2005 Vol. 20, No. 2

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Some Fundamental Experiences of Design and Development of the "Kunlun" Aero-Engine
YAN Cheng-zhong
2005, 20(2): 169-176.
Abstract PDF(726KB) icon1983 icon494
Abstract:
Briefly introduces some fundamental experiences of design and development of the "Kunlun" two-spool afterburning turbojet engine,which was successfully self-designed and developed in China.The design,development and test were strictly followed out the "General Specification of Turbojet and Turbofan Aero-Engines".The adequate proportion between creativeness and inheritance was controlled to reduce risk without sacrificing the engine’s advanced status.The design regarded the operability,reliability,durability and maintainability as important as performance.Large exhaust temperature margin and surge margin were ensured.Strict and sufficient ground and flight tests were the base of the engine reliability.
Initial Study of a Theoretical Near-Wall Turbulence Model
ZHAO Lü-shun, WANG Dan-hua, YE Jian, LU Li-peng
2005, 20(2): 177-181.
Abstract PDF(320KB) icon1676 icon450
Abstract:
Based on the classic k-ε turbulence model,ε equation is replaced by a theoretical model which formed a near-wall turbulence model.The calculation of the 2-D NACA0012 airfoil in low Reynolds number flow field validated the theoretical model.The non-dimensional property of the result obtained from the theoretical model improves the calculation,so the distribution of C_pagrees better with experimentation.The analysis shows that the effect of converse pressure gradient on ε is prominent,and it validates the result of theoretical and numerical computation.
Discussion of the "Wake Strike" Effects on Flow Field in Axial-Flow Compressor
LIU Yan, LU Ya-jun
2005, 20(2): 182-185.
Abstract PDF(267KB) icon1708 icon441
Abstract:
Influence of the wake impact effect on the flow field and its average performance in a low speed axial-flow compressor was investigated by using external acoustic excitations.Main focus is on the flow field calibration, the steady and dynamic performance measurement and the analysis of the experimental data.The results indicate that the time-space structure and the average aerodynamic performance can be improved greatly when the couple of wake impact effect is occurred.
Numerical Simulations for the Flowfield of Helicopter Rotors in Hovering Based on High-Order Upwind Flux-Difference Splitting Scheme
ZHAO Qi-jun, XU Guo-hua
2005, 20(2): 186-191.
Abstract PDF(379KB) icon1876 icon484
Abstract:
In order to reduce effectively the numerical dissipation of the rotor wake vorticity induced by Jameson’s second-order cell-centered finite volume approach,with the combination of the third-order upwind scheme (MUSCL) and flux-difference splitting scheme,a numerical method based upon the solution of three-dimensional Reynolds-average N-S equations has been developed to simulate the flowfield around a lifting rotor in hovering.To incorporate the important effects of the rotor wake,the far-field boundary condition derived from the rotor momentum theory and the cyclic boundary condition have been used.The embedded grids methodology was adopted so as to weaken the numerical dissipation of the wake and be easy to apply the above mentioned boundary conditions.Several cases of the blade surface pressure distribution have been calculated using the present method and the second-order center difference.The calculated results were validated by comparing with available experimental data.Then flowfield simulations under rotor hovering conditions were performed for three different blade tip planforms.The numerical results demonstrate that the swept tips can suppress supercritical flow.Additionally, the vorticity contours were computed and the characteristics of distorted rotor wake were analyzed.It is shown that the present method can effectively reduce the numerical dissipation of the rotor wake.
Numerical Simulation Studies on the Discharge Coefficient of Gas Turbine Combustor Liner Air Holes
CUI Yu-feng, XU Gang, TIAN Xue-qing, HUANG Wei-guang
2005, 20(2): 192-196.
Abstract PDF(294KB) icon1855 icon456
Abstract:
The discharge coefficient of the plain circular holes and the film cooling holes were investigated with numerical simulation method.The relation of the discharge coefficient to the geometrical and the flow parameters were studied.Results of the proposed formula for plain circular hole were compared with the experimental and theoretical data, and they agreed well.Sometime slot is used instead of circular holes to simplify the geometry of the combustor.The determination of gap’s equivalent area was also investigated.All calculated results indicate that numerical simulation is a feasible,simple and effective method to determine the discharge coefficient of the gas turbine combustor air holes.
