2007 Vol. 22, No. 11

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Review of heat transfer enhancement for dimpled surface
LIU Gao-wen, ZHANG Li, GUO Tao
2007, 22(11): 1785-1791.
Abstract PDF(1371KB) icon2062 icon413
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The vortex-based dimple heat transfer enhancement was introduced as a new heat transfer enhancement and cooling technique.The major characteristics include high heat transfer coefficients,low friction factors and high overall thermal performances.After review of research work on heat transfer enhancement with dimple in the last decade,the heat transfer behavior,flow resistance and vortex structures of dimpled surface were presented,and the influence of parameters,such as dimple shape,depth,and Reynolds number,were also discussed. While the thermal performances of dimples in rotating channel,circular tube and impingement target surface were described and compared with that of trip-strip,this paper provides a visibility into the dimpled surface,which is a new and potential heat transfer enhancement technology with wide applications.
Research on principle of self-fit control for fuel supply in pulse detonation engine
FAN Yu-xin, WANG Jia-hua, CAO Meng-yuan
2007, 22(11): 1792-1797.
Abstract PDF(1338KB) icon1609 icon416
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The principle of fuel supply self-fit control in pulse detonation engine was studied by measuring the instantaneous oil pressure curve with the dynamic pressure sensors located on different sites of fuel line during the operation of PDE.The results show that,startup and stop of fuel supply,under fuel supply self-fit control,depends upon gas counter-pressure in PDEand fueling pressure.Fuel supply begins with gas counter-pressure less than fuel supply pressure,and stops in reverse conditions.Under the same equivalent proportion within PDE,the fuel supply time is related only to the fueling pressure,independent of the length of fuel line and working frequency of PDE.The longer the fuel line,the larger the pressure loss is,thus leading to a higher pressure at the exit of bump.
Effect of air and fuel injection patterns in pilot zone on trapped-vortex combustor performance
HE Xiao-min, XU Jin-sheng, SU Jun-qing
2007, 22(11): 1798-1802.
Abstract PDF(1097KB) icon1597 icon464
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The matching relationship between locations of air and fuel injection in cavities is one of the most important parameters of trapped-vortex combustor(TVC).Researches were conducted to evaluate seven groups of air and fuel parameters covering4 injection locations in cavities and 3 mixed air hole locations.The combustion performance test was performed under different injection temperatures and flow rates.So,the relationship among ignition performance,lean blow out(LBO) and efficiency,and 7 groups of air and fuel parameters was obtained,showing that the 7th parameter is an optimal parameter of air and fuel injection in cavities.
Investigation on the detonation initiation by shock diffraction
HAN Qi-xiang, GE Wen, WANG Jia-hua
2007, 22(11): 1803-1807.
Abstract PDF(638KB) icon1658 icon452
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This paper reports on the investigation of detonation initiation by shock diffraction on a set of the single detonation.With kinds of different reflector,the pressure histories and flame propagation velocities in the detonator tube were measured to study the characteristics of detonation initiation.The results indicate that the shock diffraction could prompt the initiation of detonation,and which were affected by the dimension of the cone and plate of reflector.With same blockage ratio of the cone,there has a optimal cone angle where the DDT(deflagration to detonation transition) distance was minimum.The DDTdistance would be lengthened when the gap between the cone and plate was increased,but the pressure of detonation wave was influenced little by the reflector.
Evolution of ultra-thin liquid film in dynamic wetting
WANG Xiao-dong, PENG Xiao-feng, ZHANG Xin-xin
2007, 22(11): 1808-1813.
Abstract PDF(2160KB) icon1600 icon383
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Lubrication approximation was used to analyze the evolution of ultra-thin liquid film in the dynamic wetting of complete wetting fluid at low capillary number. The results indicate that van der Waals forces have an important effect on the interfacial profile of the ultra-thin liquid film in the vicinity of the apparent contact line.For repulsive van der Waals forces,the disjoining pressure is larger than zero,and the vapor pressure outside the interface is higher than the pressure of the liquid film.The thickness profile of the ultra-thin liquid film increases with the increase of van der Waals forces.Furthermore,the capillary number also affects the thickness profile of the film in that higher capillary number leads to thicker liquid film.
An improved numerical simulation method for airfoil ice accretion
CHEN Ke, CAO Yi-hua, PAN Xing
2007, 22(11): 1814-1819.
