2007 Vol. 22, No. 12

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Experimental study of fueling match on EBMC flame holder and frontal atomizing platelet injectors
MA Wen-jie, YANG Yang, LIU Yang, FAN Wei-jun, YANG Mao-lin
2007, 22(12): 1977-1983.
Abstract PDF(1244KB) icon1616 icon483
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An experimental study on the fuel match of main fuel and local fuel of EBMC Flame holder was conducted using a main atomizing platelet injector.Meanwhile,the performance characteristics of EBMC Flame holder were presented.In order to demonstrate the advantage of this new type of atomizing platelet injector by which fuel was injected into the cross flow,two different types of flame holders were used as main flame holders.Its combustion performance was compared with that of atomizing platelet injector by which fuel was injected into the opposed flow.The experimental results show that combustion performance of the atomizing platelet injectors by which fuel was injected into the cross flow is superior to that of the other one within the range of operating conditions of this experiment.
3-D numerical investigation on supersonic hydrogen combustion in scramjet combustor
ZHOU Jian-xing, PIAO Ying, QI Xing-ming, ZHU Jian-hong
2007, 22(12): 1984-1988.
Abstract PDF(1076KB) icon1972 icon477
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3-Dnumerical simulation for supersonic hydrogen combustion was performed by solving the compressible Navier-Stokes equation and composition equations using implicit finite volume methods.Meanwhile,the effect of hydrogen injection pressure on combustion was analyzed and studied.The results show that,owing to the heat release from combustion and the influences of hydrogen's injection pressure,the flow field changes greatly,leading to enhanced streamwise vortex and stronger interaction between waves in the combustor and hydrogen flow,and also facilitating the mixing of hydrogen and air for improved hydrogen combustion performance.
PIV experimental study of primary zone flow field of convergent sleeve
LIN Yang, LIN Yu-zhen, LIU Gao-en
2007, 22(12): 1989-1993.
Abstract PDF(759KB) icon1777 icon476
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The primary zone flow field of the swirler's convergent sleeve was measured by PIVtechnology under atmospheric pressure and temperature,providing detailed information on the primary zone flow field and vorticity field.The results show that the primary zone flow field of the convergent sleeve has a structure of small recirculation and big corner swirls,and the constriction of convergent sleeve on circumgyrated air could improve the mixing of air and fuel in a combustor.
Experimental investigation of infrared suppressing characteristics of rectangular nozzles with large aspect ratio
ZHANG Bo, JI Hong-hu, LUO Ming-dong, HUANG Wei, CAI Xu, GAO Chao
2007, 22(12): 1994-1999.
Abstract PDF(1132KB) icon1708 icon491
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The infrared suppressing characteristics of five rectangular convergent nozzles with different aspect ratios were investigated experimertey.The aspect ratio of the rectangular nozzles is 1,4,8,12,and 16,named AR1~AR16 respectively,while the axisymmetric nozzle is named AR0.The results indicate that infrared radiation from rectangular nozzle decreases with the increase of detection angle,and the magnitude of infrared radiation is smaller than axisymmetric one,and would accelerate with the rise of aspect ratio.
Experiment of IR suppression for hot plume from turbofan engine with convection-radiation board
HUANG Wei, JI Hong-hu, LUO Ming-dong, LEI Jin-guo, CAI Xu, GAO Chao
2007, 22(12): 2000-2005.
Abstract PDF(766KB) icon2071 icon527
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Convection-radiation board was employed to suppress the infrared radiation of hot plume from turbofan engine,while experimental research was conducted on the hot plume simulation test bench of turbofan engine.The temperature distribution of hot plume from a pure axisymmetric nozzle,and the spectral radiant intensities of hot plume in3～5 μm from a pure axisymmetric nozzle and 2Dnozzles were measured.The results show that convection-radiation board could reduce the temperature of plume core about 10%,and also suppress the infrared radiation of hot plume from turbofan engine about 20%30%.
A prediction model of film-cooling adiabatic effectiveness based on cohence non-isothermal jet theory
ZHANG Chi, LIN Yu-zhen, XU Quan-hong
2007, 22(12): 2006-2011.
