2007 Vol. 22, No. 8

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Effect of magnetic plasma on heat transfer characteristics of nozzle wall
HUANG Hu-lin, ZHANG Yan
2007, 22(8): 1209-1215.
Abstract PDF(1003KB) icon1592 icon405
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A new method, based on the concept that the turbulence and heat transfer of plasma are suppressed under the magnetic field, was proposed to separate the high temperature gas from nozzle wall by controlling the cold plasma with magnetic field.The purpose of this method is to reduce heat transfer from high-temperature gas to nozzle wall, thereby cutting down the wall temperature.The equation of induced magnetic field was set up to calculate the Lorentz force, and the modified k-ε turbulence model under magnetic force was used to measure the viscosity of turbulence.Numerical simulation was conducted to determine the flow and heat transfer characteristics of magnetic plasma under different magnetic fields.The results show that, the magnetic field could efficiently suppress the turbulence strength and reduce the heat transfer capability for lower nozzle wall temperature;the stronger the magnetic field, the more distinct the effects are.
Experimental study on heat transfer in rotor-stator cavity with high-positioned pre-swirl inflow
WANG Suo-fang, ZHU Qiang-hua, LUAN Hai-feng, ZHANG Yu
2007, 22(8): 1216-1221.
Abstract PDF(686KB) icon1712 icon469
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A turbine disc-cavity cooling configuration of an aero-engine was simplified to a rotor-stator cavity model with high-positioned pre-swirl nozzle.The influences of rotor-stator gap, cooling air flux, rotational Reynolds number and swirl ratio on the drop of cooling air temperature and heat transfer on the rotor were experimentally investigated by using advanced temperature measurement technology of the thermochromic liquid crystal.The experimental results indicate that, the high-positioned pre-swirling inflow yields outstanding cooling effect on the rotor fringe, and the temperature of the rotor is distributed in the shape of concentric circle;the drop of cooling air temperature diminishes with the increase of rotational Reynolds number and rotor-stator gap, or with the decrease of cooling air flux, meanwhile, the cooling effect on the rotor becomes worse.
A new adjustment method of combustor outlet temperature field
HU Hao-sheng, ZHAO Jian-xing, ZHONG Jian-ping, JIANG Rong-wei, YIN Mei-zhi
2007, 22(8): 1222-1226.
Abstract PDF(1113KB) icon1616 icon428
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Based on a testing platform of a small-sized reverse combustor, the effect of different axial locations of fuel nozzle in the swirler on combustor outlet temperature field is studied by experiment.And, the experimental results are also compared and analyzed.Experimental data show that, for the same combustor, there is an optimized axial location between the fuel nozzle and the swirler.In such case, the pattern factor of outlet temperature is minimum;Under the operating state of the same combustor, the optimized axial location of the fuel nozzle changes with the fuel nozzle spray angle.This study thus provides an effective technical approach to adjust the outlet temperature field and develop the combustor.
Numerical studies of heat transfer in a rotor-stator cavity with different radial positions of pre-swirl inlet
WANG Suo-fang, ZHU Qiang-hua, ZHANG Yu, LUAN Hai-feng, HUANG Ai-xia
2007, 22(8): 1227-1232.
Abstract PDF(939KB) icon2010 icon498
Abstract:
The three-dimensional numerical simulations of heat transfer in a rotor-stator cavity with pre-swirl nozzles at different radial positions in the stator were conducted in this paper.The standard k-ε turbulence model and unstructured grid were applied with the purpose of investigating the heat transfer characteristics.Under the constant mass flow rate and the different radial position of the pre-swirl nozzles, the outflow temperature and the effect of heat transfer on the rotor are greatly affected by the different rotational Reynolds number, pre-swirl angle and rotor-stator gap.The results show that the heat transfer of the rotor is enhanced with the increase of the rotational Reynolds number or the decrease of the rotor-stator gap.When the pre-swirl nozzles were moved out along the radial direction, the temperature difference between the inlet and the outlet and the averaged Nusselt number take on up-down tendency, that is, exists a optimum radial position of the pre-swirl nozzles.
Numerical analysis of combustion performance in an annular combustor with two-stage swirler
LI Jing-hua, ZHAO Jian-xing
2007, 22(8): 1233-1240.
