2007 Vol. 22, No. 3

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Experimental research of instability of kevin-helmholtz wave on conical sheets
LI Ji-bao, YUE Ming, YANG Mao-lin
2007, 22(3): 337-341.
Abstract PDF(1353KB) icon1577 icon482
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The fragmenting images of meridian plane of conical liquid sheet under different nozzle pressure were obtained with Particle Image Velocimetry(PIV) system.Also,the characteristic parameters of conical liquid sheet with centrifugal nozzle,such as half-cone angle and breakup length,were measured under different liquid pressures.The variations of nozzle liquid pressure on half-cone angle and breakup length have been analyzed.The empirical formula of parameter C was obtained from experimental results,whereby the dispersion relation was solved to obtain the wavelength at breakup point of sheet under different pressures.The predicted results were compared with experimental results,finding that the trend of predicted data fully corresponds to the experimental results.
Research on ignition performance of a hybrid airblast atomizer combustor with convergent-divergent sleeve
LIN Yu-zhen, LIN Pei-hua, XU Quan-hong, LIU Gao-en
2007, 22(3): 342-346.
Abstract PDF(738KB) icon1807 icon524
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For a hybrid airblast atomizer combustor with convergent-divergent sleeve,a simplex pressure swirl nozzle is used for the primary fuel circuit,and a direct-injection airblast atomizer is used for the main fuel circuit.Only the pilot simplex nozzle was operated in the ignition tests.The test combustor is a single-nozzle rectangular combustor,with normal inlet temperature and normal inlet pressure.Under the test condition of pressure drop of 0.9%-9.0%,the ignition performance of hybrid airblast atomizer combustor was analyzed.And,the atomization performance of this hybrid atomizer was also summarized to obtain the empirical correlation under the same condition.While major influential factors to ignition were analyzed,the empirical correlation of such combustors was summarized based on the atomization data and Lefebvre's ignition model.
Experimental investigation of the flow field between a rotating and a stationary disk at high-positioned air inflow
TAO Zhi, GAO Juan, CAI Yi, DING Shui-ting, LUO Xiang, ZOU Zheng-ping
2007, 22(3): 347-351.
Abstract PDF(327KB) icon2093 icon449
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The flow field between a rotating and a stationary disk at high-positioned air inflow condition was investigated by Particle Image Velocimetry(PIV) technology.The experiments indicate that PIV technology could be used on the flow measurement of the rotating cavity.The flow in the most area became turbulence in the range of experiments.Batchelor-type flow was observed in the experiments.Separate boundary layers were formed on the rotor and stator.Between the boundary layers there was an inviscid core rotating in the same direction as the rotor at a lower speed.The experimental data of the relative rotational speed β in the core was lower than 0.43,the value in the closure system with large clearance.β did not show obvious changes with the change of flow rate coefficient or rotational Reynolds number,but the axial clearance between the rotor and stator affected β much obviously.
Experimental investigation of the local heat transfer of impinging cooling with outflow film in closed small space
MAO Jun-kui, GUO Wen, CHANG Hai-ping, XU Lei, ZHANG Jing-yang, CHANG Guo-qiang
2007, 22(3): 352-359.
Abstract PDF(620KB) icon1999 icon408
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Experiments were carried out to investigate the heat transfer of compound cooling（impinging cooling with outflow film）.Local heat transfer coefficients on inner surface were obtained over a Reynolds number range of 10 000～40 000,nozzle-to-plate spacing H/D range of 0.17～2.0,the ratio between impinging jet and film hole distance to jet hole diameter P/D range of 0 and 1.Experimental results show that the local heat transfer coefficient was affected by impingement Reynolds number and nozzle-to-plate spacing greatly.Under the parameters in this paper,the local Nu number increased with the impingement Reynolds number.When P/D=0,the maximum Nu number was achieved while H/D=2.When P/D increased to unity,the maximum Nu number was gotten while H/D=2 and 0.17 under lower impingement Reynolds number.And this proper value of H/D will change to be 2 and 1 under higher impingement Reynolds number.
Research on protected range of the anti-icing/deicing system for helicopter rotor
CHANG Shi-nan, LIU Da-jing, YUAN Xiu-gan
2007, 22(3): 360-364.