Rig Test of Impingement/Effusion Double Wall Cooling Methods for the Main Combustor
XU Quan-hong, LIN Yu-zhen, LIU Gao-en
2005, 20(2): 197-201.
Abstract PDF(309KB) icon2011 icon478
Abstract:
For the investigation, a combustor sector with one burner head was used.Three different test pieces with impingement/effusion double wall cooling were selected for testing under high-temperature and high-pressure working conditions,which were equivalent to that of engines with a thrust/weight ratio of 10.The liner temperatures were measured using thermocouples.The test result shows that the amount of cooling airflow of double-layer wall combustor is 20% of the overall airflow,and the overall cooling effectiveness is in the range of 0.85 to 0.96.The wall temperatures of all test pieces are lower than 1 150 K.
Spray Characteristics of Side unlike Impinging Platelet Injector
GUO Zhi-hui, CAO Yong, HUANG Yong
2005, 20(2): 202-207.
Abstract PDF(402KB) icon1871 icon453
Abstract:
An experimental study of the spray characteristics of side unlike impinging platelet injector was conducted using a Particle Dynamics Analyzer (PDA).The droplet velocities,diameter and flux density of the spray were measured at three axial locations.The atomization process and special spray feature have been analyzed.The results show that the atomization process is different from that of common impinging injector.The mixing ratio γ_mand geometric parameters have important effect on the atomization and spray distribution.For a certain γ_mand passage area ratio γ_a,there is an optimum nozzle geometry to attain good atomization and spray pattern.On the other hand,both higher γ_aand γ_mcan improve atomization performance within an appropriate nozzle width.The atomization performance and spray pattern can be controlled by selecting appropriate and geometric parameters.
Numerical Simulation of Nacelle Flow and Temperature Field
WANG Fang, YU Jian-zu, XIE Yong-qi
2005, 20(2): 208-213.
Abstract PDF(464KB) icon2011 icon479
Abstract:
The finite element model of the nacelle flow was established using the non-structure grids.The flow and heat transfer control equations were solved by the SIMPLE algorithm taking the real cooling flow situation in the nacelle into consideration.The flow and temperature fields were simulated and the relationships between the flow,pressure and temperature field were analyzed. Further more,according to the problems in the existing design,plans were proposed to improve the nacelle cooling situation.The effectiveness of different plans were compared and analyzed.
An Experimental Investigation on Dynamic Wetting and Dynamic Contact Angle
WANG Xiao-dong, PENG Xiao-feng, WANG Bu-xuan
2005, 20(2): 214-218.
Abstract PDF(309KB) icon1665 icon452
Abstract:
An experimental system,composed of a liquid tank,a solid thin plate,a step-motor,a CCD camera connected with stereoscopic microscope,a high-speed image acquisition card,and a computer,was utilized to investigate dynamic wetting behavior of silicone oil on glass,aluminum and stainless steel surfaces and understand the effect of the solid surface properties on the dynamic wetting behavior.It concludes that when the value of the dimensionless parameter,λ,was selected as 0.07,0.16 and 0.35 for glass,aluminum and stainless steel,respectively,the experimental results are in good accordance with the prediction of the precursor film model presented by Wang and Peng et al.Clearly, the dynamic contact angle is dependent not only on the capillary number and static contact angle but also on λ describing the solid surface properties.Furthermore,it is shown that the Hoffman-Voinov-Tanner law valid at low capillary number (Ca1 or θ_D<10°) recommended by Cazabat still keeps true for a wide range of contact angles,up to 70°,which is reasonably explained by the precursor film model.
Method for Predicting the Performanceof Oil Cooling Systems and Its Application
YANG Chun-xin, ZHANG Li-na, GUO Hui
2005, 20(2): 219-224.
