2008 Vol. 23, No. 1

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Study on thermal fatigue life prediction for plasma sprayed thermal barrier coatings on the surface of turbine vane
WEI Hong-liang, YANG Xiao-guang, QI Hong-yu
2008, 23(1): 1-8.
Abstract PDF(1974KB) icon2339 icon477
Abstract:
According to the deformation characteristics of plasma sprayed ceramic thermal barrier coatings(TBC) and directional solidified superalloy substrate,viscoplastic constitutive models were introduced.Static oxidation test and thermal fatigue test of thermal barrier coating structures were conducted along with related FEManalysis.Alife prediction model for TBCwas established for presenting the coupling effect of oxidation damage and thermal fatigue damage.The steady temperature field,thermal barrier effect,and the macro-scale stress/strain fields of 3-dimensional turbine vane with TBCwere calculated and analyzed.The relationship between macro and micro-scale under scanning electronic microscopy of FEM(Finite Element Method) results was investigated.Amethod of equivalent coefficient was proposed while the thermal fatigue life for TBCon the surface of turbine vane was predicted,showing that the life prediction results are reasonable and the method is feasible.
Research on self-adaptive de-noising technique for rotor faults signal based on wavelet analysis
CHEN Guo
2008, 23(1): 9-16.
Abstract PDF(2453KB) icon1454 icon449
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In the current research on wavelet de-noising for rotor faults signal,the denoising effect often depends on the decomposing layer number,rotor rotating speed and signal sampling frequency.But,the de-noising process can not be realized automatically.For this reason,a new self-adaptive de-noising method for rotor fault signal was developed.Firstly,original data was re-sampled,secondly,re-sampled signal was decomposed to given layer number,finally,de-noising was achieved by Donoho soft threshold method.The de-noising process can be performed automatically without manual selection of decomposing layer number.Anumber of examples from simulation and experiments verify the efficiency of this new method.
Analysis method for same-stage-blade system strength reliability concerning the correlation
LU Shan, GAO Ya-juan, LÜ Wen-lin
2008, 23(1): 17-20.
Abstract PDF(330KB) icon1643 icon410
Abstract:
An analytical method for the strength reliability of the same-stage-blade system was proposed.The method covers numerical simulation and determination of the correlation coefficients of the same-stage-blade material strength and the strength limit state function.Moreover,the narrow limit formula for the same-stage-blade system strength reliability was presented.Then,the reliability calculation methods of the same-stage-blade system strength were discussed by taking into account failure-related factors.Finally,a numerical example of same-stageblade system was given to demonstrate the efficiency of the method.
Investigation and application of non-contact rotor blade vibration measurement technique
LI Yong, HU Wei, WANG De-you, LI Qi-han
2008, 23(1): 21-25.
Abstract PDF(778KB) icon1776 icon445
Abstract:
This paper briefly describes non-contact rotor blade vibration measurement analysis methods.Theoretical analysis was conducted for both asynchronous and synchronous resonant vibrations.This system has been applied successfully in compressor and engine testing and the theoretical predictions were validated by results from strain gauge measurement.
An iterative RBF ANN response surface method for structural reliability analysis
JIANG Xiang-hua, YANG Xiao-guang, WANG Yan-rong
2008, 23(1): 26-31.
Abstract PDF(690KB) icon1963 icon463
Abstract:
Structural reliability index for response surface method of RBF ANN was developed,which could resolve the error of structural reliability when the structure performance function was nonlinear or the variables were nonnormally distributed.An improved approach named as iterative radial basis function(RBF) artificial neural network(ANN) response surface method(RSM) was characterized by rapid iterative convergence speed,higher calculation accuracy and simple process.This method allows for reliability analysis and design of structure comprising multiple random variables,especially when the structure performance function is highly nonlinear or the variables are nonnormally distributed.
Design of simulated specimen for low-cycle fatigue of turbine engine disk
LIU Ting-yi, GENG Rui, ZHANG Jun-feng
2008, 23(1): 32-36.
Abstract PDF(688KB) icon2031 icon424
Abstract:
Based upon the research on many influential factors to the fatigue and bigger estimation error of fatigue,the stress field of actual component was proved to be a key influential factor.Aspecimen was then studied to optimize the geometric parameters through the given stress curve,so that the maximum stress and stress field correspond to the actual component stress field.Based on the platform of ANSYS,it's learnt that the simulation result is very close to the actual component life.This mode provides a simple and cost-effective solution for the component fatigue test.
