2008 Vol. 23, No. 6

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Fan/compressor aero design trend and challenge on the development of high bypass ratio turbofan
CHEN Mao-zhang, LIU Bao-jie
2008, 23(6): 961-975.
Abstract PDF(3103KB) icon3249 icon691
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Trent of fan/compressor aero design technologies for the development of high bypass ratio turbofans are analyzed,and the challenges that would be encountered in the development of out high performance large bypass ratio turbofan are discussed.Finally,some key technologies that need to be breakthrough are proposed.
Summarization of development status and key technologies for large airplane engines
LIU Da-xiang, JIN Jie, PENG You-mei, HU Xiao-yu
2008, 23(6): 976-980.
Abstract PDF(619KB) icon2212 icon555
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The development status and trends of military and civil high bypass pressure ratio(BPR) turbofan engines for large airplanes has been summarized in the paper.In the aspects of strategical goals,importance and marketing foreground of the high BPRturbofan engines for national large airplanes engineering in China,the requirements,status and gaps of high BPRturbofan engines in China have been analysis briefly as well as the introduction of the overall engine scheme for the high BPRturbofan engines with the main key technologies for the engines.In terms of military and civil high BPRturbofan engines technologies,international cooperation,materials and techniques and test facilities,some suggestion and approach have been discussed for the technical challenges with the development of high BPRturbofan engines in China.
Significant impact of engine technical innovation on airplane performance advancement
CHEN Da-guang
2008, 23(6): 981-985.
Abstract PDF(556KB) icon1988 icon489
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The innovation of propulsion technology used to be and will be continuously to be the primary motive power to the advancement of air transportation.To develop large passenger plane,it is necessary to recognize the role played by the engine technical progress on the advancement of airplane performance.The new engine GEnx for Boeing dreamliner B787 developed by general electric aircraft engines(GEAE) was used as an example to analyze the impact of new engine technology on airplane efficiency,environment pollution,intelligent airplane,low cost and comfort of riding.At last,based on the experiences of technical development in foreign countries,some suggestions of the way to develop our engine technology were proposed.
Pollutant emission and development of low-emission combustion technology for civil aero engine
ZHAO Jian-xing
2008, 23(6): 986-996.
Abstract PDF(1870KB) icon2535 icon647
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Directed against the pollutant emission status of civil aero engine,the development of low-emissions combustion technology described is done.The standards for international civil aviation organization(ICAO) aircraft engine emissions and regulations of civil aviation administration of China(CAAC) exhaust emission are given.The formation mechanisms of exhaust emissions are summarized.Various factors influencing pollutant formation and improved approaches decreasing exhaust emission are discussed.The key features,combustion concept and application of six advanced low-emissions combustors(staged,variable geometry,and catalytic combustor,lean premixed prevaporized(LPP),rich-burn,quick-mix,lean-burn(RQL) and twin annular premixing swirler(TAPS)) are detailed.In these low-emission combustors,staged combustor is the foundational design scheme LPP,RQLand TAPScombustors have widely developed perspective.Some novel low-emission combustion concept,such as lean direct injection,fuel cell and active combustor control are recommended.These new low-emissions technology are very useful,however many formidable problems remain to be solved before the systems can be applied to advanced aircraft engines.
Critical starting characteristics of hypersonic inlets
WANG Cheng-peng, CHENG Ke-ming
2008, 23(6): 997-1002.
Abstract PDF(610KB) icon2036 icon502
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An airbreathing hypersonic vehicle model was tested in the Ma=7 wind tunnel.The experimental investigations yielded schlieren pictures of the inlet flow,static surface pressure measurements along inlet/internal flowpath and aerodynamic force distributions.The flow field characteristics were achieved,such as: unstarting hypersonic inlet,critical starting and starting condition.The ability of isentropic limit,Kantrowitz limit and Van Wie limit to predict the starting contraction ratio was assessed,showing that the isentropic limit and Van Wie limit could not estimate the allowable starting and maximum contraction ratio.The Kantrowitz limit is slightly conservative.The above results are helpful to the design of the hypersonic inlet and the assessment of starting performance.
Numerical simulation of shock wave/flat-plate turbulent boundary-layer interaction
LI Zhi-qiang, LI Zheng-qiang, YAN Wen-hui
2008, 23(6): 1003-1007.