Abstract PDF(631KB) icon1657 icon468
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Under icing conditions,helicopter rotor is prone to icing.The rotor icing menaces the safety of the helicopter seriously,so the blade must be protected from icing.Through the analysis of external heat fluxes,the critical velocity was calculated for a given blade at ultimate state of icing when surface temperature was 0℃.The protected range along spanwise was then determined to be 0～95% form blade root to tip.By calculating the droplet impinging characteristic, the protected range along chordwise form the leading edge was then determined to be 12% along the upper surface and 33% along the lower surface.On the basis of the results,the configuration and structure of the heating system for a rotor blade can be designed.
Numerical simulation for impingement-counterflow convection-film cooling of a combustor wall
LI Bin, JI Hong-hu, JIANG Yi-jun, LI Feng
2007, 22(3): 365-369.
Abstract PDF(837KB) icon1804 icon516
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Fluid/solid conjugated heat transfer numerical simulation was conducted to study impingement-counterflow convection-film cooling by using the commercial codes FLUENT.The flow fields of convection passage and film forming region,and temperature distributions of fluid and solid wall were obtained and analyzed.The numerical study aims at obtaining a calculation method of flame tube wall temperature.The numerical results showed that the agreement with the experimental data was fairly good.Analyses indicated the fluid/solid conjugated heat transfer numerical simulation is a feasible way to obtain the wall temperature of impingement-counterflow convection-film cooling.
Numerical analysis of 3D temperature field of an impingement-effusion cooled flame tube floating tile
LI Bin, JI Hong-hu, JIANG Yi-jun
2007, 22(3): 370-374.
Abstract PDF(646KB) icon1843 icon452
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Heat transfer numerical analysis methods,maths model,and boundary condition treatment for an impingement-effusion cooled flame tube floating tile are discussed in the paper.By using the heat analysis module of ANSYS code,the 3D temperature field of the floating tile was calculated.The numerical results showed that the agreement with the test data is fairly good.The relative error between numerical results and test data is not greater than 6%.
A study of optimization of convection and heat transfer of impingement/effusion double wall
TANG Qing-ru
2007, 22(3): 375-379.
Abstract PDF(305KB) icon1582 icon404
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The convection and heat transfer within the effusion holes of impingement/effusion double wall were optimized to get the maximum internal cooling effect.The ratio of the number of impingement holes to the number of effusion holes per unit area is 1∶3,and the angel of effusion hole is 30 degree.As a hybrid restriction optimization approach,the sequential unconstrained minimization technique was applied for optimization.The optimal results of impingement/effusion double wall were obtained under the pressure drop and unit-area cooling air flow.The results indicate an optimal distribution between the impingement heat transfer and the convective heat transfer within the effusion holes,providing a basis for design of the impingement/effusion double wall for engineering applications.
Experimental study of cooling efficiency of film cooling with tab
YANG Wei-hua, LI Yong-kang, ZHANG Jing-zhou, MA Guo-feng
2007, 22(3): 380-383.
Abstract PDF(915KB) icon1776 icon479
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In order to study the effect of tab on film cooling,three equilateral triangular test tabs with different blockage ratio were designed,and their effects on heat transfer characteristics of film cooling were experimentally studied.The test results show that the efficiency of film cooling with tab is better than that without tab.The efficiency of film cooling will be increased with the increase in blow ratio,and it has a highest value in the direction of flow.When the blow ratio,the cooling efficiency will be increased with the increase in blow ratio;but when the blow ratio,the cooling efficiency will be decreased with the increase in blow ratio.
Influence of high aspect ratio convergent nozzle with different transition cross-section and nozzle shape on jets mixing characteristics
ZHANG Bo, JI Hong-hu
2007, 22(3): 384-389.
Abstract PDF(1112KB) icon1731 icon408
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The mixing characteristics of jets from four rectangular nozzles with aspect ratio of 8 were investigated by numerical simulation.The first and second nozzles had different transition sections from circular to rectangular,the third nozzle had a rectangular flip which was an extension of the bottom wall of nozzle exit on the base of the first one,while the last one had two triangular flips on the left and right sides of the nozzle exit on the base of the third one.The results show that the mixing characteristics of the two nozzles with different transition sections have little difference,while the flips cause strong mixing.