Abstract PDF(386KB) icon1999 icon426
Abstract:
Addresses the problem of additional oil temperature increase with a fan installed in the oil cooling system and presents a feasible model which complements the method for predicting the performance of the oil cooling system.On the basis of the system model developed,structure parameters were optimized with genetic algorithm to improve the accuracy.With this method,the impact of temperature control valve on oil temperature was analyzed and the system transient temperature prediction method was established.This method could be used to predict the harmful temperature exceedence during engine operation.Only a small quantity of experimental data is necessary for the model fitting.The simulation results agree well with the test data.This approach can reduce the experimental cost, save experimental time and can be used to predict the oil cooling ability under severe operating conditions that experimental work is difficult to conduct.
Investigation on Characteristics of Detonation Wave Propagation in Tubes with Different Diameter
HAN Qi-xiang, WANG Jia-hua
2005, 20(2): 225-229.
Abstract PDF(279KB) icon1773 icon424
Abstract:
The characteristics of premixed gas detonation wave propagating in two tubes with diameter,20 mm and 60 mm respectively,were investigated.Primarily,the detonation wave pressures and velocities were measured,and the mixture pressure, concentration,equivalence ratio,and the dimension of connection tube were considered in the study.It was found that the detonation could appear in the bigger tube even when the detonation was not triggered in the smaller tube.The connection tube with smaller diffusion angle is favorable for detonation re-triggering.The pressure and velocity of re-triggered detonation are affected by mixture pressure,concentration, and equivalence ratio.
Research on Discrepancy of Fiber Reinforced Composite Effective Performance
SONG Ying-dong, SUN Zhi-gang, GAO Xi-guang
2005, 20(2): 230-235.
Abstract PDF(605KB) icon2114 icon444
Abstract:
Discrepancies of elastic modulus,Poisson ratios and thermal expansion coefficients of fiber reinforced composites were investigated using the constitutive model of Cell and Monte-Carlo method.The results indicate that the discrepancies of fiber reinforced composite effective performance are smaller than the ones of their elements. With the increase of the percentage of fiber volume,the discrepancies of longitudinal effective performance increase, but that of transverse effective performances decrease,except the thermal expansion coefficient in the short-axial direction.The fiber shapes and packing arrays have little effect on the discrepancies of longitudinal effective performance.Composites with hexagonal section fibers and square cross section fibers have the same discrepancies of transverse effective performance.Different fiber packing arrays give different discrepancies.The presented conclusions in this paper are very useful to probabilistic design of composites.
Geabox Fault Diagnosis Based On Wigner Distribution and Empirical Mode Decomposition
SHEN Guo-ji, TAO Li-min, XU Yong-cheng, CHEN Zhong-sheng
2005, 20(2): 236-239.
Abstract PDF(409KB) icon2010 icon432
Abstract:
To reduce life cycle cost and to improve flight safety,the detection and diagnosis of gearbox faults is of vital importance.Impulsive vibration signals in gearbox are often associated with impulse resulted from faults, and thus,impulsive signals can be used as the symptoms of faults.In order to characterize fault signals,many approaches were used to seek salient characteristic signals in time-frequency domain.Wigner distribution is a common time-frequency representation.However,the fault characteristic signals are always baffled by signals from other vibration sources and the inherent cross-terms in bilinear operation of the Wigner distribution.To minimize the effect of these disturbances,Wigner distribution was combined with empirical mode decomposition.Rather than calculating Wigner distribution directly,we present a method using empirical mode decomposition as a preprocessor.The vibration signal is decomposed into a sum of intrinsic mode functions.Only the Wigner distributions of the intrinsic mode functions which relate to the gear meshing vibration are calculated.This approach was applied to the diagnosis of a gearbox test data,the results show that effectiveness of diagnosing is significantly improved.
Theoretical Analysis and Experiment of the High Speed Ceramic Rolling Bearing Equivalent Stiffness
TANG Yun-bing, LUO Gui-huo, ZHANG Jing-xuan, GAO De-ping
2005, 20(2): 240-244.
