2006 Vol. 21, No. 4

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Cooling effectiveness of a rotating disk with discrete receiver holes
LUO Xiang, XU Guo-qiang, TAO Zhi, DING Shui-ting
2006, 21(4): 621-625.
Abstract PDF(435KB) icon1623 icon417
Abstract:
Modern gas turbine blades are cooled using air bleeded from the compressor.In a rotor-stator system,the cooling air enters at the center of the stator and flows radially outward,then leaves through the discrete receiver holes in the rotor and the clearance between the rotor and the shroud.The temperature distribution was measured by Thermal Liquid Crystal(TLC) and thermocouples on the rotor surface to acquire the cooling effectiveness.The influence of rotating speed and cooling mass flow rate on cooling effectiveness were analyzed.The dimensionless average temperature and dimensionless temperature difference of rotor surface decrease with both of the dimensionless mass flow rate and rotational Reynolds number are increased.The existence of receiver holes is of advantage to cooling rotor.The experiments show that the bigger the size of receiver holes is,the higher of cooling effectiveness will be.
Convective heat transfer of jet impingement inside semi-confined channel
ZHANG Ze-yuan, ZHANG Jing-zhou, YANG Wei-hua
2006, 21(4): 626-630.
Abstract PDF(1188KB) icon2074 icon478
Abstract:

The thermal image visualization of jet impingement cooling with single or double rows of holes inside the semi-enclosed channel were revealed by using infrared camera and then the impingement cooling heat transfer coefficients were deduced.The effects of flow and geometric parameters on convective heat transfer coefficients were obtained.The results show that: for a single row normal impingement,the impingement cooling effectiveness is enhanced with the increase of impinging Reynolds number or the decrease of hole spacing to diameter ratio,and the best effectiveness is achieved under the jet-to-surface spacing equals to 2;when the jet is oblique to the confined wall,the cooling effectiveness is weakened especially when the jet-to-surface spacing ratio is greater than 2;for double rows of holes with normal impingement cooling,the cooling effectiveness of rear row jets is weaker than the front row jets at lower impinging Reynolds number or larger jet-to-surface spacing.
An experimental investigation on infrared radiation characteristics of 2-D nozzles of turbofan engine afterburner
LUO Ming-dong, JI Hong-hu, HUANG Wei, CAI Xu, ZHANG Bo, GAO Cao
2006, 21(4): 631-636.
Abstract PDF(841KB) icon2050 icon457
Abstract:

The infrared radiation characteristics of axisymmetric and 2-D nozzles with aspect ratios of 1,4,8,12 and 16,have been experimentally studied.The nozzle flow is composed of the main gas stream and the secondary air stream in order to simulate the nozzle of turbofan engine.The spatial distributions of the infrared radiation intensity of 2-D nozzles have been obtained,and compared with that of the axially symmetric nozzles.
Investigation on the working characteristics of pulse detonation engine with changing the time of fuel injection
ZHANG Yi-ning, WANG Jia-hua, FAN Yu-xin, LI Jian-zhong, ZHANG Jing-zhou
2006, 21(4): 637-641.
Abstract PDF(320KB) icon1711 icon431
Abstract:
The investigation is aimed at the improvement of the coordination of operation for the two-phase pulse detonation engine.The time delay of ignition obtained in gasoline/air mixture by experiments was about 3.6ms.The time period of DDT process was about 3.8 ms.By sharing the total cycle time aptly and changing the time of fuel injection,the operation characteristics of PDE were researched by experiments.It was found that the period of the air purge can be eliminated in the operation of the two-phase PDE.Keeping the time of fuel injecting in the period of DDT process,the PDE prototype can operate steadily and cyclically.The time of fuel injection delays to the time period of the expansion process,the peak value of detonation pressure will be decreased.These conclusions are valuable for reference to increase operating frequency of PDE and promote the efficiency of two-phase detonation.
Numerical analysis of supersonic combustion with kerosene using two different chemical reaction models
CAI Yuan-hu, LIU Ou-zi, HU Yu-li, LIU Jing-hua, LING Wen-hui
2006, 21(4): 642-646.
