analysis of fluidic vector control concepts for binary nozzle
ZHANG Xiang-yi, WANG Ru-gen, XU Xue-miao, ZHOU Min
2007, 22(9): 1435-1438.
Abstract PDF(550KB) icon1625 icon465
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The full-flow field of a certain 2DCDN(2-dimensional convergence-diffusion nozzle) with two fluidic thrust vectoring concepts was simulated numerically by using 3D Reynolds average N-S equation and RNG k-ε turbulence model.The calculated results show that,the effect of flap injector position on the nozzle vectoring efficiency is consistent under shock vector control and fluidic throat skewing package.The bigger vector angle could be obtained as the injector position approaches the nozzle outlet.When the same jet flux is injected from the same position,the total pressure loss of throat skewing concept is less than that of shock vector control concept,since the main nozzle under throat skewing concept can achieve subsonic turning.
Numerical simulation of 3-D flow field in an aeroengine combustor nozzle-loop
WANG Fei, LEI Yong, YANG Hua
2007, 22(9): 1439-1443.
Abstract PDF(569KB) icon1947 icon422
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According to the structural characteristic of the nozzle-loop,a grid calculation model of nozzle-loop was generated by using tetrahedral unstructured grid and thin & thick grid meshing method.And,numerical simulation was performed for the 3-D flow field of nozzle-loop,providing in detail the interior flow characteristic of single nozzle and the outflow flux of nozzle-loop.The results lay a firm basis for further research of nozzle-loop's flux distribution trait.
Numerical study of a 3.5-stage axial compressor at on-and off-design conditions
Zhuo Wang
2007, 22(9): 1444-1454.
Abstract PDF(1570KB) icon1565 icon479
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Numerical investigation is conducted on a 3.5-stage axial compressor,on which numerous experimental projects were carried out at the Institute during the last years and an experimental database was established.In the current study five on-and off-design operating points are simulated using a RANS solver and the results are compared with the measurement.The result shows that the compressor performance can be qualitatively predicted by the mixing-plane method.Better agreement is obtained for the on-design operating point.However,as the flow unsteadiness is insufficiently considered,the numerical method produces end-wall low-speed flow layers accumulated with the flow passing through the passage,which is in no good agreement with the experimental data.In the numerical simulation the rotor rows receive less work and this difference from the measurement increases with the rotational speed.In contrast,the stator rows increase the pressure more efficiently than the measurement.In the simulation the flow in the last stator row tends more to separate on the pressure side of the blade.For the operating points close to the surge line,the predicted separation is more intense than the experimental observation.But for the operating points close to the choke,the separation is suppressed.
Identification of vortices in a transonic compressor flow and the stall process
HUANG Xu-dong, CHEN Hai-xin, FU Song, David Wisler, Aspi Wadia, G. Scott McNulty
2007, 22(9): 1455-1460.
Abstract PDF(1102KB) icon1235 icon485
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A novel vortex identification method for the visualization of the flow field is used for the study of the stall process of a transonic compressor.The parameter η4,which is one of the five invariants formed by the stain rate and vorticity tensors from the theory of modern rational mechanics,is found to have good ability to identify vortex stretching and vortex relaxation/breakdown processes,is introduced here to identify the tip leakage vortices.Compare with former generally used DPH(dynamic pressure head) contour,the new method reveals much more flow details which may advance our understanding of the compressor behaviors.The Vortices details are revealed in both peak efficiency and near stall condition.A possible stall process is also suggested based on the vortices analysis.The tip leakage flow from mid-chord,besides leading edge leakage flow,is also considered to play an important role in the stall process.
Nonlinear dynamic analysis on post-stall transients of axial-flow compressor
CHEN Ce, NIE Chao-qun, LI Jun
2007, 22(9): 1461-1467.
Abstract PDF(688KB) icon1606 icon466
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To study the effect of Greitzer B parameter and throttle parameter γ on post-stall behavior of axial flow compressor,the static bifurcation behavior for post-stall of axial flow compressor was analyzed using bifurcation analysis method.In the γ-B bifurcation parameter space,the sketch map for steady and unsteady flow of compressor was plotted out.It is thus concluded that nonlinear bifurcation analysis can accurately capture typical post-stall transients and easily analyze the change of stability of system equilibriums under bifurcation parameters.