Abstract PDF(2075KB) icon1821 icon427
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In an arbitrary curvilinear coordinate system, a multidimensional empirical analysis methodology was developed to calculate the combustion performance of an annular combustor, which consists of the dump diffuser, two-stage flame tube and cooling passages.The RNG k-ε turbulent model was also modified, for enabling correct calculations of three-dimensional and two-phase turbulent reactive flows under a non-staggered grid system.Spray combustion was simulated through EBU-Arrhenius turbulent combustion model, six-flux radiation model and particle trajectory model.And numerical analysis was conducted for the effects of the geometry of swirlers on entire combustor flow fields and combustion performances.Predictions and measurements were in satisfactory agreement, and it was shown that numerical procedures are fairly reasonable and reliable for estimating the combustion performances of annular combustors.
Turbulent combustion flow field calculation for afterburner with heat shied
ZHANG Hai-tao, ZHAO Jian-xing
2007, 22(8): 1241-1246.
Abstract PDF(904KB) icon1614 icon472
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In an arbitrary curvilinear coordinate system, numerical simulation was performed for 3D turbulent combustion flow field of the afterburner with the cross-rippled heat shield, outer cold passage and jet nozzle.The body-fitted grids were generated using a system of elliptical partial differential equations.The k-ε model was employed to describe the turbulent characteristics.EBU-Arrehenius turbulent combustion model was used to determine the chemical reaction rate, while a six-flux model was applied to predict heat radiation and its influence on the wall and gas temperature.The discretion of governing equations in a non-staggered grid system was obtained by hybrid scheme and was solved with SIMPLE algorithm.The influences of two different inlet gas parameter distributions on afterburner flow characteristics and wall temperature profiles were analyzed numerically.Calculations were in good agreement with the experimental data and show that numerical procedures are fairly reasonable.
Influence of periodic electro-heating pulse on deicing surface temperature
CHANG Shi-nan, HOU Ya-qin, YUAN Xiu-gan
2007, 22(8): 1247-1251.
Abstract PDF(1391KB) icon1571 icon439
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The system design and optimization depends upon the research on the effect of electro-heating pulse of periodic electro-thermal deicing system on surface temperature.In this paper, periodic deicing surface temperature was calculated based on transient heat transfer modeling of two-dimensional rectangular elements of the system, while the governing differential equations were solved by using Control Volume Method.The main influential factors to surface temperature was also analyzed, helping to obtain the relationship between surface temperature and electro-heating pulse.The results indicate that, power supply density and electro-heating cycle play an important role on the effect of deicing requiring proper matching.
A numerical study on the effects of bamboo-shaped pin fin arrays on flow and heat transfer
HUANG Guo-lian, WANG Suo-fang
2007, 22(8): 1252-1257.
Abstract PDF(720KB) icon1776 icon427
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The effects of pin fins on the flow and heat transfer of passage was studied via numerical calculation method, and the flow field of bamboo-shaped columns was simulated.The calculated results show that, as compared with circle-shaped columns, the pressure loss of rectangular passage with circle bamboo-shaped and elliptic bamboo-shaped columns is 62%～77% and 25%～27%, and the average Nusselt number on the uniform heat flux end wall decreases to 9%～22% and 22%～24%.The pressure loss increases with the reduction of spacing between pin fins, and the variation of the pressure loss induced by changing spanwise pin fins spacing is more obvious than by changing streamwise pin fins spacing.
Study on the breakup lengths of free round liquid jets
ZHU Ying, WAN Yun-xia, HUANG Yong, PENG Xin-ke
2007, 22(8): 1258-1263.
Abstract PDF(636KB) icon1367 icon453
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An experi ment was conducted to measure the breakup lengths of water jets with a high-speed video camera for Weber numbers from0 to about 1.1×103.The initial jet diameters are changed from0.3 mmto 1. 0 mm.The results indicate that at lowjet velocity the breakup lengths of the jets are increased linearly from 0 to a maxi mumvalue.At the Weber number about 20 the breakup length of the jet reaches its maxi mum value for different initial jet diameter.Acomputation based onthe dispersion equationis conducted to study the relationship between the growth rate of the jet surface wave and the maxi mumbreakup length.The computations showthat the maxi mumgrowth rate for the axisymmetric surface wave has a turning point at Weber number about 20, and that agrees well with the experi ments.
Experimental investigation on heat transfer characteristics of drug-reduction surface
WU Hong, WANG Jiao, LIU Kun
2007, 22(8): 1264-1267.