Experimental and computational study of a submermerged inlet on the plane surface under ground running
SUN Shu, GUO Rong-wei, WU Yi-zhao
2007, 22(3): 390-395.
Abstract PDF(1054KB) icon1689 icon454
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Utilizing the combined experimental and computational method,the aerodynamic performance and internal flow pattern of a submerged inlet on the plane surface under ground running are obtained in this paper.Results indicate that:(1) The secondary flow at the cross sections behaves as two counter-rotating vortices which are originated by the side edge of the entrance.The ongoing vortex pair interacts with the separated flow near the aft lip of the inlet and results in the low total pressure region at the bottom surface of the exit.(2)With the ascent of Mach number at the exit,both the total pressure loss and distortion index increases.In spite of a remarkable shift of the distortion index under ground running,compared with high speed wind tunnel tests,the synthesis distortion index is kept below 10.0% at the maximum RPM which does not threaten the stable operation of the engine.(3) The CFD results agree well with the experiment and the relative errors of the total pressure coefficient is less than 1.2% though the distortion index by CFD is a bit higher.
Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet
SUN Bo, ZHANG Kun-yuan, JIN Zhi-guang
2007, 22(3): 396-399.
Abstract PDF(665KB) icon1810 icon477
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A wind-tunnel testing of a streamline traced hypersonic Busemann inlet,with a designed Mach 5.3 and shrinkage ratio CR=5,was conducted at Mach 3.85 to study its starting and overall performance as well as back-pressure capability below Mach 5.3 conditions.The results show that,the inlet can be started automatically at Mach 3.85;the flow coefficient of inlet is 0.83,the overall pressure recovery coefficient is 0.78,with a Mach number 2.01 and a compression ratio of 11.92;the inlet can withstand a maximum back-pressure of 34 times static pressure.
Unsteady numerical simulation and analysis of the flow fluctuation in the Roots blower
LIU Zheng-xian, XU Lian-huan, ZHAO Xue-lu
2007, 22(3): 400-405.
Abstract PDF(1941KB) icon1751 icon423
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The pulsation in the exhaust process of three-lobe involute type Roots blower was simulated in CFD method under the compressible、unsteady condition. To achieve the change of exhaust area that dynamic mesh updating method and multiple reference frame at rotor-stator coupled area were adopted.The result of numerical simulation was contrasted with computing result of the semi-experience theory formula.It was discussed that the characteristic of air flow fluctuation in a period and influence to the exhaust flux.
Effects of blade curved on compressor cascades with different camber angles under different incidences
CHEN Shao-wen, CHEN Fu, FENG Dong-ming, WANG Zhong-qi
2007, 22(3): 406-411.
Abstract PDF(1276KB) icon1658 icon444
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The experimental investigation of the effects of changing incidences on the aerodynamic performance of compressor cascades with different curved angles and camber angles in a low-speed annular wind tunnel were carried out.Experimental results show that with the increase of camber angle,the choice range of curve height correspond to the best performance in different incidences become narrower.The effects of incidence angles on the aerodynamic performance of positive curved cascades with large camber angle are more evident contrast to with small camber angle.The performance of positive curved cascades with 60°camber angle is so sensitive to the curved angle changing at higher incidence angles,so that a positive curved cascades with larger curved angles than 15°is inadvisable.
Experimental investigation of the characteristics of synthetic jet with different orifice aspect ratio and frequency
LI Nian, ZHANG Kun-yuan, SHA Jiang, LI Fu
2007, 22(3): 412-418.
Abstract PDF(1476KB) icon1643 icon400
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By means of experimental investigation of the unsteady flow near the orifice of synthetic jet actuator using PIV technology and using the phase-locked sample technique,72 instantaneous images and quantitative measurements during one actuating cycle for three different frequencies 10,20,30 Hz are obtained.The PIV measurements rdisplay the properties and structures of the unsteady flow field.Detailed study shows that in the current experiment,with fixed orifice scale and increasing frequency,the corresponding average orifice velocity U0 and stroke length L0 increase.While with constant driving frequency and increasing aspect ratio,both average orifice velocity U0 and stroke length L0 decrease.Also with increasing thickness of the orifice plate d,the friction in the orifice channel increases,consequently the average orifice velocity U0 and stroke length L0 decreases.Time-averaged flow field obtained by 350 image pairs overlapped shows the similarity of dimensionless cross-stream velocity profile and the centerline velocity decay ratio of synthetic jet in the fully developed segment is higher than the conventional 2D free jet.