Numerical research on influence of rotor-stator interactions in transonic compressor
MAO Ming-ming, SONG Yan-ping, WANG Zhong-qi
2007, 22(9): 1468-1474.
Abstract PDF(1419KB) icon1695 icon501
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The unsteady flow field of a single stage axial transonic compressor at a design point was simulated numerically,and an in-depth analysis of rotor-stator interaction was performed.Moreover,the influences of upstream wakes and potential effects on downstream blade loading distributions were investigated extensively.The results indicate that,under stage environment,upstream wakes have obvious influences on generation,evolution and transportation of flow losses,and also on loading distributions of downstream blade.Therefore,consideration shall be given to this effect in the design of turbomachinery.
Unsteady numerical analysis for casing treatment
TU Bao-feng, HU Jun, WANG Yong-ming
2007, 22(9): 1475-1480.
Abstract PDF(1312KB) icon1726 icon483
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The improved effect of casing treatment in axial compressors was studied by using an unsteady simulation method.Numerical calculation was performed for the cavity casing treatment with oblique slots under one-rotor and one-stage environment as well as for axial slots casing treatment of Rotor 37.The influence of downstream stator upon casing treatment simulation was also analyzed.The results show that,this computation method could simulate unsteady casing treatment,but the casing treatment cannot extend the stall margin of a compressor until the dangerous section is near the tip of rotor blade.It's found that the real role of casing treatment cannot be manifested accurately under one-rotor environment,and the presence of downstream stator would change the dangerous section of upstream rotor.
Off-design performance prediction of multi-stage transonic axial compressor
DU Wen-hai, WU Hu, HUANG Jian
2007, 22(9): 1481-1486.
Abstract PDF(878KB) icon1921 icon478
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A new loss and deviation model suitable for multi-stage transonic axial compressor was developed according to the research findings publicly available.Along with 3-D modification,numerical simulation was performed for two-stage transonic axial compressor using an improved streamline curvature method,thus obtaining the characteristic curve of design point and off-design point.By combining the calculated results with experimental value,this model and method are suitable for engineering calculation with higher accuracy of design point and off-design point.
Numerical research on a new non-axisymmetric endwall profiling method
ZHENG Jin, LI Guo-jun, LI Jun, ZHANG Xiong-wen
2007, 22(9): 1487-1491.
Abstract PDF(791KB) icon1649 icon424
Abstract:
Based on the mechanism of secondary flow formation and development in a turbine cascade,SINE function and polynomial function were applied to develop a non-axisymmetric endwall profiling method.Three-dimensional Reynolds-Averaged Navier-Stokes solution was used to study the flow characteristics of the transonic linear turbine cascades designed by non-axisymmetric endwall profiling method.And,the effect of this method and its influence on the flow characteristics of cascade were analyzed and discussed.The numerical results show that,the established non-axisymmetric endwall could suppress and delay efficiently the development of secondary flow vortex system in the cascade passage,and the total pressure coefficient along entire cascade passage declines remarkably.The maximum amplitude of the profiling method is preferably set to 7.5% span,and the total pressure loss at exit reduces by 5.6%.
Application of PSE method into aft-load cascade boundary stability analysis and transition prediction
DONG Xue-zhi, YAN Pei-gang, HAN Wan-jin
2007, 22(9): 1492-1498.
Abstract PDF(1026KB) icon1650 icon441
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The stability and transition of aft-load blade was analyzed and predicted by combining numerical calculation and experimental measurement.Parabolized stability equation(PSE) of 3D disturbance wave was deducted under orthogonal curvilinear coordinates.The static pressure distribution on blade surface was measured in wind tunnel test,and this result was used for analysis of blade's flow stability.The results show that:(1) aft-load blade can delay efficiently the transition and enhance the variable incidence of blade;(2) the positive incidence is most unsteady and negative incidence is most steady in the event of significant change of flow characteristics of blade tip.
An off-design method of turbine blade based on multiobjective optimization
SONG Li-ming, LI Jun, FENG Zhen-ping, LUO Chang
2007, 22(9): 1499-1504.