Abstract PDF(537KB) icon1523 icon465
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The heat transfer characteristics of ribbed surfaces with rectangular channel were experimentally studied under different Reynolds numbers.The experimental results indicate that the small longitudinal ribbed surface of h=s=0.5 mm has great drag-reduction characteristics within the test range, and its drag-reduction declines with the increase of Reynolds number.As compared with heat flow in flat plate channel, the heat transfer characteristics of ribbed surface decreases in the case of 10 0001).Moreover, the heat transfer enhancement ratio increases with Reynolds number under test conditions.
Numerical study of 3D heat transfer for turbine blade with air cooling
ZHANG Li-fen, LIU Zhen-xia, LIAN Xiao-chun
2007, 22(8): 1268-1272.
Abstract PDF(618KB) icon1652 icon465
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A coupled flow-thermal model was established for 3D heat transfer of turbine blade with air cooling.Radiation heat was added into the energy equation as a source of heat radiation.Using coupled flow-thermal model, 3-D conjugated heat transfer for turbine blade with air cooling was accomplished.And, heat radiation was solved with P-1 model.The different surface temperatures and temperature distributions of the blades with/without heat radiation was compared.The results show that, for high-temperature gas at 1 600 K, heat radiation is a significant heat source.If radiation heat is considered, the surface temperature of the blade is improved greatly, leading to obvious difference of temperature distribution.
Experimental research on vaporization rate of micro"T"-vaporizer
ZHU Jing, GUO Xin-hua, LIN Yu-zheng, XU Guo-qiang
2007, 22(8): 1273-1278.
Abstract PDF(714KB) icon1592 icon455
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The variations of vaporization rate of Micro "T"-Vaporizer under various working conditions were studied.The experiments were conducted at vaporizer inlet under normal atmospheric pressure.The main influential factors to vaporization rate were tested, which include the air/fuel ratio, inlet air temperature, vaporizer wall temperature and the velocity of the airflow into the vaporizer.The experimental results show that, the air/fuel ratio, inlet air temperature and vaporizer wall temperature are major influential factor to vaporization rate.But, the velocity of the inlet airflow is less influential.The vaporization rate of the micro Tvaporizer is nearly 100%, when inlet air and vaporizer tube wall are heated simultaneously and the air/fuel ratio is more than 4.5.
Numerical simulation and experimental verification of a fixed-geometry 2D mixed-compression supersonic inlet with sweepforward high-light and "X"-type missile configuration
WAN Da-wei, GUO Rong-wei
2007, 22(8): 1279-1284.
Abstract PDF(667KB) icon1557 icon432
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A numerical simulation was conducted for a fixed-geometry two-dimensional mixed-compression supersonic inlet with sweepforward high-light and "X"-type missile configuration.The results indicate:(1) The total pressure recovery declines with the rise of the free stream Mach number, while the mass flow ratio rises firstly and then declines when its maximum value is obtained at the design point.(2)When the angle of attack increases less than 6°, the total pressure recovery of both side inlets decreases in a narrow range;the mass flow ratio of the lee side inlet is higher than that of the windward inlet, the total flow mass of both sides is almost constant.(3) When the angle of attack increases from 6° to 9°, both the total pressure recovery and the mass flow ratio fall rapidly at the lee side inlet, whereas the total pressure recovery declines and mass flow ratio rises at the windward side inlet.(4)The numerical simulation results show a consistent trend with the experimental results.
A study on flight attitude model of flapping wing micro air vehicle
DUAN Hong-jun, SHI Xiao-ping
2007, 22(8): 1285-1289.
Abstract PDF(1725KB) icon1799 icon499
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The flight quality of Flapping Wing Micro Aerial Vehicle(FWMAV) depends much upon efficient control of flight attitude.So, an accurate model of flight attitude is of utmost importance.The fly mechanism of birds and big insects, especially the motion rule of wings were investigated, and the factors on mechanical design were also considered to establish a complete dynamic model and mathematical model of flight attitude of FWMAV.It is learnt that the airframe is subjected to aerodynamic force, gravity, and propulsion from airfoils.For airfoil motion with two degrees of freedom-flapping and rotation, the propulsion is an instantaneous aerodynamic force combined from instantaneous translational force and rotational force.The numerical simulation also demonstrates the validity of the dynamic model.
Study of design method of typical two-dimensional hypeisonic inlet
ZHANG Xiao-jia, LIANG De-wang, LI Bo, YUAN Hua-cheng
2007, 22(8): 1290-1296.