New characteristics of fatigue-creep tests on serration of turbine blades
SUN Rui-jie, YAN Xiao-jun
2007, 22(3): 419-424.
Abstract PDF(640KB) icon1786 icon510
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The fatigue-creep life was found to be longer than the fatigue life from the Low Cycle Fatigue experiment of turbine blade of an aeroengine.The relevant theoretical calculation and analysis were then carried out to provide a further insight into such phenomenon.The research shows that: the actual working conditions of blades were well simulated in the experimental conditions,indicating that the damage of blade was mainly attributable to fatigue damage.As compared with pure fatigue test of real turbine blade,stress relaxation occurred at the key section(serration) under fatigue-creep test conditions,showing that fatigue/creep life of blade was longer than fatigue life.The research results play a key role in ensuring the safety of engines,improving the flight reliability and developing fatigue test techniques of high-temperature components.
Fatigue characteristics of FGH95PM superalloy under dwell condition and modeling for life prediction
WEI Da-sheng, YANG Xiao-guang, WANG Yan-rong, YU Hui-chen, SHI Duo-qi
2007, 22(3): 425-430.
Abstract PDF(581KB) icon1793 icon503
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This paper performs describes under different dwell conditions of FGH95 powder metallurgy superalloy at 650℃,and analyses its features of deformation and life distribution,and studies the obvious effect on life due to dwell.Then for improving the life modeling under dwell conditions,a modified factor of position-shape of hysteresis loop is presented,and a modified life equation as function of inelastic energy is established.Comparing with the predictive results of other life equations,the modified life equation has higher predictive precision,more compact form and clearer physical meaning.So life prediction of PM FGH95 under dwell conditions can be solved better.
A viscoelastic constitutive model under broad temperature frequency and dynamic displacement
LIN Song, GAO Qing, LI Ying-hui, YANG Xian-jie, ZHAO Yun-feng
2007, 22(3): 431-438.
Abstract PDF(1306KB) icon1784 icon481
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The tests of frequency sweeping and dynamic displacement sweeping at different temperatures for the viscoelastic material silicon rubber were conducted.The predication capability of the frequency response behavior for Burgers model and RT model was evaluated.Based on RT model,M-RT model was proposed and considered the influence of temperature,frequency and dynamic displacement was considered.The comparison between the experimental and predicted results shows that the proposed model in the paper can predict the dynamic constitutive behavior very well under broad temperature,frequency and dynamic displacement.
Performance analysis of aero-engine intershaft bearing
HU Xuan, LUO Gui-huo, GAO De-ping
2007, 22(3): 439-443.
Abstract PDF(475KB) icon1674 icon500
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Two kinds of aero-engine cylindrical intershaft bearings are analyzed with quasi-static method,in which one has co-rotating inner ring and outer ring,and the other is counter-rotating.Their cage's speeds and rollers' speeds under different radial loads are discussed,and then their operating performances are compared.It is concluded that,when the intershaft bearing is counter-rotating and its inner ring's speed is larger than its outer ring's,it has lower cage slip rate and longer fatigue life,and is helpful to wear and vibration stability of rotor system;when the bearing is co-rotating and its inner ring's speed is smaller,its speeds of rollers in the loaded zone are lower,and it benefits the life of rollers.
Investigation of dynamic response property of wide-chord hollow fan blade
YANG Wen, DU Fa-rong, HAO Yong, DING Shui-ting, LI Qiu-shi, WANG Ying
2007, 22(3): 444-449.
Abstract PDF(1676KB) icon1686 icon460
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Wide-chord hollow fan blade is the trend of future development.By means of numerical simulation,basic deformations and deformations under dynamic response were investigated through the analysis of mode characteristic and the study of dynamic response characteristic under the pulsed excitation.Results show that the blade mainly has flexural deformation as the blade vibrating,and the rotating speed of the blade must be within 6 000 rpm.The flexural vibratory deformation regulation and the structure of hollow with core board decide that the stress concentration should occur in somewhere of the center of blade basin with core board.In addition,the root of blade become into the area of stress concentration with the effect of centrifugal force under the blade's high rotating speed.