Abstract PDF(542KB) icon2148 icon490
Abstract:
Ceramic bearings are widely used in the high speed machine,especially in the micro or small turbine engines.The bearing stiffness has a considerable influence on the dynamic characteristics of a rotor-bearing system.There were some databases of slide bearing dynamic characteristics.Rolling bearing stiffness is usually estimated empirically and it is simplified as a constant stiffness element.This method often causes large error.The primary factors that influence the rolling bearing equivalent stiffness were analyzed and a method for the calculation of rolling bearing equivalent stiffness was proposed.A test rig was designed for measuring the equivalent stiffness of ceramic bearings.The theoretical and experimental results agree well.
Method for Determining Crack Growth Parameters Using Fatigue Life
BAO Rui, ZHANG Jian-yu, WANG Chuan-sheng, FEI Bin-jun
2005, 20(2): 245-249.
Abstract PDF(473KB) icon1698 icon456
Abstract:
Since the (a,N) databank can not be easily obtained in corrosion fatigue,the method for determine the parameters of crack growth parameters in terms of fatigue life is presented.Via results comparison,the method shows its good capability under the general condition of b=1.The small relative error of the estimation of crack length and number of load cycles for given damage probability proves that the method given in this paper can be used in probability damage tolerance analysis.
Grey Correlation of Vibrationwith Rolling Bearing’s Machining Quality
XIA Xin-tao, WANG Zhong-yu, CHANG Hong
2005, 20(2): 250-254.
Abstract PDF(318KB) icon1692 icon445
Abstract:
It was proved that vibration was affected by machining quality of the rolling bearing elements.Unfortunately, current research did not show the degree of influence caused by each kind of quality index.Because that different machining quality index has different contributions to the rolling bearing’s vibration,so enhance machining quality without clear understanding what index is key to the problem could have no advantage in controlling vibration.Degree of influence caused by machining quality on the rolling bearing’s vibration was compared and evaluated by experiments.Two kinds of aeronautical bearing were selected for testing in this investigation.Considering the un-suitability of statistics theory,grey system theory was introduced.The results show that parameters of structural dimension error exert greater effect on the rolling bearing’s vibration than that of macroscopic parameters of form error and microscopic parameters of shape.Consequently,macroscopic parameters of form errors and microscopic parameters of shape are minor factors for high quality machining bearings selected,while parameters of structural dimension errors and its tolerance are thought to be the main factors.
Study of Vibration Damping with Dry Friction Snubberon Blade Platform
LI Quan-tong, LIAO Ming-fu
2005, 20(2): 255-261.
Abstract PDF(488KB) icon1730 icon440
Abstract:
A simplified method using transfer matrix method was applied to the analysis and calculation of the vibration damping effect induced by dry friction snubber on the blade platform.To validate the calculated results of the transfer matrix method,the finite element method ANSYS was used to calculate blade vibration with dry friction damper on the platform.The calculated results of the two methods are basically consistent,which demonstrates that the transfer matrix method suitable for chain-construction-system can also be applied to the plate-construction-system.
Numerical Simulation and Test Verification of 3-Dimensional Transonic Navier-Stokes Equations Appliedto Turbomachinery Rotor Internal Flow
WEI Ling, GE Ning
2005, 20(2): 262-266.
Abstract PDF(486KB) icon1982 icon457
Abstract:
A method of three-dimensional numerical simulation for the transonic turbomachinery rotor internal flow field by solving three-dimensional unsteady compressible thin-layer Navier-Stokes equations in rotating frame using finite volume method and Baldwin-Lomax algebraic turbulent model is presented.The local time step was used to accelerate the iteration process.Implicit treatment of convective fluxes was combined with the explicit treatment of diffusive fluxes.Roe’s method with three-order TVD scheme was used for the evaluation of convective fluxes,and central difference scheme was used for diffusive fluxes.Newton’s sub-iterations were applied to reduce the non-linear equations of conservative variable into linear one.The linear equations were solved using symmetric Gauss-Seidle iterative method.The case used for examining was NASA Rotor 67.Calculated performance,relative Mach number contours at different span location,spanwise total pressure and temperature distribution at rotor exit,etc.,were compared with the experimental data.Computation results agree well with experimental data at peak efficient point,but there is a little discrepancy at near stall point.
Frequency Analysis of Three Dimensional Compressor Cascade Unsteady Flow Mechanism Research
WU Hong-bin, ZHENG Xin-qian, ZHOU Sheng
2005, 20(2): 267-272.