Abstract PDF(1426KB) icon1884 icon473
Abstract:
Numerical analysis of supersonic combustion with kerosene was carried out using two chemical reaction models.One is the one-step irreversible finite rate chemical reaction,and the other is the mixture-fraction equilibrium chemical reaction model combined with the discrete droplet model and probability density function at the same time to describe the interaction of turbulence and combustion.Compared the numerical results with the experimental data validated the models used in the numerical simulation.In the assumed computation conditions,compared with the irreversible finite rate chemical reaction model,the mixture-fraction equilibrium chemical reaction model combined with other models can predict exactly kerosene spray combustion in the dual-mode supersonic combustor.The integrated cavity flame holder,fuel injector,mixer and flame holder together can improve mixing and combustion of the liquid kerosene and air mixture.The combustion efficiency is 0.880 6 measured at the combustor exit.
Heat transfer characteristics of liquid metal thermal drive in rotating closed cyclic small channel
MAO Jun-kui, XU Ruo-ying, CHANG Hai-ping
2006, 21(4): 647-652.
Abstract PDF(352KB) icon1933 icon445
Abstract:
Using thermal drive in the small cyclic channel,heat can be efficiently transferred from the high temperature side to the cooled side.Numerical simulations were carried out to study the flow and heat transfer properties of different fluids under centrifugal force field.Three different liquid metals(Na,Li and alloy of Na-K) were applied as thermal drive medium(fluid inside the channel) and the average heat transfer coefficient Nu on the heated side varying with the Bu number and Ro number was studied.All the results show the average Nu number increases with Bu number and decreases with Ro number.Maximum heat transfer performance of thermal drive can be achieved in high rotating speed and lower heat flux if liquid Na-K was employed as thermal drive medium.When the rotating speed and heat flux both are high,the proper thermal drive medium is liquid Li which can result in maximum heat transfer performance.
Effect of jet arrangement on the flow characteristics of the outlet hole in short confined channel
LIU Hai-yong, KONG Man-zhao, LIU Song-ling, SHEN Tian-rong
2006, 21(4): 653-657.
Abstract PDF(1655KB) icon1577 icon477
Abstract:
Experimental investigation was carried out to study the flow fields of the outlet hole in two confined passages with different staggered jet arrangement.Detailed flow field measurements were conducted with a five-hole probe.The influence of jet arrangement on the flow field and discharge coefficient of the outlet hole was investigated.Experimental data show that the jet arrangement has little influence on flow behavior in the passage of low aspect ratio,but play important role on discharge coefficient.Distinctively different flow transformation was found when the aspect ratio increased to 3 and 5,while the variation of discharge coefficient showed similar results.
Numerical investigation on heat transfer of film cooling with delta-shaped tabs
YAO Yu, ZHANG Jing-zhou, LI Yong-kang
2006, 21(4): 658-662.
Abstract PDF(1052KB) icon1775 icon427
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Using method of constant heat flux,the heat transfer coefficient of the film cooling with a row of cylindrical holes and discrete delta-shaped tabs covering a part of the hole placed parallel to the film cooling surface was investigated numerically.The main factors influencing the heat transfer include the blowing ratio and the size of the tab.During the test,the mainstream velocity was 10 m/s and the blowing ratio was 0.3 to 1.5.Results show that the tabs do not enhance the heat transfer of the film cooling significantly at lower blowing ratio;heat transfer improvement is significant in the cases of higher blowing ratio with larger tab size.
Experimental research on detonation initiation of gasoline/air two-phase pulse detonation engine
ZHANG Yi-ning, WANG Jia-hua, Liu Hong, ZHANG Jing-zhou
2006, 21(4): 663-667.
Abstract PDF(801KB) icon2043 icon467
Abstract:
Efficient initiation of detonation waves is the key to the pulse detonation engine(AB.PDE) operation.In the process of deflagration to detonation transition(AB.DDT),detonation waves were successfully triggered by controlling the shock wave reflection.Interaction between flame and shock is strengthened by putting obstacles in detonation chamber with reasonable arrangement,which can efficiently organize reflection of shock wave and initiate detonation timely.Thus,DDT distance was shortened comparatively.Gasoline/Air detonation waves propagate successfully in the combustor.These results are valuable to the investigation on DDT process of two-phase pulse detonation engine at high frequency.
Experimental study on aerodynamic and aero-acoustic performance of low pressure axial flow fan with circumferential skewed blades
OUYANG Hua, LI Yang, DU Zhao-Hui, ZHONG Fang-Yuan
2006, 21(4): 668-674.