Abstract PDF(503KB) icon1609 icon444
Abstract:
The off-design concept based on multiobjective optimization was introduced into turbomachinery cascades optimization.And,the energy optimization method was applied to develop a 2D blade fairing method and a new automatic blade design parameterization method.By combining parallel multiobjective differential evolution algorithm and CFD technique,an off-design aerodynamic optimization method was developed.Thus,the off-design aerodynamic optimization of a turbine blade was studied under the subsonic condition and transonic condition.The result indicates that this design method can help to get several blades profiles of good aerodynamic performance suitable for different working condition,presenting strong design capability and higher engineering practicability.
Influence of periodic disturbance on statistic character of turbulent boundary layer
WANG Guo-hua, JIANG Nan
2007, 22(9): 1505-1511.
Abstract PDF(1347KB) icon1578 icon442
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Simultaneous time sequence of lorgitudinal and normal velocity components with and with out periodic blow-suction disturbance had been measured by IFA300 constant temperature anemometer and X-type hot-wire probe at different normal positions along the turbulent boundary layer.A latitudinal thin slot in 5 mm width was incised on a smooth flat plate.The periodic blow-suction force with different frequency was applied to turbulent boundary layer from a speaker woofer under the plate.The quantitative influence of local periodic blow-suction disturbance with different frequency on statistic character of turbulent boundary layer had been investigated.
Large eddy simulation of scalar mixing in a 3D supersonic mixing layer
SUN Ming-bo, FAN Xiao-qiang, LIANG Jian-han, WANG Zhen-guo
2007, 22(9): 1512-1517.
Abstract PDF(774KB) icon1931 icon442
Abstract:
Large eddy simulation was conducted to study the scalar mixing of a 3D supersonic shear layer with convective Mach number 0.62.Governing equations of large scale eddy were solved with fifth-order WENO scheme,and effect of small scale eddy was simulated by using localized dynamic kinetic subgrid scale model(LDKM).The subgrid convective species flux in the filtered species equation was modeled using gradient diffusion method.The results reveal the evolution of the vortex structure of the mixing layer and the scalar field.Simulations show that coherent structures dominate the scalar mixing and the instantaneous distribution of scalar field exhibits obvious 3D characteristics.Statistics such as mean and the root mean square(RMS)of the velocity and the scalar field compares well with the experimental measurements.
Analysis of secondary flow vortex structure and losses in turbine cascades
LIN Qi-yan, ZHENG Qun, YUE Guo-qiang
2007, 22(9): 1518-1525.
Abstract PDF(2225KB) icon1809 icon609
Abstract:
Numerical simulation about the first stage of a power turbine was performed using 3D viscous code,showing that the details in this turbine stage were captured.And,the flow characteristics of endwalls and blade surfaces for these cascades and the structures of 3D flow field were also presented.After analysis of secondary flow phenomenon and loss mechanism,the evolution process of secondary flow vortex structures in cascade passage(horseshoe vortex,passage vortex,corner vortex,trailing vortex,tip leakage vortex,etc) were revealed,and the effects of vortex structures on loss distribution were also studied.
Experimental analysis of low-cycle and creep fatigue for directionally solidified DZ125 with a hole
ZHOU Tian-peng, YANG Xiao-guang, HOU Gui-cang, SHI Duo-qi, CONG Pei-hong
2007, 22(9): 1526-1531.
Abstract PDF(704KB) icon1826 icon459
Abstract:
A low-cycle/creep fatigue test was conducted for directionally solidified DZ125 component with a hole under high temperature conditions.The purpose of this test was to simulate hollow turbine rotor blade for film cooling of aeroengine.The test scheme was planned according to geometric characteristics,temperature and load conditions of hollow turbine rotor blade.The test scheme and test results were described,covering ser-vice life analysis,crack expansion analysis and metallographic analysis.The results show that holes' stress con-centration and creep are major contributing factor to the damage of components,and electric discharge machine(EDM) hole features is decisive to the crack initiation.
Reliability-robust design of compressive bar under incomplete probability information
HE Xiang-dong, ZHANG Yi-min, WEN Bang-chun
2007, 22(9): 1532-1536.
Abstract PDF(346KB) icon1636 icon438
Abstract:
Based on the reliability design theory and the robust design method,the reliability-based robust design of compressive bar under incomplete probability information was extensively discussed,and a numerical method for stable reliability-based robust design was proposed.The reliability sensitivity was added to the reliability-based optimization design model,while the stable reliability-based robust design was described as a multi-objection optimization.If first four moments of basic random variables have already been known,the computer program can be used to obtain accurately and quickly the stable reliability-based robust design information of compressive bar under incomplete probability information.