Application of symplectic geometry algorithm to the calculation of random response of the dynamic system
LUO Wu-kui, XING Yu-feng, YANG Rong
2008, 23(1): 37-43.
Abstract PDF(512KB) icon1558 icon439
Abstract:
Duffing system was linearized by equivalent linearization method based on energy difference,then,the random response of the linear system was solved by combining the pseudo excitation method and four-order symplectic geometry algorithm.It is concluded that an approach to combine the pseudo excitation method,symplectic geometry algorithm and equivalent linearization method is accurate and efficient.
Blade-root vibration monitoring method for blade vibration stress monitoring and its implementation techniques
QU Yu-chi, LIU Jun-cang, ZHANG Yong-feng, ZHAO Shu-yuan
2008, 23(1): 44-49.
Abstract PDF(645KB) icon1673 icon493
Abstract:
This paper puts forward a method for monitoring aero-propeller blade vibration stress-the blade-root vibration monitoring method.We can obtain the blade root vibration excitation by monitoring propeller vibration and establish a transfer matrix model for blade vibration calculation,and then calculate the vibratory response and stress of the blade.In this way the blade vibration stress monitoring can be realized.The blade root vibration parameters may be acquired by direct measurement or by calculating with the measured vibration at the bearing case of the propeller rotator.Finally,this method is verified by checking the calculated results against the measured results in flight test.The results show that the blade root vibration monitoring method is simple and feasible in engineering applications.
Analysis of mechanical properties of composite case after impact
CUI Hai-po, WEN Wei-dong
2008, 23(1): 50-54.
Abstract PDF(928KB) icon1333 icon467
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A 3D progressive damage model and finite element method were used to analyze the impact properties and mechanical properties of composite case after impact under static loading.The matrix-cracking,matrix-crashing,delamination,and fiber breakage may occur in the case after impact.When the impact energy exceeds 26 J,the impact damage can spread rapidly under the given static loading.
High-order scheme and its application to the computation of the internal and external flow field
WANG Bao-guo, LIU Shu-yan, JIANG Guo-yi, LI Xiang, ZHANG Feng
2008, 23(1): 55-63.
Abstract PDF(1292KB) icon1569 icon418
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High-order scheme includes two different concepts,one is the high-accuracy scheme;the other is the high-resolution scheme,both of which are closely correlated but also strictly differentiated.In the construction of concepts,high-resolution scheme is much difficult than high-accuracy scheme.The applications of these two schemes in correlative fields were presented with numerous examples in four aspects.Agreat number of numerical results and researches indicate that,the computational results obtained from low-order schemes are not close to the experimental results for complex flow fields,especially since the interaction between the shock wave and the boundary layer and the flow fields of thermal conductivity have to be considered.So,developing the high-order scheme is crucial to resolving the cooling problem of the film of the high-temperature turbo and calculation of aerothermodynamic of hypersonic aircrafts.
A flux-weighted compact scheme
YUAN Xiang-jiang, TU Guo-hua, XU Tan, LU Li-peng
2008, 23(1): 64-69.
Abstract PDF(619KB) icon1573 icon416
Abstract:
With introduction of flux-weighted concept into the compact scheme,a new flux-weighted compact scheme was presented by combining classical scheme and compact scheme.This scheme and a 2nd-order total variation diminishing(TVD) scheme were used to calculate one-dimensional square waves,combine waves and some Riemann problems,such as Sod problem and Shu problem,as well as one-dimensional steady shock.The results show that the new scheme has advantage over the 2nd-order TVDscheme in capturing various discontinuities or resolving various complex waves.The results solved by the new scheme are also highly consistent with exact solutions.
An experimental investigation of two-microphone method for in situ measurement of the acoustic impedance of a duct liner
WANG Guang-fa, JING Xiao-dong, SUN Xiao-feng
2008, 23(1): 70-74.