Abstract PDF(895KB) icon1600 icon519
Abstract:
Low pressure axial flow fan with circumferential skewed rotors was studied.The rotors include the traditional radial rotor,the forward-skewed rotor and the backward-skewed rotor.In present study,aerodynamic and aeroacoustic performance of these three type rotors was measured and analyzed.The results show that the forward-skewed rotor may reduce noise effectively and extend the range of steady operation compared to the radial rotor.With the same skew angle,both the aerodynamic and aeroacoustic performance of forward-skewed rotor is better than that of the backward-skewed one.The performance difference comes from the direction of blade radial force.The tip flow condition of forward-skewed rotor is better,but the mid-span losses are increased.
Experimental investigation of primary flow vectoring using parallel self-coupling jets
LI Nian, ZHANG Kun-Yuan, XU Jing-lei, SHA Jiang
2006, 21(4): 675-680.
Abstract PDF(893KB) icon1616 icon472
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In order to investigate the influence of self-coupling jet on the vectoring of the primary jet,parallel jets arrangement were adopted.The self-coupling jet exciter is parallel to the primary jet and the formation of a low-pressure region between the jets results in a deflection of the primary jet towards the exciting jet.The PIV experimental study shows that for f=400 Hz,the momentum flux of the self-coupling jet achieves its maximum value,while the boundary of the primary jet reaches its maximum width due to the strongest suction ability to the environmental gas.However,the experiment indicates that for f=500 Hz,due to the self-coupling jet exciting,the maximum 48° vectoring of the primary jet with a flow speed of 2.6 m/s achieves.
Computational analysis on static internal flow field of shock vector controlled vectoring exhaust nozzles
WANG Quan, WANG Qiang
2006, 21(4): 681-685.
Abstract PDF(356KB) icon1965 icon423
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After comparing the results of three different turbulence models in computing static internal flow field of shock vector controlled vectoring exhaust nozzles by means of second order upwind schemes,(RNG) k-turbulence model shows to be the most valid turbulence model,and the computation results have been compared with that of the scaled model experiments.The results indicate that small nozzle pressure ratio and large inject mass flow rate will result in a larger vector angle.
Analysis of low-pressure compressor rotor vibration characteristics induced by inlet guide vane
HOU An-ping, LI Qiu-shi, ZHOU Sheng, TANG Zha-yong, FENG Wei-ling, WU Chen-jie
2006, 21(4): 686-692.
Abstract PDF(726KB) icon1926 icon446
Abstract:
This paper estimated the possibility of flow induced vibration in low-pressure compressor rotor with inlet guide vane.Through steady and unsteady numerical simulation,it was found that blade passage frequency of the guide vanes influences little on the vibration characteristics of the low-pressure compressor rotor.Moreover,because the intensity of vortex shedding in the wake of the guide vane is too weak,it's frequency has no influence on the vibration characteristics of the low-pressure compressor rotor.The computational result shows that both the design of airfoils and the location of installation are reasonable.
Effects of the up-stream blade wakes on the spectrum of rotor blade unsteady surface pressure
WANG Ying-feng, HU Jun, LUO Biao-neng, LI Chuan-png
2006, 21(4): 693-699.
Abstract PDF(1130KB) icon1786 icon491
Abstract:
The unsteady surface pressures on the rotor blades of a single-stage low-speed axial compressor were measured by means of mounting micro-sensors on the surface the blades.The effects of up-stream blade wakes on the spectrum of rotor blades unsteady surface pressure were analyzed.On the rotor blade pressure surface,the dominant frequencies of unsteady surface pressure are the up-stream blade wake passing frequency and its harmonics,and the amplitudes of pressure fluctuations decrease from leading edge to trailing edge.However,on the blade suction side from leading edge to trailing edge,the amplitudes of pressure fluctuations increase at the fore part where flow accelerates and decrease at the rare part where flow decelerates.Flow separation produces pressure fluctuations of large amplitudes,possibly with the dominant frequencies differ from up-stream blade wake passing frequency and its harmonics.
Analysis and control of transient aero-elastic response of teetering rotor on the shipboard
HAN Dong, GAO Zheng, WANG Hao-wen, Li Xin-bai
2006, 21(4): 700-705.