Stability and bifurcation of symmetrical rotor in self-acting gas journal bearings
KANG Wei, ZHANG Jia-zhong, LIU Yan, REN Sheng
2007, 22(9): 1537-1543.
Abstract PDF(984KB) icon2088 icon435
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Based on the nonlinear dynamics theory,the stability and bifurcation of a symmetrical rotor supported in self-acting gas bearings were studied.A dynamic model of self-acting gas journal bearings and Jeffcott rotor system was established,meanwhile the finite element method was used to approach the time-dependent Reynolds equation,thus obtaining the gas film force.Furthermore,the longterm nonlinear dynamic behaviors of the system were simulated numerically,so the system state trajectory of journal center was acquired.Moreover,the system state trajectory,phase diagram,bifurcation diagram and power spectrum were adopted to analyze the nonlinear behaviors of system and the stability of unbalanced response.The results show that this method could give a deep understanding of whirling instability of the gas film bearings-rotor system.
Application research of damage dynamics for low cycle fatigue test
ZHANG Guo-dong, YU Hui-chen, HE Yu-huai, SU Bin
2007, 22(9): 1544-1549.
Abstract PDF(646KB) icon1833 icon436
Abstract:
The change of elastic modulus and stress associated with fatigue cyclic number was investigated during low cycle fatigue.The research shows that,the low cycle fatigue damage can be determined by the change of elastic modulus and stress.For the materials,which have no cyclic steady stage but exhibit cyclic softening,this method isn't suitable to determine the low cycle fatigue damage with the change of stress.The fatigue crack initiation life was acquired by the change of elastic modulus under different strain levels,so the relationship between strain and fatigue crack initiation life was determined by three parameters power equation.
Analysis of contact pressure between boltless baffle and blade
LUAN Yong-xian, LUO Gui-huo
2007, 22(9): 1550-1553.
Abstract PDF(505KB) icon1657 icon421
Abstract:
The changing relation among the penetration and turbine angular velocity,the fore-and-after pressure difference of back boltless baffle and pressure of blade imposed on the baffle was discussed based on the finite element platform.The equation of the relation mentioned above was established by the least square method.According to the deformation coordination of baffle and turbine,the relational equation of rotational speed,fore-and-after pressure difference of boltless baffles and available pressure was concluded.
Multi-objective optimization of centrifugal pump impeller for conceptual design
ZHENG Yun-tao, CAI Guo-biao, CHEN Jun
2007, 22(9): 1554-1559.
Abstract PDF(1565KB) icon1621 icon382
Abstract:
Two multi-objective optimization methods were applied to design the centrifugal oxidizer pump impeller for liquid propellant rocket engine.Major geometric parameters of pump impeller were optimized for the targeted delivery head,efficiency and mass of pump.The Pareto Front of multi-objective optimization was gained by Neighborhood Cultivation Genetic Algorithm(NCGA);the super-transitive approximation method was introduced to acquire optimal weights of individual objectives.Then,Evaluation Function method was used to obtain optimal design of multi-objective optimization.The effects of major structural parameters on pump performance parameters were also analyzed.
Aerodynamic analysis and wind tunnel testing on maglev launch assist
CHEN Xiao-dong, YANG Wen-jiang, LIU Yu, DUAN Yi
2007, 22(9): 1560-1564.
Abstract PDF(576KB) icon1751 icon446
Abstract:
The aerodynamic characteristics of a maglev(or magnetic levitation) launch assist vehicle were analyzed and rational design principles for its aerodynamic shape were proposed.The aerodynamic shape configuration for the maglev sled as well as for the support and separation structure was analyzed and the optimal values of design parameters were obtained.A wind tunnel testing for a scale model was made in the FD-06 wind tunnel,in which simulation ground effect was considered.The results show that the lift and drag coefficient increases along with the increase of Mach number or the attack angle of the space vehicles.The launch assist vehicle has a tendency to face upward.When the attack angle is zero,the drag coefficient is relatively small and the variation of each coefficient is relatively small too.