Abstract PDF(1155KB) icon1769 icon524
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The two-microphone method is investigated for the objective of in situ measuring the impedance of an acoustic liner in a duct.In order to avoid the influence caused by directly inserting the comparatively large microphones into a practical acoustic liner typically consisted of small honeycomb cells,the probe tubes as small as 1.5 mm in diameter are used to conduct the sound pressure at the liner surface and that at the back plate to the microphones.Acalibration method is designed to ensure high measurement accuracy of the thus-formed probe microphones.By the use of the two-microphone method,the acoustic impedance of a honeycomb-structure acoustic liner is measured when exposed to the sound waves at oblique incidences inside a duct.The measurement result is compared with the data obtained on a standard impedance tube and the prediction of an existing impedance model.The reliability of the present two-microphone method is validated by the good agreement between the different results.
Thrust/lift system parameters optimization of gyroplane with jump takeoff capability
ZHU Qing-hua, LI Jian-bo, NI Xian-ping, ZHANG Cheng-lin
2008, 23(1): 75-80.
Abstract PDF(717KB) icon1796 icon610
Abstract:
For designing modern gyroplane with jump takeoff capability,the characteristics of thrust/lift system parameters are investigated,and a multiobjective optimization method is presented.To calculate thrust/lift,the mathematical model is established through numerical integral method based on blade element theory and dynamic inflow theory.The jump takeoff is modeled on the basis of autorotating rotor aerodynamic characteristics and energy equation.The impact of parameters on jump takeoff performance is analyzed,and a computation example shows that the model is feasible and efficient.The multiobjective optimization design of the parameters is carried out hierarchically by using improved genetic algorithm and design for six sigma(DFSS).The optimized result indicates that the method is accurate and the general performance of gyroplane with these parameters is advanced.
Study of bypass transition mechanisms in the boundary layer of blunt bodies
YUAN Xiang-jiang, LU Li-peng, SHEN Qing, TU Guo-hua
2008, 23(1): 81-86.
Abstract PDF(7520KB) icon1689 icon375
Abstract:
A new instability mechanism in the boundary layer of blunt bodies was studied under reentry conditions by using numerical simulation method.The instability mechanism cannot be addressed by linear instability theory.The recent research shows that,there is a nonlinear instability mechanism associated with local finite amplitude disturbance,which differs from the ordinary instability with respect to the T-Swave and secondly instability.The instability process under the influence of the local disturbance in the boundary layer of blunt bodies was simulated numerically.The physical mechanisms for nonlinear interaction of various disturbance modes were identified in the simulation.
Analysis of dynamic simulation and fluid field of parachute in inflation stage
PAN Xing, HU Li, CAO Yi-hua
2008, 23(1): 87-93.
Abstract PDF(1879KB) icon2226 icon523
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The axis-radial momentum equations of circular flat parachute were established the changing parameters of a selected parachute were calculated for dynamic simulation of the inflation process.Accoroling to the inflation model calculated by the momentum equation,based on the shape and descent velocity of the parachute at fixed nodes of time,the fluid field was simulated and analyzed according to computational fluid dynamics method under quasi-steady hypothesis.The mechanism of inflation and evolvement of fluid field were analyzed.
Study of aerodynamic model for the maneuvering rotor
XU Jin, GAO Zheng
2008, 23(1): 94-99.
Abstract PDF(715KB) icon1665 icon461
Abstract:
To improve the prediction of the rotor's off-axis aerodynamic response,the wake distortion effect of maneuvering rotor was studied with the introduction of time-accurate wake curvature parameter(KR) into the maneuvering rotor model.As compared with existing approaches,the computed results from this model are more close to the test data.Besides,a dynamic wake distortion model was constructed,while the necessity of incorporating the wake contraction effect was analyzed.The research results show that: the operating-state-dependent(KR) shall be applied to aerodynamic models in order to calculate accurately the rotor aerodynamic forces and moments,especially for off-axis response.
Study of phase-lag algorithm for unsteady flow of compressor
YAN Ming, SUN Li, LIU Xiang-feng
2008, 23(1): 100-105.
Abstract PDF(765KB) icon1616 icon471
Abstract:
Phase-lag boundary conditions were applied in unsteady flow calculation of turbomachinery by not changing the real frequency of rotor wake and potential disturbance of stator,with a 1∶1 ratio of rotor/stator.Based on the computations over NASA Stage67,the results were found to match the experimental data,showing that the method is suitable for engineering applications.
Study on aerodynamic optimization design of multistage axial turbine under multiple working conditions
ZHAO Hong-lei, WANG Song-tao, HAN Wan-jin, FENG Guo-tai
2008, 23(1): 106-111.