Abstract PDF(587KB) icon1713 icon507
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To predict the slot film-cooing adiabatic effectiveness,a mathematic model was developed based on cohence non-isothermal jet theory.The core temperature distribution of mixing layer in2Dwall jet was deduced through reasonable assumptions,and the temperature was regarded as the adiabatic wall temperature.In addition,this influence of slot geometry parameter and film blowing ratio on the cooling effectiveness was also considered,so the adiabatic effectiveness equation was obtained.The empirical coefficients in this prediction model should be fitted to the experimental data,showing that the present prediction model has an accuracy of within ±8% to all previous experimental data.The feasibility and potential application of this model have been demonstrated,and more experimental data are required for future verification and improvement.
Cold flowfield experiment study of an inlet Mach number 2.5 scramjet combustor with a stream-wise vortices mixer between supersonic/subsonic-pilot-combustion flow
JIE Ke, YANG Zhan-yu, ZHAO Lü-shun, LIU Jian, WANG Hong-ming, HUANG Yong, SHAN Peng
2007, 22(12): 2012-2017.
Abstract PDF(1291KB) icon1664 icon535
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An experimental study of cold flow field was conducted under entrance Mach number 2.5 on a supersonic combustor experiment rig with subsonic pilot combustor and stream-wise vortices mixer.The experiment result suggests that the up-wall static pressure distribution of wall surface and shock wave structure coincide with the CFDcalculation results,and the full flow field supersonic combustor reaches the design state.The cold test data and CFDcalculation data under 2.5Mach provide a basis for ignition test.
Numerical simulation of conjugate heat transfer for an internally cooled 3-D turbine blade
SU Sheng, LIU Jian-jun, AN Bai-tao
2007, 22(12): 2018-2024.
Abstract PDF(1320KB) icon1860 icon537
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To study the internal cooling technology of turbine blade,three types of blades,i.e.non-cooled blade using adiabatic boundary condition,non-cooled blade using conjugate heat transfer method,and air-cooled blade using conjugate heat transfer method,were studied.The results show that heat conductivity of the blade has a significant influence on blade temperature distribution;the structure of rib-roughened cooling and latticework cooling makes the blade temperature drop markedly.However,this leads to increased non-uniformity of blade temperature distribution and irregular heat transfer coefficient distribution on the blade surface.
Experimental investigation of using plasma aerodynamic actuation to extend low-speed axial compressor's stability
WU Yun, LI Ying-hong, ZHU Jun-qiang, SU Chang-bing, LIANG Hua, SONG Hui-min, LI Gang
2007, 22(12): 2025-2030.
Abstract PDF(646KB) icon1699 icon500
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The effect of plasma aerodynamic actuation on low-speed axial compressor performance and stability range was investigated experimentally.Aplasma aerodynamic actuation treated casing(PAATCTM) was designed.Asingle low-speed axial compressor rotor with no inlet guide vanes was tested.Pressure rise coefficient and flow coefficient for the compressor test rig were calculated with/without plasma actuation at a constant rotor speed to represent compressor performance and stability range.The experimental results show that,with plasma actuation,the mass flow coefficients near stall is decreased by 5.2% and 5.07% when the rotor speed reaches 900 r/min and 1080 r/min respectively.The influences of different actuation voltages and different actuation locations were investigated experimentally.Compressor's stability became larger along with the rise of actuation voltage.The actuation away from rotor's leading edge for 49.5% axial chord can extend compressor's stability more than the actuation away from the rotor's leading edge for 8.3% axial chord.
Study of staged propagation of circumferential steady total pressure distortion in axial flow compressors
RUI Chang-sheng, WU Hu
2007, 22(12): 2031-2035.
Abstract PDF(468KB) icon1622 icon453
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Based on the stage characteristics of axial flow compressor,a new model was established for calculating the propagation of circumferential steady total pressure distortion in multistage axial flow compressors.The inlet angle of attack,circumferential flow of stages and coupled compressor diffuser flow were also analyzed numerically.Meanwhile,the influences of axial attenuation of circumferential steady total pressure distortion,unsteady primary level and coupling performance of compressor outlet on the characteristic of compressor were discussed.Based on this model,the multistage axial flow compressors were analyzed numerically,proving that this model is reasonable and feasible.
Investigation of aspirated compressor cascade flow fields using numerical simulation method
ZHOU Zheng-gui, WANG Chuan-bao
2007, 22(12): 2036-2042.
Abstract PDF(1498KB) icon1922 icon462
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To explore the application of boundary layer aspiration technology in compressor stator blade profiles of potential regions,the cascade flow fields were simulated numerically.The results indicate that:(1) for high subsonic inlet flow,the boundary layer in blade suction surface being aspirated can increase the cascade pressure rate and flow turning angle,but not always reduce flow loss;(2) for middle subsonic inlet flow,the boundary layer in blade suction surface being aspirated can increase the cascade pressure rate,flow turning angle and reduce flow loss;(3) if there is flow separation region in rear part of blade suction surface,the aspiration position located upstream far from the region can eliminate flow separation;but the separation region can not be eliminated if the aspiration position is near or within the region.