Abstract PDF(1665KB) icon1805 icon403
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An improved numerical method of simulating ice accretion on airfoil was developed based on parcel concept following the fundamental assumption of droplet movement.This method has overcome the shortages of traditional Lagrangian method,such as:low computation efficiency,ice shape dependence on droplet partition density and grid consistency.But,it has also maintained the robustness of original method,without the issue of convergence in Euler method.NACA0012 rime ice accretion,local droplet collection and local impingement efficiency at 0° and 4° AOA(angle of attack) are simulated with this method in order to verify its correctness.The calculated results show that,this improved method contributes to reduce the calculation efforts.The predicted ice shape was consistent with the experimental result,while the effect on aerodynamics of airfoil was also analyzed.
Research of the influence of aspect ratio on infrared suppressing characteristics of rectangular nozzles
ZHANG Bo, JI Hong-hu, LUO Ming-dong, HUANG Wei, CAI Xu
2007, 22(11): 1820-1825.
Abstract PDF(1013KB) icon1889 icon422
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Based on a fanjet currently used in an advanced unmanned vehicle,an axisymmetric nozzle AR0 of 4.3 expansion ratio was obtained.Under the same exit area,five rectangular convergent nozzle models(AR1AR16)of different W/H(W/H=116) were experimentally investigated.The infrared radiation of nozzles and hot jet streams at 35 μm were tested using Fourier Infrared Spectroscope.The results indicate that the magnitude of infrared radiation from rectangular nozzle is smaller than axisymmetric one,and the infrared suppressing effect of rectangular nozzles improves with the increase of aspect ratio.
Numerical simulation of three-dimensional heat flows for longitudinal heat shield afterburner
HUANG Hai-ming, ZHAO Jian-xing
2007, 22(11): 1826-1832.
Abstract PDF(2135KB) icon1513 icon380
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Athree-dimensional turbulent combustion flow field of longitudinal heat shield afterburner was numerically investigated in a body-fitted coordinate system.The k-ε model,EBU-Arrhenius and Second-moment turbulent combustion model,as well as six flux model were used.The influences of two different afterburners,inlet gas parameter distributions and turbulent combustion models on afterburner flow fields and wall temperature profiles were calculated.By comparing the experiment results with the calculated results,it shows that:the effect of different geometric afterburners on turbulent combustion flows was more than inlet gas parameter distributions,and Second-moment combustion model was more suitable for simulating the turbulent reacting flow.
Research of heat management for aircraft fuel system
XU Zhi-ying, ZHUANG Da-min
2007, 22(11): 1833-1837.
Abstract PDF(1071KB) icon2511 icon530
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To make full use of onboard fuel to cool down airborne equipments and systems as a cool source,the concept of heat management of aircraft fuel was presented.The flow rate,pressure,temperature and heat loss of various nodes in the fluid network could be obtained through mathematical modeling of key components in the fluid network of aircraft fuel system,e.g.the fuel pressure pump,turbine-pump,and pipeline network.This makes it possible to predict the inlet temperature before the heat changer and the engine in any circumstance.The research provides a basis for scientific comprehensive utilization of fuel and heat management of aircraft fuel system.
Aerodynamic experimental investigation for mechanism of lift and thrust of flexible flapping-wing MAV
ANG Hai-song, ZENG Rui, DUAN Wen-bo, SHI Zhi-wei
2007, 22(11): 1838-1845.
Abstract PDF(1273KB) icon1902 icon537
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Anew flapping-wing model of MAV(Micro Air Vehicle) with flexible structure was developed in order to explore mechanism of lift and thrust generation in flexible flapping-wing MAV.Wind tunnel test demonstrated the downstroke of the flapping-wing by utilizing laser instrument.Variation of the lift and thrust of flexible flapping-wing under conditions of different flap parameters such as flap frequency,angle of attach,flow speed and so on was investigated and compared with computed results.The research provides reference for design of flapping-wing MAV.The flight tests of the Flexible Flapping-wing MAVconducted in Research Center of MAVof NUAAwere also successfully completed.
The design and performance study of a multi-diaphragm piezoelectric synthetic jet actuator
XU Jing-lei, LI Chao, SHA Jiang, ZHANG Kun-yuan
2007, 22(11): 1846-1851.