Abstract PDF(1356KB) icon1641 icon443
Abstract:
A three-stage axial turbine was redesigned by using an aerodynamic optimization design process of multistage axial turbine in multiple working conditions,which combines quasi-3Ddesign methods and multistage local optimization methods.Genetic algorithm and artificial neural network were employed to 3Dlocal optimization of various cascades.The flow field was computed through a three-dimensional viscosity Navier-Stokes equation.With optimization design,the performance of every cascade was optimized,and the overall efficiency increased by 1% under the reliable total flow mass,indicating that the total performance was improved to satisfy the design requirements.
Some discuss on technology trend and aerodynamics problem of adjustable blade
XIONG Jin-song, HOU An-ping, YUAN Wei, ZHOU Sheng
2008, 23(1): 112-116.
Abstract PDF(889KB) icon1561 icon508
Abstract:
Current adjustable blade application in military aero-engine was discussed and the further development trend was predicted.High load,high mach number,broad flow angle range,and low flow loss level will be pursued.Aerodynamic analysis was carried out on a flectional cascade.It indicates that flectional cascade is an excellent solution for turning angle control in compressors.But still more work is needed on advanced adjustable cascade with higher turning angle and higher mach number.
Effects of stator clocking on unsteady aerodynamic loads of a compressor blade
YAN Pei-gang, LI Shao-bin, Chen Fu, WANG Zhong-qi
2008, 23(1): 117-124.
Abstract PDF(1000KB) icon1572 icon464
Abstract:
Numerical simulation was applied to the unsteady flow at the mid span of a twostage low-speed compressor.The aerodynamic load of the second row of stator blade at two typical circumferential positions was investigated.The influence of unsteady aerodynamic load of each blade cascade and the stator clocking effect on blade aerodynamic load was also analyzed.Through spectrum analysis of the unsteady aerodynamic forces and moments of each blade cascade,the unsteady aerodynamic interferences between blades were discussed.The results show that,the influence of stator clocking effects on the stator blade's unsteady aerodynamic loads is larger than that on the rotor blade.Stator clocking effect can help improve the compressor performance and its blade service life.
Research on effect of slot inlet angle and turning angle on the flow field characteristic of cascade
ZHOU Min, WANG Ru-gen, CAO Zhao-hui, ZHANG Xiang-yi
2008, 23(1): 125-129.
Abstract PDF(921KB) icon1997 icon479
Abstract:
The effect of slot inlet angle and turning angle on flow field characteristic of cascade with slot was studied numerically.The result shows that slot outlet jet can blow off separation flow of boundary layer on the trailing edge of suction surface and enhance cascade performance.An optimal slot inlet angle exists,at which the cascade performance is best.When the slot inlet angle increases from the optimal point,the flow loss increases due to larger geometrical turning angle of the slot,which in turn leads to a lowered speed of slot outlet jet and consequently,its effect is reduced.When the slot inlet angle decreases from the optimal point,the accelerating effect of slot is reduced due to less differential static pressure,thus the effect of jet would also be reduced.
Research on permeability and flow resistance characteristic of sintered porous structure
SUN Ji-guo, WANG Jian-hua
2008, 23(1): 130-133.
Abstract PDF(369KB) icon1621 icon501
Abstract:
To study the permeability and flow resistance of sintered porous stainless steel,a test was conducted for compressed air and gaseous hydrogen as the medium.The experimental results indicate that,there is a linear relationship between the pressure loss through the porous structure and the medium flow rate,when the flow Reynolds number in the pores is less than 1;or there is a non-linear characteristics when Reynolds number is larger than 1.This shows that:the flow friction of gaseous hydrogen or air within the pores is underestimated using the traditional correlations based on the experiments of packed beds;but the permeability of the sintered porous structure is overestimated by the Ergun's corrective correlation.The relationship between the friction resistance and permeability of hydrogen or air flowing through the porous structure was simulated with the aid of the experimental data.
Effect of various gases on the energy separation performance of vortex tube
ZHANG Guo-qing, WU Yu-ting, DING Yu, MA Chong-fang
2008, 23(1): 134-137.
Abstract PDF(483KB) icon1636 icon410
Abstract:
The energy separation performance of the vortex tube with various gases,such as air,nitrogen,argon and carbon dioxide,was studied in the experiment,whereby cold and hot characteristic curves,refrigeration output,unit refrigeration output and coefficient of performance(COP) versus cold flow rate were obtained.The results indicate that cold and hot effects are closely related to mol mass: the bigger the mol mass,the better the cold and hot performance will be;additionally,these effects are subjected to the coefficient of Joule-Thomson to some extent.Refrigeration output and COPalso have a corresponding direct correlation with mol mass,in addition to refrigeration effect and specific heat at constant pressure.