Method of reliability evaluation for P-T curve based on multi-sample time series analysis
MA Xiao-bing, ZHAO Yu
2007, 22(3): 450-453.
Abstract PDF(319KB) icon1609 icon444
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A reliability evaluation method for P-T curve based on multi-sample time series analysis is proposed.The method can synthesize longitudinal and transverse information existing in performance curves,and evaluate the internal ballistic reliability of solid rocket engine with high precision.The maximum likelihood estimations of multi-sample time series with both equally and unequally spaced data are discussed in detail.Furthermore,the formulas of point estimation and confidence interval estimation are introduced when upper and lower limits of P-T curve are assumed.An example is presented.
Preliminary development of fan and compressor aerodynamic design system
DU Hui, CHEN Bao-shi, HU Guo-rong, JIANG Da-zhi
2007, 22(3): 454-459.
Abstract PDF(490KB) icon1807 icon505
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This paper provides a brief introduction of the development of SAeRI's Fan and compressor aerodynamic design system.The new developed system is also a platform to cumulate experience and design rules.Emphasis was place on making the system efficient,easy to use and flexible.Now the system has been used in compressor design.
Experimental investigation and analysis of an axial compressor stage with 45° circumferential inlet pressure distortion
HUANG Jian, WU Hu, DU Wen-hai
2007, 22(3): 460-464.
Abstract PDF(569KB) icon1748 icon454
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A 45° circumferential inlet pressure distortion screen was designed and the effects of screen-induced circumferential inlet pressure distortion on axial flow compressor stage were investigated at a high speed subsonic compressor test rig. The performance characteristics for the rotor with circumferential inlet pressure distortion and clean inlet flow were compared at middle-speed.The circumferential pressure distributions at three axial locations(rotor inlet,rotor outlet and stator outlet) were measured.The results show that the inlet flow distortion has weak effects on the compressor stage at middle-speed.In addition,the enlarging and moving of the distortion-section are not obvious at rotor outlet, but it is enlarged about 100 percent at stator outlet;the distortion is enhanced at rotor outlet and decayed at stator outlet.However,with inlet distortion the pressure ratio of this compressor rotor is improved 1.8 percent and the equivalent mass flow reduced 2.5 percent at near-stall condition in comparing with clean inlet flow.
Effect of blade bowing and local modification on high-turning angle compressor stator performance
LI Shao-bin, SU Jie-xian, FENG Guo-tai, WANG Zhong-qi
2007, 22(3): 465-470.
Abstract PDF(878KB) icon1645 icon470
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This paper presents a numerical study of a high-turning angle compressor stator with 51°.The main ideas and local modification to achieve better control of boundary layer flow in aircraft are applied to the contouring of bowed stator.The skin friction line of suction side and total pressure loss are discussed in the straight blade,bowed blade and local modified bowed blade.The results show that the local modified bowed blade can effectively control the boundary layer flow and it is applicable to the boundary conditions of high adverse pressure gradient,high-turning and high subsonic inlet velocity.
Adaptive control study and experimental validation of a micro turbine engine
ZHANG Tian-hong, LI Qiu-hua
2007, 22(3): 471-474.
Abstract PDF(1056KB) icon1567 icon409
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In order to deal with the control problems of nonlinearity and difficulty of establishing an exact model of a micro turbine engine,a kind of adaptive control arithmetic is proposed and realized.Dead-area robust controlling is used in the adaptive control arithmetic to overcome the stability problem caused by model error and outside disturbance.By adopting forward feed compensation,the output of the engine can track the output of the reference model,and eliminate the possibility of saturation and oscillation when using pure adaptive control arithmetic.The rig test experiments show that,the adaptive control arithmetic has good real time characteristic and robustness in the whole working range of 125000 r/min with the overshoot of less than 500 r/min and the stable error of less than 200 r/min,which can meet the demands of micro turbine engine state regulation.
Optimal sensor location of scramjet combustor
BAO Wen, GUO Lin-chun, CUI Tao, LIN Min, NIU Jun
2007, 22(3): 475-479.