Abstract PDF(1016KB) icon1560 icon416
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Considering the shortcomings and incompetence of conventional piezoelectric synthetic jet actuator(PE-SJA),a novel multi-diaphragm PE-SJAdesign was proposed in this paper and some detailed experimental studies were carried out upon it.By using the hotwire anemometry,the optimum resonance frequency of the actuator was obtained through measuring the velocity magnitude at a fixed position on the axis of the orifice exit flowfield at different frequencies.Then the orifice exit velocities with different numbers of diaphragm were measured,analyzed and compared,which showed that at the axis of the orifice exit flowfield the averaged and peak velocities of one-diaphragm PE-SJAwas only the half of those of the five-diaphragm PE-SJA.But the performance of three-diaphragm PE-SJAwas almost the same as that of the five-diaphragm PE-SJA,which suggested that although the performance of the PE-SJAincrease with the number of the piezoelectric diaphragm,it did not occur in a linear way.PIVwas also used to obtain the structure of vortex of the flowfield.
PIV measurement of water tunnel for the flow field of a hovering coaxial-rotor
YU Shi-mei, DENG Yan-min
2007, 22(11): 1852-1857.
Abstract PDF(1205KB) icon1702 icon411
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Particle Image Velocimetry(PIV) technique was applied to water tunnel experiment for the flow field of hovering coaxial-rotor.Vortex contours and velocity distribution of the rotor flow fields,configuration and trajectory of the tip vortex were measured.The aerodynamic interference characteristics of hovering coaxial-rotor flow fields were also investigated.Asingle-rotor was also measured for comparison purpose.The experimental results provide reliable reference for aerodynamic calculation and reasonable design of helicopter.
Calculation of aerodynamic forces of a car with the effect of crosswind
ZHENG Hao, KANG Ning, LAN Tian
2007, 22(11): 1858-1862.
Abstract PDF(1636KB) icon1852 icon460
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The outflow field of a simplified fast back car was simulated numerically with the effect of no cross wind,steady cross wind and unsteady cross wind.The aerodynamic forces and coefficients were calculated.The results show that,steady crosswind will generate bigger lateral force,and also increase the drag and lifting force to a certain extent;the change trend of aerodynamic forces was the same as that of lateral wind speed.With the effect of unsteady cross wind,the drag increases more slightly,and the lateral force increases most significantly;the lifting force remains moderately.When cross wind reaches a high level,the flow field will change dramatically,and the wake vortex is turned into side vortex.
Dynamic stability analysis of tiltrotor aircraft in forward flight
YUE Hai-long, XIA Pin-qi
2007, 22(11): 1863-1867.
Abstract PDF(1048KB) icon2107 icon436
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Tiltrotor aircraft has a tilting proprotor at the tip of wing.The analytical model of dynamic stability for tiltrotor aircraft in forward flight in this paper consists of a cantilever wing and a rotor.The wing withstands vertical bending, chordwise bending and torsional deformations,and the rotor blade is considered to be capable of rigidly withstanding one order flap and lag motions.The aerodynamic loads are gained by quasi-steady flow and thin wing theory.Using the model,the differential equations of motion have been formulated under the condition of high inflow,making it possible to analyze the dynamic stability of tiltrotor aircraft in forward flight.The numerical results are basically consistent with the experimental results obtained by the Bell Helicopter Company,showing that the analytical model is suitable for analyzing the dynamic stability of tiltrotor aircraft in forward flight.
Study of aerodynamic characteristics of fastback car in starting process
LAN Tian, KANG Ning, ZHENG Hao
2007, 22(11): 1868-1873.
Abstract PDF(1278KB) icon1644 icon465
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The unsteady flow field of a fastback car during starting process was simulated numerically with Computational Fluid Dynamics(CFD)method.The aerodynamic drags and drag coefficients under two starting accelerations were calculated using k-ε turbulent model and the first order upwind scheme.The results show that the aerodynamic drag increased significantly in the starting process and reached a maximum value in a very short period after starting.When the car ran steadily,the drag tended towards a constant value.The drag-coefficient decreased rapidly during starting and became steadily after completion of starting.In the process of staring,wake vortex formed gradually and the pressure difference between the front and back of the car became bigger.After running steadily,the difference became smaller.
Analysis for influence of different tip clearance on transonic fan rotor
LIU Jian-yong, YUAN Wei, ZHOU Sheng, LU Ya-jun
2007, 22(11): 1874-1878.