Abstract PDF(1732KB) icon1883 icon489
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Rational Gao-Yong compressible turbulence model was used to simulate numerically the shock wave/flat-plate turbulent boundary layer interactions.The results show that the computational results of the pressure distribution along the wall surface,skin-friction coefficient distribution along the wall and the velocity profile distribution along x-coordinate are consistent with the experimental results.And the computational results predict well the flow characteristics of flat-plate turbulent boundary layer separation induced by incident shock wave.Hence,it is shown that when the Gao-Yong compressible turbulence model is applied to simulate the shock wave/turbulent boundary layer interaction,the detailed flow characteristics of shock flows can be well predicted.
Quasi-3D simulation of aero engine full flow field
YU Long-jiang, CHEN Mei-ning, PIAO Ying
2008, 23(6): 1008-1013.
Abstract PDF(558KB) icon1827 icon488
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Mathematical models for each component of aero engine based on S2 surface theory were analyzed.Afull engine S2 flow simulation was performed using this method.High order Godunov's scheme was used,presenting good numerical stability and shock capturing capability.Viscous effects and secondary flow losses were treated as source terms.Their influence on the components and full engine system's performance were estimated effectively.Aconservative process was taken to handle the parameter transfer between neighboring domains,ensuring the consistency of flux.The method features high accuracy by comparing the simulation and experimental results.
Experimental investigation on the starting characteristics of a hypersonic inlet with moving entrance door
WANG Yi, FAN Xiao-qiang, LIANG Jian-han, LIU Wei-dong, WANG Zhen-guo
2008, 23(6): 1014-1018.
Abstract PDF(550KB) icon1591 icon513
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A three dimensional hypersonic inlet with moving entrance door was designed and tested in the Ma=6 free-jet wind tunnel to investigate the starting characteristics.This variable geometry design was testified to be a feasible way to accomplish the entrance opening process of the inlet.The results reveal that the moving entrance door can effectively improve the starting ability of the inlet.The gradually opening process could assist the inlet in starting and also avoid the hysteretic effect of the inlet selfstart.
Aerodynamic optimization of transonic cascade using global aerodynamic optimization method
SONG Li-ming, LUO Chang, LI Jun, FENG Zhen-ping
2008, 23(6): 1019-1023.
Abstract PDF(1190KB) icon1461 icon545
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A global aerodynamic optimization method was proposed for three-dimensional cascade design.The method was applied to the NASA Rotor 37,which was a test transonic compressor cascade representing complex three-dimensional viscous flow structures.The capability of the computational fluid dynamics(CFD) code was validated by comparing the computed results with experimental data available in the open literature.The transonic cascade was optimized for the maximization of the isentropic efficiency under given flow conditions,using constraints on the mass flow rate and the total pressure ratio.The isentropic efficiency of the optimized design was 1.66% higher than that of the reference design,showing a better aerodynamic performance and better off-design performance.It shows that the shock losses of the transonic cascade could be reduced by optimizing the profiles of the transonic cascade and its radial stacking mode.
Influence of magnetic plasma on performances of the convergent nozzle
ZHANG Yan, HUANG Hu-lin
2008, 23(6): 1024-1030.
Abstract PDF(1255KB) icon1618 icon451
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The characteristics of flow and heat transfer for plasma controlled by external magnetic fields in the convergent nozzle and the jet wrapped by the plasma were simulated using the models of magnetic induction equation,the multiphase flow mixture and modified turbulent two-equations under magnetic forces.The results show that the plasma volume fraction decreases with the acceleration of flow in the convergent nozzle.Magnetic intensity increase may improve the plasma volume fraction near the wall and suppress its turbulence strength,thereby cutting down the increase of nozzle wall temperature effectively.The rising wall temperature is reduced by 54.4%,the thrust coefficient is increased by 0.74% and the jet is still wrapped at 4D* from the nozzle exit after applying the 1.3 Tmagnetic field.
Uncertainty of quality being produced in the course of manufacture management of aerospace power system
MAO Jing-li
2008, 23(6): 1031-1040.
Abstract PDF(2068KB) icon1641 icon441
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The quality forming has a big uncertainty,which is the basic feature in the course of manufacture of aerospace power system.First,the factors that caused the uncertainty were analyzed.Then,the schemes that would delete the uncertainty of quality was given,which was to build supervising mechanism,encouraging mechanism and binding mechanism.