Accuracy verification and efficiency analysis of parallel program based on MPI
JIANG Xiao-song, LIU Jian-jun
2007, 22(12): 2043-2049.
Abstract PDF(1127KB) icon1542 icon519
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An existing serial computational fluid dynamics(CFD) program was modified to a parallel simulation program based upon message passing interface(MPI).Four flow fields of different combinations for NASA-TP1680 single-stage turbine were simulated to validate the accuracy and parallel efficiency of the parallel program.The major influential factors to the parallel efficiency were also analyzed.
Investigation of the influence of splitter chord length on the transonic axial fan rotor
SUN Xi-miao, YAN Pei-gang, WANG Song-tao, WANG Zhong-qi
2007, 22(12): 2050-2054.
Abstract PDF(917KB) icon1625 icon492
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An axial transonic fan with splitter was designed.An optimization method was used to eliminate the influence of the splitter camber shape.The effect of splitter chord length on the aerodynamic performance of the fan rotor was analyzed under the maximum efficiency condition.The results show that the leading edge expanding wave can adjust the length of the main blade boundary layer negative gradient and its strength.Correctly selecting the splitter leading edge position can reduce the boundary loss,control the separation at the rear part of the main blade and produce optimal aerodynamic load distribution.
Application of fourier pseudo-spectral method in the incompressible boundary layer on a flat plate
LI Ning, LUO Ji-sheng
2007, 22(12): 2055-2061.
Abstract PDF(2591KB) icon1506 icon453
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Three-dimensional incompressible boundary layer on a flat plate was studied where disturbance N-Sequation was taken as governing equation.The evolution of three-dimensional instability T-Swave was simulated by spatial DNS(direct numerical simulation) in which third-order precision mixed explicit-implicit scheme was employed for temporal discretization while a method combining Fourier pseudo-spectral method with high precision compact finite difference was implemented for spatial discretization.Acoordinate transform of nonuniform meshes was applied in normal direction,fringe method was adopted as exit boundary condition and MPImethod was used in programming.Through a simple case,the results obtained by this method were tested to be in consistence with the ones obtained with stability theory.
Modeling and analyzing of low pressure pipeline transients accompanying gas bubbles and cavitation
JIANG Dan, LI Song-jing, BAO Gang
2007, 22(12): 2062-2067.
Abstract PDF(649KB) icon2097 icon479
Abstract:
In order to predict pressure transients accompanying gas bubbles and cavitation inside low pressure pipeline in hydraulic system of aerospace,pressure transient mathematical model was given to describe the flow behavior in the pipeline.By using finite difference method,partial differential terms of spatial dimension in differential equations can be calculated.Mathematic models were presented for calculation of effective bulk modulus,friction,gas bubble and cavitation volume during the transients.The model of low pressure pipeline transients involves three parameters,i.e.initial gas bubble volume in oil,gas releasing time constant and resolving time constant.By making use of genetic algorithms(GA),parameter identification for the mathematical model of pressure transients was performed.Thus the model with parameters identified from GAwas obtained and simulated.Comparison between simulation results and experimental data shows that low pressure transient model is capable of predicting pressure pulsation accompanying gas bubbles and cavitation.
Numerical simulation of the start-up process of augmented turbofan engines
WU Hu, FENG Wei-lin
2007, 22(12): 2068-2072.
Abstract PDF(1730KB) icon1767 icon484
Abstract:
An approximation method for simulating the low speed,low flow characteristics of axial flow fan,high-pressure compressors and high-/low-pressure turbines were presented,based on their high-speed characteristic maps and design point parameters of the engine.With the component matching technology of turbofan engines,a calculation model and corresponding algorithm for the start-up process of a certain turbofan engine was set up,thereby providing rational simulation results for the start-up process of engine.
Numerical simulation of flat plate plasma flow control
LI Gang, HUANG Wei-bing, ZHU Jun-Qiang, NIE Chao-Qun
2007, 22(12): 2073-2077.