Abstract PDF(397KB) icon1797 icon436
Abstract:
A simulation using unsteady Reynolds-averaged viscous turbulent equations was carried out.The results show that the flow in the separation region and wake region is characterized as periodic or quasi-periodic vortex shedding and the frequency of vortex shedding is varied with incidence and Mach number.At same Mach number,the frequency of vortex shedding decreases with the increase of incidence.Yet,the frequency increases with the increase of Mach number keeping incidence unchanged.In the same situation,the frequency of vortex shedding differs along the span of the cascades.The frequency is lower at the middle of the span than that at the hub.
Improvement on Dynamic Characteristics of High Response Pressure Probe
GUO Yong, WANG Xiao-kui, WANG Hong-wei
2005, 20(2): 273-277.
Abstract PDF(350KB) icon1693 icon439
Abstract:
It is necessary to broaden the working frequency band of the existing high response pressure probe to make it can be used to measure the compressor dynamic flow field.On the basis of dynamic calibration,the application of the dynamic compensation digital filter technique will improve the dynamic characteristics,and thus its response time is shortened and the frequency band is broadened.
Time-Frequency Analysis of the Axial Flow Compressor Endwall Flow at Near Stall Conditions
ZHANG Pu, LI Ying-hong, WEI Xun-kai, WU Yun, ZHANG Bai-ling
2005, 20(2): 278-281.
Abstract PDF(391KB) icon2067 icon458
Abstract:
To identify the flow pattern of a single-spool turbojet axial flow compressor at near stall conditions,the compressor end wall static pressure signals were analyzed using time-frequency analysis technology.The results show that at near stall conditions,the endwall flow of the first compressor stator varies dramatically compared to other stators.As the operating point runs close to the surge line along the operating line,a broad band signal centered on 550 Hz occurs and gradually builds up.The observed end wall flow patterns can be used to assess the stall margins during engine throttling,and thus,it has certain value in engineering application.
Method of Fault Diagnosis and Fault-Tolerant Control for Actuator Loop in Aeroengine Digital Control System
JIANG Ping-guo, YAO Hua, SUN Jian-guo
2005, 20(2): 282-286.
Abstract PDF(227KB) icon2110 icon517
Abstract:
A model-based aeroengine digital control system actuator loop fault diagnosis method and fault-tolerant control method for actuator position sensor fault control algorithm were put forward.These methods were implemented to a full authority digital engine control system and validated.The results show that these methods can greatly improve the successful rate and reduce the time necessary for actuator loop fault diagnosis.These methods are easy to implement and have good real time diagnosis capability.Thus,they have a significant effect on improving the reliability of aeroengine digital control system.
Aeroengine Separate Decoupling Control Based on Recursive Neural Networks
LIU Jian-xun, LI Ying-hong, CHEN Yong-gang, WEI Xun-kai
2005, 20(2): 287-292.
Abstract PDF(367KB) icon1852 icon460
Abstract:
To solve the problem of coupling in aeroengine multivariable control system,a dynamic decoupling control method based on recursive wavelet neural networks is presented.The structure of engine decoupling control system, as well as its decoupling principle and algorithm,is given.The structure includes two separate control loops.The two recursive wavelet networks,which employed normalized wavelet basic functions,were used as the decoupling identifier,and two PID neural networks were used as the controller.The wavelet networks identify the dynamic model of the engine and feed back the sensitivity information through on-line learning.The neural network PID controller updates the weights adaptively according to the on-line sensed information,and accomplishes self-governed control of each engine control loop.The simulation results of a turbofan engine show that the proposed method can effectively reduce the coupling influence of each control loop and assure satisfactory transient performance.It can be successfully applied to decoupling of aeroengine control system.
Study of Aeroengine Adaptive Inverse Control
HU Wen-fei, HUANG Jin-quan
2005, 20(2): 293-297.
Abstract PDF(474KB) icon1988 icon471
Abstract:
The adaptive inverse control system for aeroengines was designed.The aeroengine was modeled using linear adaptive filters. The adaptive inverse control structure with integral control was proposed to reduce the steady-state error.Simulation of the aeroengine speed control system in the whole flight envelope was performed,and excellent tracking performance and robustness were obtained.