Abstract PDF(455KB) icon1587 icon460
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To investigate the problem of transient dynamic aero-elastic response of teetering rotor engagement and disengagement during shipboard operations,finite rotation of teeter angle was introduced as generalized coordinate based on the moderate deflection beam model.Nonlinear quasi-steady aerodynamic model was adopted and the flow field was determined by the test data.According to the Hamilton principle,dynamic equations were derived based on the generalized force formation.Calculation results are in good agreement with the test data and the data from other literatures.Result shows that teetering rotor blade tip has the danger of touching fuselage because of the excess flapping motion during shipboard operations.Some methods of controlling blade excess flapping are discussed.Installation of the blade flap restraint device can restrict the blade excess flapping.Increasing collective pitch has contrary effect.Cyclic pitch control has some effect on the blade flapping motion.The blade excess flapping motion can be evidently reduced by the control of the rotor speed.
Numerical simulation of LCF probability life of a turbine disk
TANG Jun-xing, LU Shan
2006, 21(4): 706-710.
Abstract PDF(552KB) icon1648 icon467
Abstract:
Crack initiation life behaves large scatter which induces inconvenience in the evaluation of the safe boundary in predicting low cycle fatigue(LCF) life of disks.To determine the safety life,a probability model based on strain fatigue was introduced to take into account the random factors such as rotating speed,material property and the interference between pin bolt and pinhole.Then the distribution of the disk fatigue life was acquired through the combination of the response surface method and Monte-Carlo simulation.Finally,the life with reliability level of 99.87% was derived and fitted well with the technical life of the disk based on test evaluation.
Forced response characteristics of bladed disks with disordered dry friction
WANG Hong-jian, HE Er-ming, YU Shi-xia
2006, 21(4): 711-715.
Abstract PDF(326KB) icon1808 icon408
Abstract:
Dampers in bladed disks are main components for reducing vibration.The dry friction disorder among those dampers can affect their damping performance.In this paper,the harmonic balance method and the technique of fast Fourier transmission were employed to simulate the forced response of bladed disks with nonlinear dry friction.The characteristics of bladed disks with disordered dry friction were investigated and analyzed under different coupling,viscous damping ratio,dry friction strength and the degree of dry friction disorder.The study indicates that the disorder of dry friction can significantly increase the resonant response of bladed disks,especially in the system with weaker coupling and larger viscous damping ratio.
Condition based aero-engine maintenance decision method using proportional hazards model
ZUO Hong-fu, ZHANG Hai-jun, RONG Xiang
2006, 21(4): 716-721.
Abstract PDF(1554KB) icon2020 icon545
Abstract:
Condition based aero-engine maintenance(CBM) decision based on condition monitoring information is an important issue to the safety operation of airlines.In this paper aero-engine historical data of removal due to performance degradation were analyzed,and a functional relationship between aero-engine performance parameters and time-on-wing was established using Weibull proportional hazards regression model.Furthermore,maintenance decision threshold is determined by the minimum maintenance cost or maximum availability strategy.Thus,an objective quantitative decision method for optimal maintenance decision was provided.Finally,the failure data of CF6 aero-engines were analyzed in detail as an example using the method mentioned above.The result shows that the method has high practical value for aero-engine CBM decision.
High-precision reconstruction of blade leading edge
ZHANG Li-ning, ZHANG Ding-hua
2006, 21(4): 722-726.
Abstract PDF(308KB) icon2000 icon480
Abstract:
The shape of leading/trailing edge is very important to the performance of the turbine blade.Precise description is the premise for turbine blade machining.Generally,the leading/trailing edge is a circular arc or elliptic arc.In order to reconstruct them accurately,a method for fitting the ellipse based on the principle of conditional least square was applied at first,and then its fitting result was used as an initial value to find a more precise result according to the polar line geometrical properties of the ellipse.Some examples were given to prove the good robustness and high accuracy of this fitting method,especially for a part of ellipse.During the reconstruction of the blade,some outliers which are difficult to exclude beforehand may influence the accuracy of fitting result greatly.Because of our method's good robustness,this fitting method was applied to the progressively increasing number of data centered at leading edge for several times to exclude outliers.Numerical experiments show the effectiveness of this scheme.In conclusion,the method presented is suitable for the reconstruction of blade in the reverse engineering.
Signal periodic segment processing technique for diagnosing gear pairs faults
CHEN Jin, LIAO Ming-fu, CHEN Gang
2006, 21(4): 727-731.
Abstract PDF(929KB) icon1620 icon469
Abstract:
This thesis presented a technique for diagnosing gear pairs faults and introduced the procedure in detail.When there is a fault in the gear pairs,there will be some pulse(s) in the vibration signal which is picked with high sampling rate on the gearbox.Firstly,the vibration signal was processed by time domain averaging to weaken noise.Then the average signal was divided in equal segments with the same number of the gear teeth which was to be diagnosed in the gear pairs.The analysis of individual segment reveals more sensitive changes of the vibration signals in both time and frequency domain caused by gear faults.Further more,the location of the failed gear tooth can be identified in terms of the position of the segment which is different from normal segment.Both the numerical simulated signal and the experimental investigation verify the availability of the signal periodic segment processing technique.