Numerical and experimental study on flow and heat transfer performance of some compact surface recuperators
PENG Hao, SUN Zhi-jiang, LING Xiang
2008, 23(1): 138-144.
Abstract PDF(806KB) icon1371 icon460
Abstract:
A unit control model was established using computational fluid dynamic(CFD) method,while the heat transfer and fluid flow performances on primary surface of recuperator(stainless steel serrated fin and cross corrugated(CC) primary surface) were simulated numerically and also compared with the experimental results.The results show good consistency between numerical simulation and experimental data.To this end,the effect of CCsurface structural parameters on heat transfer performance was discussed,and then the heat transfer and flow characteristics were compared for different structural scales and surface arrangements,thus providing a basis for design optimization of recuperators.
Research on the feasibility of displacing the single annular combustor with a dual annular combustor
LI Feng, SHANG Shou-tang, CHENG Ming, PENG Lang-qing, YANG Hui, SONG Bo
2008, 23(1): 145-149.
Abstract PDF(884KB) icon1727 icon429
Abstract:
The combustor was redesigned into dual annular structure in radial direction,under the precondition that the diffuser,outer case and exit dimension are kept consistent with single annular combustor(SAC).With the help of the same physical models,a 3-Dsimulation for full-flow process in both SACand dual annular combustor(DAC) was conducted in the Fluent code.By using the DAC,it shows that the total-pressure recovery coefficient and combustion efficiency can be improved remarkably,the exit temperature distribution coefficient of the combustor and NOx/COemission,especially for COemission under slowrunning state,is reduced accordingly.
Numerical study on flow field in three supersonic combustors
ZHOU Jian-xing, PIAO Ying, CHEN Mei-ning, QI Xing-ming, LIU Zhao-shu
2008, 23(1): 150-155.
Abstract PDF(950KB) icon1605 icon487
Abstract:
The supersonic combustion in three different combustors was numerically investigated by solving the compressible Navier-Stokes equations with implicit finite volume method.The results show that the cavity can change the waves in combustors,and facilitate the mixing of hydrogen and air for easier combustion. Besides,the relatively steady reversing area in cavity can be used to ignite and stabilize the flame;ejection of secondary hydrogen can neutralize the problems induced by injecting hydrogen only one time,and also improve the mixing and combustion of hydrogen and air,in despite of slightly larger total pressure loss.
An adaptive terminal sliding mode control and its applications
HUANG Guo-yong, JIANG Chang-sheng, XUE Ya-li
2008, 23(1): 156-162.
Abstract PDF(505KB) icon1511 icon397
Abstract:
A novel adaptive Terminal sliding mode control based on fast fuzzy disturbance observer is designed for a high order MIMO(multiple-input multiple-out-put) nonlinear system.To solve the shortcoming of learning slowly of traditional fuzzy disturbance observer when the approximation errors are very small,a fast fuzzy disturbance observer is designed.It is strictly proved that the tracking errors and approximation errors converge to very small regions in finite time.Finally,simulation results of ASV(aerospace vehicle) re-entry demonstrate the effectiveness of presented control scheme.
Fault diagnosis for aeroengine gas path components based on neural network multisensor data fusion
ZHAO Shi-rong, HUANG Xiang-hua
2008, 23(1): 163-168.
Abstract PDF(791KB) icon1901 icon422
Abstract:
A fault diagnosis method for aeroengine gas path components,which was based on the technology of neural network multisensor data fusion and combined application of fuzzy logical theory,was studied in the paper.And this method was employed in simulation analysis of a given turbo-shaft engine.The whole diagnosis process of this method is simple and high accuracy of modeling is not required.Fault alarm,mistaken report and false positive can be reduced.
SRUKF research on aeroengines for gas path component fault diagnostics
ZHANG Peng, HUANG Jin-quan
2008, 23(1): 169-173.