Numerical study on combination flow field of axisymmetric convergent-divergent nozzle under transonic and supersonic conditions
HU Hai-yang, WANG Qiang
2008, 23(6): 1041-1046.
Abstract PDF(1004KB) icon1548 icon551
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Finite volume method and second order Roe's scheme are employed to discretize the three-dimensional N-Sequation.Lower-upper symmetric Gauss-Seidel(LUSGS) implicit time stepping method and multigrid technique are employed to accelerate convergent rate.Different turbulence models and wall function are applied to 3Dnumerical simulation of internal-external flow field of axisymmetric nozzle.The comparison with experimental data shows that the most accurate results can be obtained by the means of RNGmodel coupled with eddy viscosity formula,and by using enhanced wall functions for inner wall treatment and standard wall functions for outer wall treatment.The final calculation data are summarized,the pressure distribution of nozzle's outer wall at different NPR(nozzle pressure ratio) and Mach numbers are compared under transonic and supersonic conditions.
Modification design and flowfield analysis of a centrifugal turbine stage with discrete nozzles
LIU Jing, SHAN Peng
2008, 23(6): 1047-1053.
Abstract PDF(1036KB) icon1203 icon428
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For an air turbine with high loading,low rotational speed and greater torque output single-stage startup,aerodynamic analysis of prototype and aerodynamic modification design were conducted for achieving a more powerful shaft-power output.This turbine employed a centrifugal flow path,discrete nozzles and an impactive rotor.The flowfield analysis indicates that,this turbine has a very high loading coefficient,rather than a high adiabatic efficiency.Atechnical package was adopted in the modification design of increasing mass flow with almost the same turbine inlet total pressure.The flowfield simulation indicates that,when the rotor′s diameter is reduced to 94% of the original turbine,the power output of the modified turbine is about 2 times and 2.8 times of the original one at both the rotational speed of 100% and 140% of the original one.
Numerical research of two-dimensional flow-path in ram-rotor
HAN Ji-ang, YAN Hong-ming, ZHONG Jing-jun, SUN Peng, YU Yang
2008, 23(6): 1054-1060.
Abstract PDF(2304KB) icon1650 icon478
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According to the design method of 2D supersonic inlet,a kind of 2Dflow-path of a ram-rotor is designed.The 2D Reynolds-averaged Navier-Stokes equations and the Spalart-Allmaras turbulent model are adopted to simulate the flow field of the designed 2Dflow-path of the ram-rotor.The influence of rotational speed and the back pressure on the structure of shock wave,the characteristic of inner flow and the performance of the ram-rotor are researched.It has been found that the design method of the ram-rotor flow-path presented in this paper is feasible.The shock wave system in the flow-path is similar to that in the 2Dsupersonic inlet.The difference is that the shock wave in the flow-path is curve shock wave,and the shock wave in the 2Dsupersonic inlet is line shock wave.The back pressure and the rotational speed have great influence on the performance of the 2Dflow-path.
Experiment and design improvement of an axial flow blood pump
ZHAN Zhao, ZHANG Yan, GUI Xing-min
2008, 23(6): 1061-1066.
Abstract PDF(823KB) icon1794 icon456
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The numerical investigation and experimental results of the proto-pump LAP-00 show that at design rotational speed of 9000 r/min,the flow rate corresponding to the highest efficiency point is 11 L/min,which is much higher than clinical use(38 L/min),causing the pump to work at off design point in clinic use with a low efficiency.Besides,in the diffuser region,flow separation and recirculation may cause blood stagnation and thrombosis.The improved design for pump LAP-23 decreases the design rotational speed from 9000 r/min to 8000 r/min,thus reduces the high shear stress on blood cells at impeller tip;meanwhile,it decreases the design flow rate to 6 L/min and eliminates flow separation and recirculation in the diffuser region.
Role of tip leakage flow on flow instability and its control with circumferential groove casing treatment
WANG Pei, ZHU Jun-qiang, HUANG Wei-guang
2008, 23(6): 1067-1071.