Topology optimization of continuum structure under multiple constraints using genetic algorithm with elitist strategy
SUN Ming-hua, CUI Hai-tao, WEN Wei-dong
2006, 21(4): 732-737.
Abstract PDF(732KB) icon2162 icon457
Abstract:
Genetic Algorithm(GA) was served as an optimization tool for the topology optimization of continuum structure under multiple constraints.The elitist strategy was introduced into GA to improve the convergence and optimization results.During the process of optimization,GA was used to optimize the structure,while ANSYS-based finite element technique was used to model and analyze the structure.An example shows the rationality and effectiveness of the method.The method can apply to the topology optimization of complex engineering structure,and it can provide multiple initial design schemes.
Life scatter factor method based on the kth order experimental life with logarithm normal distribution
LU Xiao-yan, LU Shan
2006, 21(4): 738-740.
Abstract PDF(586KB) icon1968 icon439
Abstract:
For the needs of the life scatter factors under different conditions to assess the engine component lives,in this paper,the theoretical formulas of the life scatter factors based on the arbitrary kth order experimental life of a small sample with logarithm normal distribution were deduced.Life scatter factors were given with the confidence of 0.95,the reliability of 0.9987 and the standard deviation of logarithm normal distribution 0.13.The life scatter factors based on the worst experimental lives fit well with those in the published literatures.The life scatter factors based on the best experimental lives are more reasonable than those in the literatures.Using the formulae given in the paper,the life scatter factors can be obtained with any given confidence,reliability and standard deviation of the logarithm normal distribution,which can be used to assess component lives in engineering application.
Redesign of a transonic compressor stage using highly loaded bowed stator
LI Shao-bin, SU Jie-xian, WANG Zhong-qi
2006, 21(4): 741-746.
Abstract PDF(586KB) icon1988 icon466
Abstract:
Study on the redesign of a highly loaded fan stage using high-turning bowed compressor stator suitable for high subsonic inlet flow conditions was presented.The original tandem stator was replaced by the highly loaded bowed stator.3D contouring technique and local modification of blades were applied to the design of the bowed blade in order to improve the aerodynamic performance and the compressor structure.The performances along the constant design speed line and at design point both of the original fan stage and the redesigned fan stage were obtained by numerical simulations.The results show that the highly loaded bowed stator can be used to improve the structure and the aerodynamic performance of the compressor,and it is believed that the highly loaded bowed stator can also be used to develop high-performance compressor.
Design of radial flow and mixed flow compressor rotor splitter-blades
WANG Qi, SHAN Peng
2006, 21(4): 747-753.
Abstract PDF(1147KB) icon1860 icon463
Abstract:
A method was developed for the design of non-axial turbomachine airfoils with arbitrary surfaces.The method can be applied to the design of centrifugal compressor and mixed flow compressor blades and vaned diffusers.Especially,the employed blade surface setting method is that letting the blade thickness be distributed as a triple spline function.Also the application of splitter blade to centrifugal compressor and mixed flow compressor and rotor splitter-blades design were introduced in this paper.Fairly ideal airfoils were obtained.This method of airfoil design has been validated to be operational and applicable by CFD simulation.It built a sound foundation for further aerodynamic optimization of those non-axial flow type turbomachines.
Detection of rotating stall in aircraft engine based on wavelet analysis
XIE Feng, XIE Shou-sheng
2006, 21(4): 754-758.
Abstract PDF(320KB) icon2236 icon456
Abstract:
Stalled pressure data in compressor was de-noised by wavelet analysis and then resolved with multi-resolution analysis.The pressure signals in related frequency band were reconstructed by the wavelet coefficient in dN level.Rotating stall was considered to be examined out when the amplitude of the reconstructed signals was somewhere beyond the given threshold value.The results show that it is effective to identify the peak signal and noise by wavelet decomposition.Different threshold values are given with different sampling frequencies.By monitoring the dN level of the reconstructed signals,rotating stall can be detected.
Aero-engine nonlinear dynamic starting model based on parsimonious genetic programming
WEI Xun-kai, LI Ying-hong
2006, 21(4): 759-766.