Aero-Engine Fault Diagnosis Based on Support Vector Machine
XU Qi-hua, SHI Jun
2005, 20(2): 298-302.
Abstract PDF(288KB) icon1927 icon575
Abstract:
The capabilities of Support Vector Machine (SVM) applied to aero-engine fault diagnosis (i.e.classification of multiple faults) were investigated.The gas path components of a jet engine were selected to gather datasets for the evaluation of the classification capabilities.With the proposed approach,24 sets of component single fault testing data from the datasets were classified into 5 single faults and 16 sets of multiple faults testing data were classified into 8 faults.The single faults are low pressure compressor (LP) fault, high pressure compressor (HP) fault,low pressure turbine (LT) fault,high pressure turbine (HT) fault and no fault;while the multiple faults are LP+HP,HP+HT,HT+LT,LP+LT and LP+HP+LT+HT faults.There is no misclassification for all of the testing data using SVM.When the datasets are masked with noise as great as 12% in single faults and 10% in multiple faults,the effectiveness and robustness of the fault diagnosis algorithms are still satisfactory.
Fusion Diagnosis of Engine Wearing Fault Based on Neural Networks and D-S Evidence Theory
CHEN Guo
2005, 20(2): 303-308.
Abstract PDF(551KB) icon1638 icon462
Abstract:
Four common oil analysis techniques, namely Ferrography analysis,Spectrometric analysis,Particle count analysis,and Oil chemical-physics analysis,were used together with the engine test data to develop the fusion diagnosis method of engine wearing fault based on Neural Networks (NN) and D-S evidence theory.Firstly,according to standard wear limit,original data were transformed into BOOL value.Then,each sub-NN structure was established,and their training samples were obtained based on expert experience.After each sub-NN was trained successfully,the intermediate diagnosis results were obtained through each sub-NN.Finally,the NN diagnosis results are used as the basic probability distribution value to each fault mode,and the D-S evidence theory is applied,and the final fusion diagnosis results are obtained.An example was used to verify the method presented in this paper.
Turbo-Fan Engine Dynamic Output Feedback Control with Mixed Weighted Sensitivity Based on LMI
TAN Dao-liang, WANG Xi, ZHEN Tie-jun
2005, 20(2): 309-313.
Abstract PDF(329KB) icon1765 icon449
Abstract:
Choosing appropriate weighted functions in the frequency domain,and in combination with the state-space model of the real plant,the formulation of the state-space model for some generalized plant by employing the method of loop shaping and internal principle was established.The original control problem was converted to a standard H_∞ problem.The controller for the original plant was derived by means of solving optimal H_∞ dynamic output feedback controller for the generalized plant based on Linear Matrix Inequality (LMI).This design procedure was applied to a turbo-fan engine.The controller obtained by this method was verified in a wide engine operating range in the flight envelope.Simulation results of the turbofan engine nonlinear model show that the characteristics of the controller,namely,tracking characteristics,disturbance rejection and robustness,are satisfactory.
Aeroengine Performance Monitoring and Fault Diagnosis Based on Chaos Variable
HOU Sheng-li, HU Jing-hai, LI Ying-hong
2005, 20(2): 314-317.
Abstract PDF(414KB) icon1706 icon423
Abstract:
While the synthetic weighted method is used to calculate the synthetic exponent characterizing the overall engine performance,the weights of every parameter are difficult to determine.To solve this problem,a method of chaos variable was introduced.The synthetic exponent optimized by chaos variable is more sensitive and accurate than the one gained by the expert investigation method in reflecting the overall engine performance change. This method improves the successful rate of identifying whether the engine performance is normal or not,and can be used to detect the potential incipient fault,thus prevents the spread of the fault.The validity of this method is verified by monitoring a turbofan engine.
Influence of Environmental Pressureon Arcjet Thruster Performance
XIAO Ying-chao, LIU Yu, ZHANG Zhen-peng
2005, 20(2): 318-322.