Abstract PDF(993KB) icon1761 icon465
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In order to study the influence of tip clearance flow on the performance of a transonic compressor,a high-load transonic fan's rotor with five constant width clearances and two step-clearances were numerically simulated.After analysis of the overall performance parameters and the detailed flow parameters including the static pressure,circumferential velocity and entropy,it is concluded that the front part clearance flow has greater influence on the compressor than the back part clearance flow.In particular,the vortex-shock interference may worsen the front part clearance flow,as demonstrated by comparing the simulation of two step-clearances.
Dynamics analysis,feature extraction and intelligent diagnosis for rubbing fault of rotor supported on bull bearings
LI Fei-min, CHEN Guo, HOU You-ping
2007, 22(11): 1879-1885.
Abstract PDF(2350KB) icon2034 icon376
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This paper aims at diagnosing the rubbing fault of a rotor supported on ball bearings.Firstly,a dynamics model of unbalance-rubbing coupling fault of rotorball bearing system was established by taking into account the nonlinear Hertzian contact and the radial clearance;secondly,3-Dspectrum diagram was used to analyze the rubbing fault and determine the characteristics of every frequency zone;thirdly,an optimized self-adaptive neural network was obtained using simulation data,and rubbing test samples were diagnosed with a recognition accuracy over 91%.The results validate the usefulness of this dynamics model,meanwhile the research findings provide a new method for effectively combining malfunction mechanism analysis and intelligent diagnosis.
Mechanical analysis of single fiber pull-out on ceramic matrix composites
ZHANG Hong, SONG Ying-dong
2007, 22(11): 1886-1892.
Abstract PDF(1053KB) icon1836 icon453
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Amechanical model of single fiber pull-out for composites was established if considering the interfacial frictional sliding.The expressions of the matrix axial stress,the fiber axial stress and interfacial shear stress including Poisson's effect were obtained.As for SiC/RBSNceramic matrix composites,the stress distributions of fiber,matrix and interfaces was analyzed under partial debonding/slipping and full debonding.The calculated results were well consistent with the finite element results,showing that the variable fiber volume fraction could change the failure point of debonding/slipping on the interface.The debonding propagation of interface occurs more easily in partial debonding/slipping than in full debonding.The stress distribution changes little if only the interface friction coefficient is increased without considering fiber/matrix thermal mismatch.
Experimental investigation on rotor vibration control by elastic support/dry friction damper
WANG Si-ji, LIAO Ming-fu, YANG Shen-ji
2007, 22(11): 1893-1897.
Abstract PDF(1006KB) icon2010 icon431
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An actively controlled elastic support/dry friction damper was designed and investigated experimentally for its effectiveness of reducing rotor vibration.It is proven that the active damper can effectively reduce rotor vibration by an active control strategy.Experimental results show that the damper features simple construction,ease-of-control and little power consumption.So,such an actively controlled elastic support/dry friction damper is promising in practical application.
Research on consistent tangent modulus for unified viscoplastic constitutive equations
WANG Qing-wu, YANG Xiao-guang, SHI Duo-qi
2007, 22(11): 1898-1902.
Abstract PDF(1513KB) icon2080 icon474
Abstract:
Unified viscoplasticity constitutive equations are a system of integral or incremental equations with implied internal variables.So,it is difficult to provide a well-defined expression of the consistent tangent modulus.Based on the backward Euler's integral for unified viscoplasticity constitutive equations,a new expression of consistent tangent modulus was derived for rate-dependent plasticity.The constitutive equations and consistent tangent modulus expression were implemented in a commercial finite element code-MARC.The numerical examples of finite elements verify the feasibility of consistent tangent modulus.
Numerical design optimization of compressor blade based on ADOP
JIN Dong-hai, GUI Xing-min
2007, 22(11): 1903-1908.
Abstract PDF(1191KB) icon1392 icon477
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An aerodynamic design optimization platform(ADOP) has been developed.The numerical optimization method is based on genetic algorithm(GA),Pareto ranking and fitness sharing technique.The platform was used for design optimization of the stator of an advanced transonic stage to seek high adiabatic efficiency.The compressor stage efficiency is increased by 0.502% at optimal point and the stall margin is enlarged by nearly 1.0% at design rotating speed.The flow fields of the transonic stage were simulated with FINE/Turbo software package.The optimization result indicates that the optimization platform is effective in3Dnumerical design optimization problems.
Numerical simulation of boundary layer transition under pressure gradient
DONG Ping, HUANG Hong-yan, FENG Guo-tai
2007, 22(11): 1909-1914.