Abstract PDF(842KB) icon1819 icon482
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Combustion control and performance evaluation for scramjets need effective measurement information,therefore it is important to choose the optimal location and number of sensors.This problem is a combinatorial optimization problem which is difficult to solve.This paper applies genetic algorithm to choose the optimal location and number of sensors,and the genetic algorithm performs a parallel,non-comprehensive search for the global optimal results.
Research on key control technology of micro turbine engine in centimeter size
LIU Yuan, HUANG Xiang-hua, ZHANG Tian-hong
2007, 22(3): 480-484.
Abstract PDF(467KB) icon1830 icon459
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Key control technology of micro turbine energy(MTE) in centimeter size was studied for engineering applications,based on MTE's characteristics.The starting control was firstly transformed for the targeted engine with reference to the starting control time sequence of MTE.The self-revised fuel supply technology was proposed for the first time in order to solve the startup problem of MTE.After the idle state,MTE's model was established by means of system identification,and a closed-loop PI with self-adjust feedforward was designed through simulation and experiments.The test run of MTE demonstrates that the control rules can ensure normal and reliable operation of MTE while meeting the requirements of performance indicators.
Design of non-fully recover LQG/LTR control system of aeroengine
WANG Yong-ting, GUO Ying-qing, WANG Hai-quan
2007, 22(3): 485-489.
Abstract PDF(575KB) icon1868 icon434
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To solve the problem of excessively big parameter value in the conventional LQG/LTR controller,a design method was proposed for non-fully recover LQG/LTR.The principle for reducing the controller parameter value was explained from the perspective of system's zero-pole relationship.This method was applied to design the aeroengine control system.Simulation results indicate that this method could suppress effectively the parameter value of controller,but also present more satisfactory performance than conventional LQG/LTR design method.
Multivariable adaptive decoupling control based on auto-tuning neurons for aeroengine
ZHU Yu-bin, FAN Si-qi, ZHANG Xiu-hua, LI Hua-cong
2007, 22(3): 490-494.
Abstract PDF(1384KB) icon2027 icon435
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According to the requirements of aeroengine performance control,a new neural network called auto-tuning neurons and gradient descent learning method are presented.A multivariable decoupling control algorithm based on the auto-tuning neurons is used for aeroengine multivariable control systems in this paper.The main difference between an auto-tuning neuron and a general neuron is that there are adjustable parameters of the activation function used in an auto-tuning neuron.Unlike traditional fully connected neural network,there are no synaptic connections among the independent neurons.The emphasis is focused on the research of the algorithm and the properties of the controller,as well as their application to the aeroengine control by means of computer simulation.Finally the aeroengine multivariable control system is designed.Simulation shows that the system has perfect performance of decoupling and adaptive capabilities.
Design of codec for FIR used in the telemetry of aeroengine rotor
YAN Hou-xuan, ZHANG Tian-hong, SUN Jian-guo
2007, 22(3): 495-499.
Abstract PDF(719KB) icon1604 icon390
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In the telemetry system of aeroengine rotor,the multi-channel parallel FIR(fast infrared) data communication needs several codecs.With the CPLD(complicated programmable logic device) they can be realized on only one chip.It avails to reduce devices of the telemetry system and simplify setting on the rotor.In this paper,a Codec for FIR data communication was designed with one CPLD chip.The data communication with 4PPM(four pulse position modulation) was tested at 4 Mbps.The reason of mistakes in the communication with 4PPM was found after analyzing the response time of the infrared transceiver and the precision of the oscillation.Then two more efficient codes,2/3PPM and 4/5PPM,were proposed,which enhanced the speed of the data communication.
Experimental investigation of flowrate characteristics of gas-gas injector
DU Zheng-gang, JIN Ping, YANG Li-jun, CAI Guo-biao, ZHANG Meng-zheng
2007, 22(3): 500-504.
Abstract PDF(593KB) icon1769 icon429
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Seven types of gas-gas injectors involving two patterns were employed to conduct the flowrate characteristics tests at different back pressure conditions.An investigation on flowrate characteristics of one type of injectors was made at single propellant injection.The effects of inlet pressure of injector and back pressure as well as interaction between oxidizer injector and fuel injector on flowrate characteristics were investigated.Through the experimental measurements and fitting a mathematical expression,the formula of discharge coefficient was given.The results presented in this paper may provide valuable reference for the optimization design of the gas-gas injector for full flow staged combustion cycle engine.

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