Abstract PDF(319KB) icon2064 icon458
Abstract:
To investigate the influence of environmental pressure on arcjet thruster performance,computation of operating performance of a low power nitrogen/hydrogen arcjet thruster under various environmental pressures was performed.Non-oscillating and non-free-parameter dissipative finite difference scheme with second order accuracy and classical Runge-Kutta time-stepping scheme was used to solve Navier-Stokes equations coupled with electromagnetic source terms,and Gauss-Seidel over-relaxation iteration method was adopted to solve electromagnetic equation.The results present thrust,specific impulse and thrust efficiency of the thruster under various environmental pressures,as well as impulse density distribution on the exit plane.Analyses of the results demonstrate influence of the environmental pressure on arcjet thruster performance quantitatively,and provide reference for its experimental investigation and its space application.
Experimental Investigation of Gas-Dynamic Resonance Heating
YU Nan-jia, ZHANG Guo-zhou, SONG Ya-na
2005, 20(2): 323-327.
Abstract PDF(307KB) icon1639 icon449
Abstract:
In order to learn more gas-dynamic resonance heating rules and to provide experimental foundation for investigating gas-dynamic resonance igniter,gas-dynamic resonance heating experiments based upon initial tests were carried out.Factors investigated,which affect resonance heating characteristics,include variation of flow rate,different structures of exhaust hole and different diameters of connect cavity.Through lots of experiments with different design parameters,some gas-dynamic resonance heating rules were found,and optimum structure design parameters were obtained for gas-dynamic resonance igniter design.
Research and Analysis of the Full-Flow Staged Combustion Cycle Rocket
HU Wei, ZHANG Qing-song
2005, 20(2): 328-333.
Abstract PDF(359KB) icon2495 icon508
Abstract:
The working process of the H2/O2 engine full-flow staged combustion cycle is discussed,and the system sketch of the rocket engine based on this cycle is presented.Based on the development status of the H2/O2 rocket engine, the system parameter balance calculations were executed.The calculated results show that the full-flow staged combustion cycle yields a lower temperature of the pilot burner and the turbine working gas compared to the fuel-rich staged combustion cycle engine with the same power output.The advantages of the full-flow staged cycle are discussed.It is believed that reliability and performance of the engine with this kind of cycle are superior and the full-flow cycle engine can satisfy the high reliability,low cost and reusable requirement.
An Experimental Equipment for Small ScaleRocket Engine with Full Flow Staged Combustion Cycle
ZHANG Qing-song, HU Ze-bao, HU Wei
2005, 20(2): 334-338.
Abstract PDF(323KB) icon1881 icon449
Abstract:
A new kind of power cycle of the propellant feed system for liquid propellant rocket engine is presented.The full flow staged combustion cycle and its superior performance compared to the traditional cycle are discussed.For further study of this advanced cycle system,experimental equipment for small scale rocket engine with full flow staged combustion cycle was designed and established.One-dimensional propellant feeding pipe system calculation has been carried out to confirm the pressure and volume needed for the propellant store tank.Through the thermodynamic calculation of two pilot burners,the burning temperature and the thermodynamic properties of the burning gas were obtained for further design of the pilot burner.A large number of specific impulse for the hydrogen-oxygen propellant was investigated with the chamber pressure and mixture ratio varying in a wide range.According to the performance analysis done,the chamber pressure and mixture ratio were determined to be 4.0 MPa and 0.75 respectively with certain consideration of the practical experimental conditions.Finally,the thrust generated was predicted to be 4 018.77 N.
Modular Simulationfor Tank Pressurization System of LRE Test-Bed
CHEN Yang, GAO Fang, ZHANG Zhen-peng, CHEN Feng
2005, 20(2): 339-344.
Abstract PDF(376KB) icon1891 icon439
Abstract:
Using the finite element state-variable model for one-dimensional ideal gas flow,a modularized simulation model was established,and then the working process was calculated for the tank pressurization system of LRE test-bed.Detailed distribution curves of state parameters for the pipe net were obtained,which could be used to analyze the working process of the system and the function of every component.The mathematical model and the method of modularized modeling and simulation were validated to be effective and versatile.

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