Abstract PDF(1016KB) icon1652 icon533
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In order to provide a state-of-the-art understanding of the flow field in axial-flow compressor in the perspective of enhancing its stability by using passive means,the detailed tip flow structure and inception of rotating stall were measured in a subsonic compressor rotor with high response pressure transducers.The inception of spike-type rotating stall that correlated with the tip leakage vortex was detected in this compressor.The physical processes occurring when approaching stall and the role of complex tip flow mechanisms on flow instability in current subsonic compressors were assessed by using time-accurate single blade passage computations.Based on these observations,circumferential groove casing treatment was introduced to control the tip leakage flow;and the physical mechanism responsible for stall margin improvement attributed to circumferential groove casing treatment was explored.
Improved streamline curvature throughflow method and its application in a bypass compression system design
SHAO Fu-yong, YANG Jin-guang, LIU Zhen-de, HU Jun
2008, 23(6): 1072-1076.
Abstract PDF(518KB) icon2047 icon482
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Based on axisymmetric S2 stream surface theory,a streamline curvature throughflow method is presented in this paper.Improvements on streamline curvature calculation and relaxation factor determination were made,which enhanced the convergence,stability and precision of this method.Asimple blade force handling method was also proposed for computing flow field in the blade passage.At the same time,a bypass compression system computational method was integrated,which was stable and fast,and which enabled this method to solve arbitrary regions in bypass compression systems composed of fans and any type of high pressure compressors(axial-flow,centrifugal and combined type etc.).Finally this method was applied to an inverse design of a fan/high pressure compressor system,which demonstrated its validity.
Effect of slot width on the aerodynamic performance of compressor cascade
ZHOU Min, WANG Ru-gen, ZENG Ling-jun, ZHAO Ying-wu
2008, 23(6): 1077-1081.
Abstract PDF(1122KB) icon1975 icon477
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The effect of slot width on aerodynamic performance of compressor cascade was studied numerically.The result shows that slot outlet jet on the suction surface can blow off the boundary layer flow on the trailing edge of blade;and all the flow control solutions using blade slot treatment,though of different slot widths,can enhance cascade performance.Corresponding to the maximum enhancement of cascade performance,an optimal slot width exists.As the slot width increases,jet flow and effect area are increased,but the flow loss at the slot outlet also increases.Therefore,the effect of jet is reduced and the performance of cascade with large slot width drops.
Way to evaluate fatigue life of fillet weld of plate with flange based on stress field intensity
GUO Hai-ding, WU Qi
2008, 23(6): 1082-1086.
Abstract PDF(1263KB) icon1731 icon406
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The fatigue behavior of welded joint has local damage characteristics.Based on stress field intensity(SFI) theory,the field diameter of fillet welded joint was analyzed,and the stress field intensity at the weld toe of fillet weld joint of flange was calculated using elastic-plastic finite element method.Based on the calculation results and the results of S-Ncurve of smooth specimen of the same material,a fatigue life evaluation of flange fillet welded joint was obtained.The precision of fatigue life prediction with SFImethod is better than the one with the local stress-strain method,and the result is much closer to the experimental result.
Influence of magnetic damper on dynamic characteristics of magnetic bearing system
XIE Zhen-yu, LI Ke-lei, ZHAO Qing-quan, HUANG Pei-zhen
2008, 23(6): 1087-1092.
Abstract PDF(1325KB) icon1526 icon420
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Dynamic characteristics of the system supported by two radial magnetic bearings,one axial magnetic bearing and one magnetic damper are studied in this paper.Compared with the system without magnetic damper,supporting damping of the system increases obviously and the vibration of the system can be reduced effectively,especially when it operates on the first two bending critical speeds.This helps the system to get across the first two bending critical speeds safely and operate on16 000 rotations per minute.
Improved fault diagnosis method for aero engine rotor-sator rubs
HE Tian, LIU Xian-dong, LI Qi-han
2008, 23(6): 1093-1097.
Abstract PDF(2014KB) icon1940 icon486
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In view of actual conditions of aero engine's rub-fault,the application limitations of variant diagnosis methods were analyzed.Aboundary extension method was presented for restraining the ending effect of the reconstructive signals;and an improved method was adapted to process both short time series and long time series based on singularity value decomposition and the boundary extension method.The selective method of singularity values for reconstruction was also discussed.Then the vibrating signals of certain aero engine were analyzed,showing good detection results of fault signals of a certain Aero-engine.
Blade wake excitation caused by twin-shaft engine speed difference
ZHAO Fu-xing, SHI Hai-qiu, YANG Xing-yu
2008, 23(6): 1098-1101.