Abstract PDF(1293KB) icon1659 icon459
Abstract:
An algorithm based on square root unscented Kalman filter(SRUKF) was presented to solve the aeroengine health parameter estimation problem.The SRUKFmethod could be applied to addresses the estimation inaccuracy of linear Kalman filter and the filtering divergence problem caused by error covariance matrix non-positive in general unscented Kalman filter.Amethod for improving the filtering convergence rate and stability was developed according to the residual vector.The results obtained from gradual and abrupt fault diagnostic simulation show that,SRUKFfeatures rapid convergence,higher stability and accuracy,making it become an efficient estimation and fault diagnosis method for health parameters of gas path components in aeroengines.
Multi-objective optimization of aeroengine PID control based on multi-objective genetic algorithms
LI Yue, SUN Jian-guo
2008, 23(1): 174-178.
Abstract PDF(500KB) icon2205 icon468
Abstract:
Multi-objective genetic algorithms were applied to the parameter optimization of aeroengine proportional integral derivative(PID) controller.The PIDcontroller parameters of aeroengine were optimized by multi-objective genetic algorithms NSGA-Ⅱ.In this paper the controller parameters of an aeroengine was optimized,and the simulation results indicate that compared with the traditional optimization method,the speed controller system shows good dynamic and stable performance.The result is satisfactory.
Study on operating temperature of high-speed cylindrical roller bearings
WANG Li-qin, CHEN Guan-ci, GU Le, ZHENG De-zhi
2008, 23(1): 179-183.
Abstract PDF(1187KB) icon1915 icon471
Abstract:
Heat generation between rollers and raceways treated as moving heat source,a model for calculating the temperature field of a high-speed cylindrical roller bearing was set up.Aparametrical code has been developed with the APDLlanguage of ANSYS.Using this code,the operating temperature of cylindrical roller bearings with different types of lubricants can be obtained more accurately when boundary conditions such as heat flux are input.Taking one model of bearing as an example,effects of various operating parameters on operating temperature have been analyzed.It is shown that the rotational speed of the inner ring,the radial load and the inlet temperature of the lubricant have a great influence on operating temperature of the bearing.
Optimization design for single-crank and double-rocker kind of driving mechanism of FMAV
ZHOU Kai, FANG Zong-de, CAO Xue-mei, ZHANG Ming-wei
2008, 23(1): 184-188.
Abstract PDF(1376KB) icon1720 icon513
Abstract:
Flapping-wing micro air vehicles(FMAV) often tilt toward the left or the right and fall off in the course of flight,and this is mainly caused by the incomplete symmetry of the wings' movement.Models of the margins of the flapping-angle and angular speed between the left wing and the right wing were established;and an optimization design for the objective function was carried out by using Hooke-Jeeves method under restraint conditions of mechanics,bionics and aerodynamics.Both comparative analysis of parameters before and after optimization and flight test indicate that the optimization can remarkably improve movement symmetry of flapping-wing micro air vehicles.
Tooth surface design of spiral bevel gears based on meshing performances and work offset
CAO Xue-mei, FANG Zong-de, XU Hao, ZHU Zi-bing
2008, 23(1): 189-194.
Abstract PDF(1068KB) icon1645 icon426
Abstract:
Three meshing points on the tooth surface were designed according to the contact pattern and transmission errors.The meshing quality was controlled exactly through control of these three meshing points.To meet different processing demands,the processing parameters of pinion was redesigned according to the given value of work offset,thus maintaining the magnitude of transmission error with little variation of contact pattern.In the end,a pair of gears was designed by Gleason software and this approach respectively,showing the consistency of these two designs by comparing the tooth surface,contact pattern and transmission errors.
Numerical calculation of the radiative heat transfer and wall temperature of the rocket nozzle
ZHANG Xiao-ying, CAI Guo-biao, ZHU Ding-qiang
2008, 23(1): 195-200.
Abstract PDF(1544KB) icon2138 icon469
Abstract:
The computation methods for the coupled heat transfer and transient wall temperature of composite walled rocket nozzle were studied.While the stable ablative calculation for C/Cthroat insert was considered,the Enclosure-Radiative Heat Flux model was established to compute the radiative heat transfer in the nozzle,thus improving the calculation method of radiative heat transfer.The time-dependent variations of wall temperature for two composite walled nozzles were computed,and also compared with the results in the literature.The research shows that,the radiative heat transfer is stronger than the convective heat transfer in the entrance section of the nozzle;the Enclosure-Radiative Heat Flux model could compute more precisely the radiative heat transfer of the rocket nozzle.

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