Abstract PDF(1367KB) icon1808 icon406
Abstract:
Numerical simulation was performed for the flat plate boundary layer transition test at zero and non-zero pressure gradients,T3A,T3C1 and T3C2.The results have been validated through the experimental data,showing that the pressure gradient could have great influence upon the starting position of transition process;MLtransition model could predict accurately the transition and development process.However,the applicability of M-Lone-equation transition model is limited as compared with M-Ltwo-equation transition model,since it depends on how to correctly choose the transition onset momentum thickness Reynolds number by experiences.During calculation with M-Ltransition model,selecting the import viscosity based on the nature of vortex assists in predicting the transition process.
Numerical simulation of the three-dimensional flow field of transonic turbine cascade
ZENG Jun, XIANG Chuan-guo, CHENG Xin-hua
2007, 22(11): 1915-1920.
Abstract PDF(965KB) icon1596 icon433
Abstract:
Athree-dimensional Navier-Stokes simulation was performed numerically for a transonic turbine planar cascade and a transonic turbine annular cascade using CFDsoftware CFX-TASCflow code.The results show that CFX-TASCflow code software could predict reliably turbine cascade flow field and its performance.The characteristics of the researched transonic turbine cascades viscous flow field were analyzed.
Multivariable decoupling control of aeroengine based on QDRNN
LI Hua-cong, RONG Li-ye, ZHU Yu-bin
2007, 22(11): 1921-1924.
Abstract PDF(580KB) icon1562 icon391
Abstract:
Through analysis of QDRNN(quasi-diagonal recurrent neural network) and GMD(gradient decent method),a multivariable decoupling PID(proportional integral,differential) control system based on QDRNN was presented to resolve the complex nonlinear model of aeroengine.The structure and principle of the algorithm were also illustrated through simulation of design points and non-design points.The research results show that,a multivariable decoupling PIDcontrol system based on QDRNN is well-suited for decoupling of variables in dual-variable control system.
Troubleshooting soft failure of aircraft engine sensor with sequential probability ratio
XUE Wei, GUO Ying-qing
2007, 22(11): 1925-1929.
Abstract PDF(1627KB) icon1894 icon410
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Amethod for troubleshooting soft failure of aircraft engine sensor was proposed based on Kalman filters and sequential probability ratio test(SPRT). This approach was used to process Kalman filter residuals and detect the soft sensor failure with revised SPRT.Thereafter,this method was compared with WSSR (Weighted Sum of Squared Residual) in troubleshooting soft failure of sensors.The simulation results show that SPRTmethod is more suitable to detect soft failures of aircraft engine sensor.
Online optimization control of turboshaft engines based on variable inlet guide vane
YAO Wen-rong, SUN Jian-guo
2007, 22(11): 1930-1934.
Abstract PDF(800KB) icon1556 icon475
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The online optimization control of variable inlet guide vane was studied for minimum fuel consumption,and the effect of variable inlet guide vane on the turboshaft engine was analyzed.Thus,an online optimization method based on variable inlet guide vane was proposed.At last,a simulation test was conducted for online optimization control of turboshaft engine,showing that the specific fuel consumption(SFC) will decreases by 3%~7% with higher applicability.
Time-frequency characteristics of stator passage pressure signal of aeroengine compressor
WEI Feng-ting, LI Ying-hong, ZHANG Pu
2007, 22(11): 1935-1938.
Abstract PDF(450KB) icon2362 icon440
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Tests on aeroengine were conducted to obtain stator passage pressure signal of the first compressor stage of a test aeroengine.By means of time-frequency analysis,the time-frequency structures centered on550 Hz and 2200 Hz were identified;the blade passing frequency of the first 3 compressor rotors,and some of their sum-frequency and difference frequency signals,were identified too.It's also observed that for the first 3 compressor rotors,in the process of engine throttling,the blade passing frequencies,their sum-frequency and difference frequency signals would gradually increase their magnitudes before the opening of discharge valve,which indicated that the first compressor tip region flow separation became server following the decrease of engine speed.Thus compressor rotor flow field information might be obtained through monitoring the time-frequency characteristics of pressure signal of specific compressor stator passage,which was helpful for the control of compressor stability.
Heat transfer characteristics of expander cycle thrust chamber
HAN Fei, LIU Yu
2007, 22(11): 1939-1946.