Abstract PDF(1746KB) icon1716 icon471
Abstract:
Through Laplace equation and transformed Helmholtz equation in the electric field,this paper simulated successfully the plasma flow control in the flat plate.Abody force vector was introduced to the Navier Strokes equations to simulate the effect of plasma actuation on the flow.Debye length,maximum charge density and scale parameter,etc,could be determined by comparing the calculated result with experimental data.This helps to establish a numerical simulation method for flat plate plasma flow control,thus providing a crucial technical support for applying plasma flow control into external and internal sharp shear flow.
Experimental investigation of propulsion characteristic of flapping-wing MAV
ZHANG Ya-feng, SONG Bi-feng, YUAN Chang-sheng, WANG Li-guang
2007, 22(12): 2078-2082.
Abstract PDF(685KB) icon2158 icon445
Abstract:
In order to investigate the effect of aspect ration and stiffness and camber of flapping-wing on thrust force characteristic,the wind tunnel test of Flapping-wing MAV(Micro air vehicle) was performed in special micro air vehicle wind tunnel of NPU(Northwestern Polytechnical University).The rectangular wing which has the aspect ration of 2,4.5 and 7 and cambered aerofoil and flat aerofoil were fabricated.Structure strength of three different stiffness rectangular flapping-wings was analysed.The velocity(from 4m/s to 10m/s) and flapping frequency(between4Hz to 8Hz) were applied for test.In this experiment we find it improves thrust efficiency of flapping-wing through increase aspect ration or decrease stiffness of flapping-wing.It is disadvantageous to thrust characteristic through increase camber of airfoil.
Asymmetry stator mistuned blade design and research
MENG Yue, LI Lin, LI Qi-han
2007, 22(12): 2083-2088.
Abstract PDF(503KB) icon1685 icon431
Abstract:
To reduce the dynamic stress of rotor blades under the wake of front stator vane,an asymmetry stator mistuned design was conducted.According to mistuned blade design for the asymmetry stator,the wake force on rotor changed from single frequency and higher amplitude to multi-frequency and lower amplitude.The frequency and amplitude of wake force were deduced theoretically,while the influence of stator sector distribution and stator vane quantity on the wake force of vane was also discussed.Transient analysis was conducted for the forcing response of rotor blades under the same stator sector distribution and different quantities of stator vane,so an optimum asymmetry stator mistuned design was developed.
Numerical simulation of erosion and abrasion of separator blade coating
DENG Ying, YAN Xiao-jun, NIE Jing-xu
2007, 22(12): 2089-2093.
Abstract PDF(915KB) icon1371 icon441
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The damage evolution of blade coating in the erosion process was studied.Firstly,the flow field was measured;secondly,the erosion process of single solid particles was simulated to propose the concept "Effective erosion region",allowing to simulate numerically the erosion process of multiple solid particles.Next,the erosion resistance performance of coating materials in the "Effective erosion region" was simulated.The results show the weak coating region and provide life prediction by simulating the erosion process of blade coating with the flow field data and erosion resistance performance parameters.
Experimental study on bird damage of vortex vane in the particle separator
GUAN Yu-pu, ZHANG Zai-kun, ZHAO Zhen-hua, CHEN Wei, GAO De-ping
2007, 22(12): 2094-2100.
Abstract PDF(855KB) icon1433 icon483
Abstract:
The rule of damage on the vortex vane in the particle separator caused by bird impact was studied with a view to improve the resistance design of particle separator to foreign object damage.By the method of experiment on impact damage,the process in which the vortex vane in the particle separator is impacted by a model bird was researched.By using the system of measurement and test on transient response,the strain-time history of the vortex vane impacted by model bird was gained.Profile of the vortex vane before and after the impact inflicted by the model bird was obtained with a three-coordinate device.Through comparison and calculation the deformation of the vortex vane after the model bird impact was gained.It is found that plastic strain in the vortex vane emerges and the deformation of the vortex vane is very large when the model bird impacts the vortex vane at the velocity Ma=0.2.
Displacement transfer with the mesh deformation method in multidisciplinary optimization of turbine blades
LI Li-zhou, WANG Jing-chao, HAN Yong-zhi, LU Zhen-zhou, YUE Zhu-feng
2007, 22(12): 2101-2104.
Abstract PDF(830KB) icon1594 icon470
Abstract:
A mesh-deformation-based method was provided in transferring structural displacements to aerodynamics meshes for multidisciplinary optimization of turbine blades.The method focuses on disturbing interior nodes of aerodynamics meshes to keep mesh-quality for the deflected blades.The nodes was disturbed as if they are in a deformed solid under displacement loads.This solid represented the interrelationship of nodes of the aerodynamics meshes.Adisplacement transfer of a turbine blade was provided.The results indicate that the mesh-deformation-based method work well for the displacement transfer.