Abstract PDF(1335KB) icon1811 icon464
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This paper proposed the features of speed difference's change along with high pressure or low pressure rotor speed when twin-shaft engine was used in flight.Apoint of view was presented that speed difference is likely to arouse wake excitation between high pressure and low pressure rotor blade.The features of blade wake excitation caused by speed difference were briefly described through numerical examples.As compared with vane wake excitation,the blade wake excitation caused by speed difference features low stage vibration mode of high hazard exposure,wide resonance speed range and low excitation intensity.
Conservative fuzzy reliability design of engine connecting rod
WANG Tie, WU Jing, ZHOU Shu-wen, ZHANG Guo-zhong, BA De-chun
2008, 23(6): 1102-1105.
Abstract PDF(348KB) icon1235 icon432
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In consideration of the strength and safety,both distribution's density and function's density were integrated to induce the conservative fuzzy reliability design formulas about engine connecting rod,namely,the stress,strength,geometry dimension of component etc,were normally distributed,and subordinate function was obtained from fuzzy reliability design formula in the case of parabola of exponential k;the numeric result about the conservative fuzzy reliability design of engine connecting rod was achieved by VBprogram in the computer.This program can be used in design of connecting rod to improve the level of design.
Numerical analysis of the damage of bird impaction against composite laminates and the influence factors on absorbing energy
YU Lian-chao, CHEN Wei, GUAN Yu-pu, WEN Hai-tao
2008, 23(6): 1106-1110.
Abstract PDF(1398KB) icon1616 icon432
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The numerical analysis is a very important work in the process of design on how composites resist the damage from bird impact.The paper analyzed and tested numerically the initial damage,stress and strain of every layer of laminates from bird impact using instantaneous non-linear FEM.It also analyzed how the changes of ply stacking sequence,parameter of laminates and birds affect the absorbing energy of laminates.The results of this paper provide a basis for further research on composite structures resisting bird impact.
Fault diagnosis for gas turbine engines based on Kalman filter and neural networks
YAO Hua, SHAN Gui-ping, SUN Jian-guo
2008, 23(6): 1111-1117.
Abstract PDF(1636KB) icon2486 icon467
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A method for gas path fault diagnosis of gas turbine engines based on Kalman filter and neural networks was proposed.For the fault diagnosis,the Kalman filter was used to estimate the variations of measurable parameters,while neural network was applied for mapping the variations of performance parameters of gas turbine engines.Digital simulations show that the proposed method is feasible and effective.
Fault diagnosis and adaptive reconfiguration control for sensors in aeroengine based on improved least squares support vector
CAI Kai-long, XIE Shou-sheng, YANG Wei, WU Yong
2008, 23(6): 1118-1126.
Abstract PDF(3082KB) icon1762 icon535
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Amethod of fault diagnosis and adaptive reconfiguration control based on improved least squares support vector machine(LS-SVM) was presented for sensors in aeroengine control system.LS-SVMrobustness was improved by adding weighed values to errors,and its sparseness was improved by clipping algorithm.Some turbofan engine normal models were set up with improved LS-SVM.The threshold discriminance was used to real-timely watch and diagnose sensors fault.Adaptive reconfiguration control for aeroengine was realized by model output which is fed back to closed loop control system in replacement of fault sensor measurements.The simulation results show that the proposed method can exactly diagnose sensor faults in time,and also effectively realize adaptive reconfiguration control.
Extracting algorithm for diagnostic parameters of aero-engine based on fuzzy-rough sets
SONG Yun-xue, ZHANG Chuan-chao, SHI Yong-sheng
2008, 23(6): 1127-1130.
Abstract PDF(635KB) icon1567 icon464
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Extracting diagnostic parameters of aero-engine performance is an essential approach to enhance the validity and the reliability of aero-engine fault recognition.In view of fuzzy and consecutive characteristics of aero-engine fault parameters,an extracting algorithm based on fuzzy-rough sets was put forward and the algorithm was used for fault recognition of one aero-engine.The research result shows that the core attributes of reductions are diagnostic parameters of aero-engine failure,whereby the algorithm ensures high precision of fault diagnosis.The anti-interference ability of the algorithm enhances the validity of fault recognition.The algorithm can be also used for fault classification,fault diagnosis and performance monitoring of aero-engine.
Automatic code generation technology for control method based on RTWEC
LU Jun, GUO Ying-qing, WANG Bin-zheng
2008, 23(6): 1131-1134.