Abstract PDF(614KB) icon1804 icon457
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A feasible design principle was developed by combining a series of design and performance predicting methods of typical two-dimensional hypersonic inlets.The design methods of inlet entrance, external compression shocks, internal contraction tunnel, cowl and isolator were presented at the given flux, pressure rise ratio and working range(starting Mach number and capability of enduring back pressure).A preliminary design of hypersonic inlet at the design point of H=22 800 m, Ma0=6 was conducted, so the performance parameters(pressure rise ratio, Mach number, temperature rise ratio and total pressure recovery), starting Mach number and capability of enduring back pressure were predicted and calculated with small error.With this method, the inlet could present simple construction, high flow coefficient and low compression loss in developing a satisfactory model without optimization.
Hypersonic vehicle-inlet integrated aeroheating simulation
DING Hai-he, WANG Fa-min
2007, 22(8): 1297-1302.
Abstract PDF(593KB) icon1544 icon490
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Aeroheating analysis of propulsion/forebody integration has been conducted by means of CFD technique.Especially, different computation models are adopted for different flow regime, including laminar, transition and turbulent flow.In this text, compressibility-corrected SSGZ-J k-ε model has been employed in turbulent region, moreover, we introduce algebraic intermittency model of transition to simulate the transition process from laminar to turbulent.By these methods, wall heat flux of forebody and engine has been calculated and compared with experimental results.Results show that compressibility-corrected SSGZ-J kε model can reasonably predict heat flux in the complex high-speed compressible flow, and algebraic intermittency model of transition can simulate transition process of boundary layer.Flow regime, structure geometry and shock wave have great effects on heat flux.
A finite element model of sound propagation in flow duct with its application to linear optimization
LU Zhen-bo, JING Xiao-dong, SUN Xiao-feng
2007, 22(8): 1303-1308.
Abstract PDF(474KB) icon1615 icon534
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A finite element model is presented for sound propagation in a flow duct with an acoustic liner, which incorporates the major practical effects of wall impedance, variable duct geometry and non-uniform flow.This model is applied to simulate the duct liner effect on reducing the noise of a real high-speed rotor.Both the distribution andreduction of the sound pressure inside the duct and the optimized liner impedance are obtained.The results show that the present model can be used for the design purpose of a duct liner in the practical engineering applications.
Aircraft engine performance-cost tradeoff model framework based-on CAIV
TAN Yun-tao, GUO Bo
2007, 22(8): 1309-1314.
Abstract PDF(2227KB) icon1607 icon396
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A study on aircraft engine performance-cost tradeoffs and decision-making method was made in application of CAIV(Cost as an independent variable) method.An engine parametric-cost-estimating model was brought forward, and then an analysis was made on the relationship between performances and parameters, and an engine performance model was built.Thereafter, the research was focused on how to define the constraint of parameter alternatives.Finally, by integrating all above studies, an aircraft engine performance-cost tradeoff model framework was built to assist decision making of parameters targets and total ownership cost goal.
Experimental study of flapping-wing MAV in wind tunnel
LIU Lan, FANG Zong-de, ZHANG Xi-jin
2007, 22(8): 1315-1319.
Abstract PDF(932KB) icon1801 icon485
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The lift wind tunnel tests were conducted for the manufactured flapping-wing MAV(Micro Air Vehicles) in a low Reynolds number wind tunnel of NPU(Northwestern Polytechnical University).And, the lift characteristic curves of MAV in normal flight and climbing state were measured.Also, the influence of flapping frequency, wind velocity and angle of attack on aerodynamic characteristics was investigated.Based on the wind tunnel test, the composition of flapping lift and their relations were discussed.The test result provide a reference for the design of flapping-wing MAV.
Research on identification model of turbofan windmilling starting characteristics based on parsimonious genetic programming
ZHANG Dong-fang, LI Ying-hong, WEI Xun-kai
2007, 22(8): 1320-1324.
Abstract PDF(1550KB) icon1889 icon535
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In order to solve the problem of turbofan starting characteristics estimation under windmilling condition, an approach to automatic selection of model structure via Parsimonious Genetic Programming(PGP) was presented.The engine windmilling starting model based on PGP was also studied.The starting characteristics of a certain turbofan under windmilling condition were modeled and simulated by this method.It is proved to be correct and feasible if the estimation results are compared with the experimental data
Numerical investigation on internal flow of a spherical convergent flap nozzle with complex geometry
SONG Jie, WANG Qiang
2007, 22(8): 1325-1329.