Optimization of inverse design of antimissile interceptor based on physical programming
WANG Zu-yao, LI Xiao-bin, ZHANG Wei-hua
2007, 22(12): 2105-2112.
Abstract PDF(1878KB) icon1678 icon457
Abstract:
The optimization method for inverse design of antimissile interceptor was put forward based on physical programming,and a multidisciplinary system analysis model was established.According to the performance parameters of antimissile interceptor in the literature,the antimissile interceptor was disposed as a "greybox" system.The performance parameters of antimissile interceptor were gained through research of inverse design optimization.
Design optimization of secondary chamber response surface of boron-based propellant ducted rocket motor
HU Jian-xin, XIA Zhi-xun, ZHAO Jian-min, GUO Jian, ZHANG Wei, LUO Zheng-bing, Miao Wan-bo
2007, 22(12): 2113-2118.
Abstract PDF(539KB) icon1997 icon489
Abstract:
There are a variety of influential factors to the combustion efficiency of secondary chamber of boron-based propellant ducted rocket motor,which are difficult to be expressed accurately by analytical functions.Atwo-phase turbulent flow combustion value simulation model was firstly established within the secondary chamber of the rocket motor.Then,the structural optimization of secondary chamber of Boron-based propellant ducted rocket motor was achieved through the response surface based on orthogonal polynomial.This method allows to compute less frequently the flow field of secondary chamber in obtaining the approximate functions,and makes it easier to optimize and analyze the parameters of secondary chamber of boron-based propellant ducted rocket motor.
Start-up experimental research on oxidizer-rich preburner
WANG Xiao-wei, JIN Ping, YU Nan-jia, CAI Guo-biao
2007, 22(12): 2119-2123.
Abstract PDF(465KB) icon1763 icon497
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In order to develop oxidizer-rich preburner technology of full-flow staged combustion cycle engine(FFSC),this paper planned the start-up experiment for an H2/O2 ox-rich preburner,and described their characteristics under test conditions.And,a fuel-rich ignition start-up mode was selected.The simulation study and test run of preburner show that,the calculated results match the test results,demonstrating that fuel-rich ignition for small flux ox-rich preburners is reliable and steady without any burning.This research and simulation lay a firm basis for future test and study of similar preburners.
Design and dimensional calculation of mounting holes of slipping shoe in piston pump
SHI Pei-lin, ZHANG Ting, GAO Yi
2007, 22(12): 2124-2133.
Abstract PDF(1436KB) icon2251 icon522
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Based on in-depth analysis of the operation of piston pump with the methods of coordinate conversion and track projection via the help of MATLABsoftware,the dimensional formation of mounting holes in the holder slipping shoe were presented,and the design and calculation methods were developed,which has the following advantages: all formulas are calculated by integrated theory,no rounding numbers are required;all outputs are accurate solutions,ensuring that all the outputs are real theoretical values;all dimensional design parameters of mounting holes in slipping shoe can be obtained in one calculation process.The simulation results indicate that the design method and dimensional calculation are correct.
Modeling of and simulation research on turbofan engine based on MATLAB/SIMULINK
XIA Fei, HUANG Jin-quan, ZHOU Wen-xiang
2007, 22(12): 2134-2138.
Abstract PDF(1071KB) icon2177 icon449
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A generic component-level simulation model of a turbofan engine was developed using graphical modularization technology in MATLAB/SIMULINKgraphical simulation environment.With modular block library of SIMULINKand S-function of MATLAB,the goal of this model is to develop a four-layered,modular and highly visible engine structure facing structural diagram.Dynamic simulation was made in SIMULINK,and the model was validated from test data curve.This provides a flexible simulation platform for future research on engine control and fault diagnostics.
Control system design for engine of a small-size unmanned helicopter
WANG Xiao-qing, HUANG Yi-ming, YANG Yi-dong, ZENG Guo-gui
2007, 22(12): 2139-2142.
Abstract PDF(895KB) icon1819 icon498
Abstract:
Engine control is the base of helicopter flight control system.Acontrol system was proposed for pistol engine of a small-size unmanned helicopter;and the engine was modeled by analysis of engine power,engine load,and engine dynamics.The engine control system included feed forward control block and feedback control block;and real-time simulation and ground test verified good performance of this control system.

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