Research on influence of diameter ratio and length-diameter ratio on structural integrity of solid propellant under temperature loading
YU Yang, WANG Ning-fei, ZHANG Ping
2007, 22(9): 1565-1568.
Abstract PDF(1032KB) icon1836 icon468
Abstract:
To investigate the influence of number m and length-diameter ratio on structural integrity of solid propellant under temperature loading,the thermoviscoelastic large deformation incremental constitutive equation was derived from Total Lagrangian method.Nine different numbers m and eight length-diameter ratios for calculation 72 models were selected to measure the effects on the structural integrity.The results show that,number m and length-diameter ratio have cooperative effects on the maximum value of equivalent Von Mises stress and strain.If the length-diameter ratio is larger than 3,it's concluded that the maximum value of equivalent Von Mises stress and strain are mainly determined by number m of solid propellant.
Optimization of response surface of secondary gas injection thrust vector control
WU Xiong, WANG Zhong-wei, JIAO Shao-qiu, ZHANG Wei-hua
2007, 22(9): 1569-1572.
Abstract PDF(284KB) icon1787 icon433
Abstract:
The secondary gas injection thrust vector control system of a test engine was optimized using partial orthogonal-polynomial based response surface methodology (RSM) along with numerical simulation.The results show that such optimization method could reduce and save the calculation time of primary/secondary interference flow field for approximate functional equation,and enable you to optimize and analyze easily the parameters of secondary gas injection system.
Optimizing control of turboshaft engines based on variable rotor speed
YAO Wen-rong, SUN Jian-guo
2007, 22(9): 1573-1577.
Abstract PDF(707KB) icon1859 icon439
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The integrated optimization of turboshaft engine/rotor was studied to analyze the relationship between power requirement of helicopter and the operating status of turboshaft engine,and the effect of the rotor revolutions per minute(RPM),collective,longitudinal cyclic and lateral cyclic on the power requirement of the helicopter.Linear programming(LP) was used to optimize the turboshaft engine/rotor performance by taking the minimum power requirement of rotor as the objective function.Meanwhile,digital simulation test was conducted for optimization of turboshaft engines with variable rotor speed in cruising state.The simulation results show that,the fuel consumption could decrease by 1.5%5.5% and the turbine temperature decrease by 4.416 ℃ after optimization of turboshaft engine with variable rotor speed in cruising state.
Optimization of turbine disk based on particle swarm optimization and neural network
YIN Yi-yun, GUO Hai-ding
2007, 22(9): 1578-1582.
Abstract PDF(1677KB) icon1858 icon441
Abstract:
A new computational intelligence method was established by combining particle swarm optimization(PSO) and back propagating(BP) neural network.In addition to structural optimization,PSO is also used in BP neural network's construction and training,thus enabling self-adaptive optimization.In the structural optimization,the neural networks were used to map object function and constraints instead of finite element method(FEM),helping to accelerate greatly the computation speed.A disk model was optimized to decrease its volume by 17.5%.The results show that,this convenient and efficient method will provide a new approach to structural optimization.
QFT control of aeroengine through LMI-based diagonal dominance pre-compensation
LI Hua-cong, HAN Xiao-bao, WU Zhi-kun
2007, 22(9): 1583-1587.
Abstract PDF(594KB) icon2027 icon446
Abstract:
Based on linear matrix inequalities(LMI) and quantitative feedback theory(QFT),a new design method of aeroengine robust controller was developed for uncertain mathematical model of aeroengine.The method has combined the design problem of frequency domain diagonal dominance pre-compensator and the solving process of LMI,thus achieving the decoupling of uncertain control objects.Moreover,a robust controller was designed with induction of QFT.The simulation results show that this method has good control efficiency and engineering applicability.
Optimization methodology of PID controller parameters for aeroengines based on mixture genetic algorithm
CAO Zhi-song, PIAO Ying
2007, 22(9): 1588-1592.
Abstract PDF(1281KB) icon1630 icon423
Abstract:
Based on the mathematical model of aeroengine,an optimization methodology of the PID controller parameters with genetic algorithm(GA) was developed.This optimization methodology is a global optimization and has nothing to do with initial values.Mixture genetic algorithm fusing the advantage of steeply convergence and highly precession of simplex algorithm and global convergence of genetic algorithm,is used to improve the searching process and precision.The result shows that the algorithm has good convergence and steadiness.

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