Abstract PDF(669KB) icon1751 icon465
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To analyze three-dimensional internal flow characteristic of spherical convergent flap nozzles with hexagonal and bowtie geometries, the geometric models were established and N-S equation and S-A model were employed in the numerical simulation.The simulation was developed at different NPR(nozzle pressure ratio).The calculated results are compared favorably well with experimental data.Furthermore, the internal flow characteristic and performance of two nozzles are compared and analyzed.
Source term model of vane flow on a flat plate
GAO Li-hu, ZHANG Xi-wen, HE Feng, ZHU Yu
2007, 22(8): 1330-1334.
Abstract PDF(725KB) icon1674 icon426
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A source term model was applied to numerical simulation of a vane vortex generator, where the lift force created by a vane vortex generator was used as one part of the prototype of source term model, and a normal force was introduced as the other one.The source term depends on the shape, size and location of the vane and the freestream conditions.During numerical simulation, the vane was located on a flat plate, with its height about one fifth of the thickness of local boundary layer.The calculated results of "lift & normal force" source term model were compared under the same conditions with the calculated results and experimental data for a full gridded vane vortex generator.This source term model helps to predict the velocity and vortex fields in consistent with a full gridded vane vortex, but the grid number reduces by 65%.
Entropy method of reliability assessment for system consisting of binomial units and exponential units
SUN You-chao
2007, 22(8): 1335-1339.
Abstract PDF(288KB) icon1556 icon450
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According to the information equivalence principle, the reliability assessment method was studied for the system comprising binomial units and exponential units.The basic conversion models of entropy method were established for the binomial system or the exponential system based on individual test information.Meanwhile, the conversion formulas were presented for the binomial information and exponential information, and the availability of the method was illustrated comparatively through analysis of the examples and assessment results.
A diagnostic approach to rolling element bearing based on vibration signal of shaft in a rotating reference frame
LEI Jian-yu, LIAO Ming-fu
2007, 22(8): 1340-1345.
Abstract PDF(1441KB) icon1706 icon494
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In order to diagnose local defects in a rolling element bearing, an approach was developed based on vibration signal of shaft in a rotating reference frame.A test rig for rolling element bearing was established, and piezoelectric accelerometers were used to measure the vibration signals of shaft.The feasibility of this approach was demonstrated by the experimental results from four typical defects involving inner race, outer race, rolling element and cage.It was found that the transmission path of vibration signals of shaft is relatively simple, contributing to early detection and diagnosis of minor defects for inner race, outer race, rolling element and cage.
Parametric modeling and multidisciplinary design optimization for cooling turbine blade
YU Kua-hai, YUE Zhu-feng
2007, 22(8): 1346-1351.
Abstract PDF(925KB) icon1653 icon532
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A multidisciplinary design optimization system for gas turbine blade, which involves structure, aerodynamic, heat transfer, vibration and service life, etc, has been developed, serving the purpose of multidisciplinary design optimization of single-hole thin wall cooling blade.A parametric modeling method was also proposed for single-hole thin wall cooling blade.The blade surface geometry is defined by five-order polynomials, while 3-D coupling analysis was made for aerodynamic and heat transfer.The average temperature and maximum temperature of blade volume were optimized, with aerodynamic, vibration and service life as the constraints.A combined algorithm of annealing simulation and SQP(Sequential Quadratic Programming) was used to optimize the blade parameters.While the flow rate of cooling air was kept unchanged, the cooling effect was improved and the performance requirement on the blade materials was reduced.
State function for evaluating steady stress of aeroengine parts
LIU Ting-yi, ZHANG Jun-feng, LI Qi-han
2007, 22(8): 1352-1355.
Abstract PDF(298KB) icon1607 icon440
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According to the law of aerodynamic similarity, based on the stress obtained from FEM analysis under characteristic condition, state function was deduced for other operating conditions.This function can be used to determine steady stress and strain for any arbitrary operating conditions.This technique provides stress spectrum for the prediction of structure life.The method presented is valuable in life prediction and life management.
Numerical analysis and optimization of the inlet stage of a multi-stage high pressure compressor
XU Quan-yong, HOU An-ping, XIONG Jin-song, ZHOU Sheng
2007, 22(8): 1356-1364.
Abstract PDF(1336KB) icon1352 icon428
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An opti mization process is used to redesign blades of a high-pressure compressor.An artificial neural network (ANN) method is coupled to Navier-Stokes solvers and is applied to three different redesigns.A newrotor blade of a transonic compressor is designed by modifying thick, stacking line andinlet angle using a 3Dapproach, with a significant efficiencyi mprovement at the design point.The off-design behavior of this new compressor is also checked afterwards, which shows that the whole performance of the inlet stage is improved over a wide range of mass flow.The losses are reduced, proving the good performance of the opti mum.The whole results indicate that the opti mization method can find i mproved design and can be integrated in a design procedure.