Abstract PDF(828KB) icon1750 icon537
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This paper analyzed automatic code generation technology for complex control of aeroengine with real-time workshop embedded coder(RTWEC),and described the principle and applied method.Automatically generated and manually programmed codes of an areoengine controller's multi-variable control method were comparatively analyzed by Hardware in-the-loop simulation(HILS) of electronic controller.The results show that this feasible technology could reduce the workload of programming,checking,debugging,and also shorten the development cycle,so it can be widely used in the development process of controller's complex algorithm from design and simulation to implementation.
Cold flow research in scramjet combustor
WANG Dian, SONG Wen-yan, LI Jian-ping, CAI Yuan-hu
2008, 23(6): 1135-1140.
Abstract PDF(1461KB) icon1608 icon400
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The scramjet combustor cold flow was researched in Northwestern Polytechnical University direct-connected resistance heated facility.The cold flow experimental was performed,for the designed supersonic combustor model with different isolator length,different combustor inflow and different exit back pressure.The combustor inlet Ma=2.0,inflow m=0.73～1.0 kg/s,total pressure pt≈(7～8)×105 Pa,total temperature Tt=300 K.The cold flow field of the supersonic combustor is also simulated with computational fluid dynamics(CFD) software and is analyzed and compared with experimental results.The experimental and computational results show: The length/height ratio of isolator increases,the capacity of resist back pressure for the scramjet combustor increases.The exit pressure distortion of combustor has greater effect on the internal flow field of combustor.The comparison of computational results and experimental results also verify the applicability of numerical simulation method.
Investigations of the bleed air anti-icing system for an aircraft wing
CHANG Shi-nan, YUAN Mei-ming, HUO Xi-heng, ZHANG Quan
2008, 23(6): 1141-1145.
Abstract PDF(1087KB) icon2053 icon460
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Calculation and analysis for bleed air anti-icing system of an aircraft wing was conducted,Influences of droplet diameter on impinging limits and Mach number on heat transfer coefficient were analyzed.Evaluation of the system's effectiveness at different flight height was conducted.The results showed that impinging limits increased with the droplet diameters increasing,heat transfer coefficient of the wing surface increased with the Mach number increasing,and dry temperature of anti-iced surface was higher than wet temperature under the same conditions.Results for several typical cross sections under different flight conditions indicated: for the given parameters,the system was effective at H=4 km and H=7 km,some wet temperature of anti-iced surface at H=7 km was lower than0 ℃.
Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor
TIAN Hui, CAI Guo-biao, SUN Zai-yong
2008, 23(6): 1146-1150.
Abstract PDF(618KB) icon1909 icon505
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Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide(N2O)/hydroxyl-terminated polybutadiene(HTPB) based fuels hybrid rocket motor.MacCormack decomposition scheme and B-Lalgebraic turbulence model and two-phase equilibrium flow model were used.The nozzle flow and performance under three oxidizer-to-fuel ratios and four nozzle types were calculated.Effect of oxidizer-to-fuel ratio and nozzle type on nozzle performance was analyzed from the two-phase and gas phase results.Vacuum specific impulse is bound up with oxidizer-to-fuel ratio.This paper will be useful for the hybrid rocket motor design.
State parameter image identification method based on fuzzy mathematical morphology and immune intelligence for rotating machinery
DOU Wei, LIU Zhan-sheng, WANG Zheng-xian, HE Peng
2008, 23(6): 1151-1160.
Abstract PDF(2146KB) icon1570 icon483
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Taking the multi-dimensional image information of rotating machinery vibration as the research object,this paper investigated the fuzzy morphology method of directly extracting and mining the texture feature in vibration parameter image of rotating machinery,and then presented a state parameter image identification method of rotating machinery based on fuzzy mathematical morphology and immune intelligence.Using the method of fuzzy mathematical morphology filter to implement image filter,this paper studied fuzzy morphology edge detection operator and extracted the edge texture feature based on the morphology gradient from the vibration parameter image of rotating machinery,and finally diagnosed and identified the image feature using the artificial immune algorithm.On the modeling of 600MWturbine rotor experimental bench,the rotor normal state,unbalanced fault,misalignment fault and steam exciting vibration were tested.The diagnosis result shows that the method can accurately obtain image feature and improve the diagnosis accuracy.

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