Abstract PDF(1370KB) icon1642 icon469
Abstract:
In order to understand the heat transfer characteristics of expander cycle regeneratively-cooled thrust chamber,three dimensional computational models of expander cycle thrust chamber were established and numerical simulation was employed.The influence of a number of factors,such as increased length of chamber cylinder,different cooling routing,different surface roughness and rib configurations on the heat transfer characteristics like coolant heat pick-up,pressure loss in the cooling circuit,wall temperature and heat flux distribution was investigated.k-ε turbulence model was adopted for the computation.The results show that the co-flow cooling routing contributes to lower pressure loss in cooling circuit but yet lower coolant heat pick-up,when comparing with converse cooling routing.The compared results of the two uncooled ribs with different rib heights demonstrate that the increase of the heat flux is proportional to the increase of the total surface area exposed to hot gas.
Heat transfer characteristics of axi-symmetrical nozzle and RS nozzle
HAN Fei, LIU Yu
2007, 22(11): 1947-1953.
Abstract PDF(1263KB) icon1837 icon428
Abstract:
To understand and compare different heat transfer characteristics of regenerative cooling in axi-symmetrical nozzle and round to square nozzle(RS nozzle),computational models of axi-symmetrical nozzle(thrust chamber) and RS nozzle(thrust chamber) were established.Numerical simulation was employed to investigate and compare fluid field,wall temperature,heat flux,coolant heat pick-up and pressure loss in the cooling circuit of axi-symmetrical nozzle and RS nozzle.The results show: In case of RS nozzle,because its contour is not continuous,peak values of wall temperature and heat flux exist at the location next to shape transformation,which leads to non-uniform temperature and heat flux distribution along the wall circumference.
Stability analysis on variable thrust engine of partially catalyzed hydrogen peroxide
LIU Jing-hua, TAN Jian-guo, YANG Tao, WANG Zhen-guo
2007, 22(11): 1954-1957.
Abstract PDF(468KB) icon1847 icon497
Abstract:
Apartially catalyzed engine scheme was presented.This engine could keep the inject pressure drop almost unchanged when the thrust varies very much.It's proved that this engine functions stably in a wider thrust range if non-catalyzed engine and fully-catalyzed engine are compared.The regulating performance of this engine was also simulated.The results show that the engine's response is rapid and stable when ramp input is employed.
Multidisciplinary design optimization based on advanced model of satellite attitude control system
WANG Xiao-feng, HUANG Hai
2007, 22(11): 1958-1962.
Abstract PDF(355KB) icon1633 icon364
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The coupled relationship between the attitude control system and other subsystems of three-axis-stabilized satellite was analyzed in this paper,and then attitude control models and subsystem hardware were selected.More accurate analysis model was established to calculate subsystem mass and power,then optimization models of integrated system,attitude control subsystem,power subsystem and structure subsystem based on collaborative optimization(CO) methodology were built. Finally,the programs were compiled with Clanguage for the analysis models and optimization models.The results shows: subsystem model collaborates well with this system model to obtain better system performance.
Non-linear dynamic study of2-stage star gear train
ZHU Zi-bing, ZHU Ru-peng, BAO He-yun
2007, 22(11): 1963-1970.
Abstract PDF(3214KB) icon1908 icon463
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A dynamic analysis model was established for 2-stage star gear train,wherein the transmission error and the time-varying stiffness and backlash were considered.Using ODE45 integration method,the nonlinear differential equations with multiple backlashes were solved.The nonlinear dynamic behavior,which leads to chaos from harmonic vibration,non-harmonic vibration,period-doubling vibration and quasi-periodic vibration by changing frequency excitation of the system,was discussed thereof.
Study on critical load of skidding in high speed ball bearing
CUI Li, WANG Li-qin, ZHENG De-zhi, GU Le
2007, 22(11): 1971-1976.
Abstract PDF(797KB) icon1626 icon477
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The skidding principle for high-speed ball bearing was obtained from the stress analysis of rolling body.The theoretical rotary speed of various components was determined through interaction modeling of bearing elements.And,the critical load of combined loaded bearing was calculated by combining quasi-static and quasi-dynamic analysis methods.Take 276927NK1W1(H) bearing,for example, the critical load under different loads was studied.The results show that,radial load has greater influence on critical load;the critical load of combined loaded bearing can be obtained when rotary speed of cage becomes steady obviously and no skidding occurs on the surface of loaded rolling elements.Finally,the reliability of this method was verified by the computation example of Gupta and test result of Poplowski.

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