Numerical investigation of boundary layer suction in an axial transonic compressor cascade
GE Zheng-wei, GE Zhi-mei, ZHU Jun-qiang, ZHANG Hong-wu, HUANG Wei-guang, DU Hui
2007, 22(8): 1365-1370.
Abstract PDF(1886KB) icon1684 icon482
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Based on the numerical investigations on the performance of an axial transonic compressor cascade with different suction slot locations and suction mass-flow, it has been shown that for a given inlet Mach number and flow angle, there exist an optimal suction mass-flow corresponding to the suction slot location.And the optimal suction mass-flow increases as the suction slot moves far from the shock location towards the trailing edge.The perfect suction slot location should be at the beginning of the transition region where the boundary layer thickness has developed to a local maximum value downstream of the shock.
Frequency-domain analysis of NASA67 unsteady flow field
ZHAO Jun, LIU Yang-wei, LIU Bao-jie
2007, 22(8): 1371-1377.
Abstract PDF(1277KB) icon1627 icon412
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Based on fast fourier transformation for the typical profile of NASA67 unsteady flow field, the rotor-stator interactions, the circumferential distributions of typical unsteady perturbations at the rotor-stator interface and the inter-blade phase angle were analyzed in the frequency-domain.Also, some phenomena difficult to observe in time-domain were visualized in frequency-domain.Finally, the deterministic stresses from five-order harmonic synthesis and unsteady simulation were compared, meanwhile the feasibility and advantage of nonlinear harmonic method in modeling the deterministic stresses were analyzed.
Design of aero engine multi-loop controllers with switching characteristics
YU Da-ren, LIU Xiao-feng, SUI Yan-feng
2007, 22(8): 1378-1383.
Abstract PDF(1646KB) icon2002 icon465
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The switching problem of aero-engine multi-loops control system was studied, and the performance index requirements were also analyzed.Based on the pole placement and H∞ robust synthesis, linear matrix inequalities(LMI) were constructed to provide a firm basis for determining H∞ design method under multi-loop switching.As compared with traditional method of single-loop system, the simulation showed the feasibility and the necessity of the method hereto.
Research on the startup model of turbofan engine at high altitude
ZHOU Wen-xiang, HUANG Jin-quan
2007, 22(8): 1384-1390.
Abstract PDF(1977KB) icon1823 icon455
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Based on the above-idle component-level model, a two-spool turbofan engine startup model was developed according to extrapolated component characteristics.The model can simulate the startup of windmilling and starter at high altitude.This model has taken into account the influence of fuel-air ratio on combustion efficiency, heat transfer model was built up to estimate the influence of heat transfer on combustor, thermal inertia of combustor and high-/low-pressure turbine as well as the change of total pressure recovery coefficients of different components during startup.The method of volume dynamic was used in order to avoid iterative calculations.The simulation results show that the real-time model has a simulated speed error less than 5%, making it possible to meet the demand of high-altitude startup performance simulation for aeroengine.
Double variable PID decoupling control of turbofan engine based on RBF neural network identification
YANG Hua, GUO Ying-qing
2007, 22(8): 1391-1395.
Abstract PDF(602KB) icon1720 icon401
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According to the concept of combining the neural network and PID in solving the problem of coupling in turbofan engine double-variable control system, double variable PID decoupling control method for turbofan engine based on RBF neural network identification was presented in this paper.The structure of engine decoupling control system, as well as its decoupling principle was given.Simulation of the control system was performed and excellent tracking performance and robustness were obtained.The simulation results show that the method can effectively reduce the coupling influence of each control loop and assure satisfactory transient performance, thus it is suitable for the aero-engine control.
Signal processing and on-line failure monitoring of LVDT sensor on aero-engine control system
JIANG Cheng, PENG L i zhi, SUN Jian-guo
2007, 22(8): 1396-1400.
Abstract PDF(490KB) icon1816 icon437
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After in-depth study of LVDT signal processing circuit, a basic solution for problems, such as: chip fever, temperature drift and signal accuracy, were presented.Meanwhile, an on-line monitoring method combining software and hardware was also proposed without addition of external components.The result of engine bench experiment proves the feasibility of this method.

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