Abstract PDF(445KB) icon1931 icon416
Abstract:
A novel Parsimonious Genetic Programming(PGP) algorithm for aero-engine starting process optimum data-driven nonlinear dynamic modeling was proposed.First, the method used the traditional GP to generate nonlinear input-output models that were represented in a binary tree structure.Then,Orthogonal Least Squares algorithm(OLS) was applied to estimate the contribution of the tree branches to the accuracy of the model.On this basis,the complex redundant subtrees can be eliminated and the GP's convergence speed is enhanced.Finally,the simple,reliable and accurate linear-in-parameters nonlinear dynamic model can be obtained via GP evolution.Applications to real aeroengine starting process modeling validate that the proposed method can generate more robust and interpretable models.
Influence analysis and self-adaptive optimization of support vector machine time series forecasting model parameters
YANG Yu-wei, ZUO Hong-fu, CHEN Guo
2006, 21(4): 767-772.
Abstract PDF(368KB) icon1778 icon426
Abstract:
Support Vector Machine(SVM) is based on Statistical Learning Theory(SLT) and Structural Risk Minimization Principle(SRM),and theoretically assures best generalization,therefore,it is theoretically better than Artificial Neural Network(ANN) which is based on Empirical Risk Minimization Principle(ERM).In this paper,SVM was used to establish time series forecasting model,and on the basis of analyzing the influence of model parameters,a self-adaptive optimizing algorithm based on genetic algorithm was put forward.Finally,the sunspot data and the spectrometric oil data of some aero-engines were used for preliminary analysis,and the results show the correctness and validity of the new method.
Modeling of electromagnetic field within arcjet thruster
XIAO Ying-chao, LIU Yu, ZHANG Zhen-peng, ZHANG Guo-zhou
2006, 21(4): 773-777.
Abstract PDF(421KB) icon1872 icon423
Abstract:
In order to reveal electromagnetic characteristics and interaction between electromagnetic field and high temperature ionized gas within arcjet thruster,improved modeling of electromagnetic field was developed and various numerical techniques were observed and studied.Contributions of electric field force,lorentz force and electronic pressure gradient to conduction current were considered in the model.Electricity equation was derived from electron dynamic equation and particle collision theory.Electromagnetic field equation was simplified from Maxwell's equations.And ten iteration techniques were introduced to solve discretized electromagnetic field equation,including Strong Implicit Procedure(SIP) iteration technique.The investigation shows that SIP iteration technique can be adopted to solve electromagnetic field within arcjet thruster very effectively,and the present modeling can well demonstrate the interaction between electromagnetic field and high temperature ionized gas within it.
Compare of plug nozzle's heat transfer characteristics in different opertoin condition and with different coolant flow rate
HAN Fei, LIU Yu, LI Jun-wei
2006, 21(4): 778-783.
Abstract PDF(702KB) icon1759 icon480
Abstract:
To understand the different heat transfer characteristics of regenerative cooling in plug nozzle at different operating conditions,computational model of two dimensional plug nozzle and internal nozzle were established and numerical simulation was employed.Heat transfer results of the internal nozzle and the parameter distribution at the outlet were obtained.Flowfield and heat transfer characteristics of the plug at different operating conditions with different coolant flow rates were investigated.For calculation,governing equations were discretized with second order upstream scheme.The results show that at sea level,coolant flow rate affects the plug pressure,heat flux and temperature;at design operating condition,coolant flow rate has no effect on pressure and heat flux on the plug wall.With the same coolant flow rate,plug temperature at sea level is higher than that at design operating condition;under the same operating condition,ramp temperature is higher than the plug base temperature.
Nmerical analysis of SRM's safety under nmechanic impact
CHEN Guang-nan, ZHANG Wei-hua
2006, 21(4): 784-788.
Abstract PDF(1681KB) icon2025 icon450
Abstract:
Based on the meso-scale model for the hot-spot of crack friction in solid propellant,with the consideration of the theory of thermo-visco-elasticity and using the method of hydrodynamic finite elements,numerical investigations of solid rocket motor(SRM) structural deformation and hot-spot formation in SRM's grain under mechanic impact were carried out,in which the effect of viscous heating in the solid propellant matrix was also considered.Critical impact velocities for the solid propellant ignition were determined.In comparison with the results of impact tests of the energetic material samples and small SRM,it is showed that results obtained through numerical analysis agree reasonably well with that of experiments.

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