2015 Vol. 30, No. 8

Display Method:
Analytical solutions of velocity and temperature in laminar boundary layer over a flat plate with wall injection flow using HPM-Padé method
ZHAO Guo-chang, KONG Jing-ru, SONG Li-ping, DU Xia, SHAN Long, ZHAO Heng
2015, 30(8): 1793-1801. doi: 10.13224/j.cnki.jasp.2015.08.001
Abstract:
The HPM-Padé method was used to derive the analytical expression of dimensionless velocity and dimensionless temperature in the laminar boundary layer of a constant property, incompressible fluid over a flat plate with injection flow, when the injection fluid velocity is inversely proportional to the square root of the distance from the leading edge of the flat plate. The analytical solution produced by the HPM-Padé approximation of the first order derivative dimensionless stream function was consistent with the numerical solutions produced from the fourth order Runge-Kutta method. Analysis on the effects of injection coefficient and Prandtl number on the velocity and temperature distributions was performed using the analytical solutions obtained by the HPM-Padé method. Results show that, as Prandtl number increases, the temperature boundary layer becomes thinner and the temperature gradient on the wall becomes larger. As the injection coefficient increases, the thickness of temperature and velocity boundary layers increases. Furthermore, both wall velocity gradient and wall dimensionless temperature gradient decreases as the injection coefficient increases and injection on the wall creates an insulation effect. When injection coefficient is 0.619, wall velocity gradient and temperature gradient are both zero and the heat transfer from the high temperature flow to the wall is completely blocked by the injection fluid.
Influence of wind directions on the flow field structures of helicopter rotor and deck
SUN Peng, GENG Xue, ZHAO Jia, ZHONG Jing-jun
2015, 30(8): 1802-1810. doi: 10.13224/j.cnki.jasp.2015.08.002
Abstract:
In order to study the interaction between helicopter rotor and deck flow fields, numerical simulation was carried out on a composite flow field made up of ship and rotor. Streamline patterns, vorticity distribution, and balance of the helicopter rotor with different wind directions were analyzed. The appearance and evolution of the main vortex structures were elaborated and the vortex structures were classified. Simulation results show that,the rotor and the deck interfere with each other's flow field, forming a complex composite flow field structure. The existence of the rotor, with the wind coming from 0 degree direction, markedly enlarges the vortex range and accelerates the downwash flow in the back area of the deck. Crosswinds enlarge the vortex range of the deck and intensify the imbalance of the rotor blades. It becomes unfavorable to the helicopter's hovering when the wind comes from 15 degree to the starboard, because the lifting and balance capacity of the rotor blades are the worst under this condition.
Effects of passive cavity on high pressure ratio single expansion ramp nozzle
ZHOU Li, XIAO Hua, WANG Zhan-xue, LIU Zeng-wen
2015, 30(8): 1811-1817. doi: 10.13224/j.cnki.jasp.2015.08.003
Abstract:
The flow control method of single expansion ramp nozzle (SERN) was investigated based on passive cavity, and the effects of passive cavity on internal flow field and performance of SERN were numerically investigated under over-expanded condition by solving Reynolds average Navier-Stokes equations, with adoption of standard two-equation k-ε turbulent model. When the pressure ratio value equals 8, the results show that the passive cavity for SERN has evident effects on the flow field structure by encouraging stable separation and affecting pressure distribution on upper expansion ramp wall, thus improving by 1.75% of the axial thrust coefficient of SERN as compared with baseline SERN, meanwhile the nose-down pitching moment does not get worse. Within the range of 3 to 13 of pressure ratio, the passive cavity can enhance the separation of boundary layer near the passive cavity for SERN, and improve the performance of SERN by decreasing the number of shock train and increasing axial thrust coefficient of SERN and pressure peak value distribution on upper expansion ramp wall.
Adjustment method of effective throat for axisymmetric vectoring exhaust nozzle
DU Gui-xian, JIN Wen-dong, SHAO Wan-ren, DENG Hong-wei
2015, 30(8): 1818-1825. doi: 10.13224/j.cnki.jasp.2015.08.004
Abstract:
Based on three-dimensional Reynolds-averaged Navier-Stokes equations, the interior flow field of axisymmetric vectoring exhaust nozzle was investigated numerically, and variation of effective throat and flux coefficient with vectoring deflection angles was analyzed at different nozzle pressure ratios. The results show that,when the vectoring deflection angle exceeds a certain value, effective throat position of the axisymmetric vectoring nozzle inclines, effective throat area reduces, and flux coefficient decreases with the increase of vectoring deflection angle and the decrease of nozzle pressure ratio. According to the results, an adjustment method of effective throat for axisymmetric vectoring exhaust nozzle used during nozzle vectoring is proposed by taking the nozzle pressure ratio and the vectoring deflection angle as input parameters; and the variation of flux coefficient is considered before and after adjusting the axisymmetric vectoring nozzle throat area. This method can provide a more accurate input for engine control system, improve the control accuracy with the flux variety less than 0.4%,and shorten by 10% of the adjustment time at least. The method can provide a reference for state regulation of thrust-vectoring engine.
Modularized simulation modeling of air system with fast transients
LIU Chuan-kai, LIU Hai-ming, LI Yan-ru, CHE Wei-wei, DING Shui-ting
2015, 30(8): 1826-1833. doi: 10.13224/j.cnki.jasp.2015.08.005
Abstract:
A modular modeling method for air system with fast transient was established. The air system model was decomposed into four kinds of basic units interconnected by the standard data interface, which accounts for combined effects of volume packing and flow inertia during rapid transients. The numerical code was programed by utilizing object oriented technology, and its predictions were validated against published data. The results show that the simulation model accurately predict the millisecond time scales physical phenomena of air system with fast transients, such as reversal flow, transmission of pressure wave, coupled oscillations between multiple cavities, etc. Moreover, its modular charicteristic allows integration of further detailed air system units and establishment of more complex air system network. The modularized simulation method has prospect in studying the complex dynamic characteristics and mechanism of aero-engine air system.
Optimal design and endurance estimation of propulsion system for electric-powered unmanned aerial vehicle
WANG Gang, HU Yu, SONG Bi-feng, TAN Chang
2015, 30(8): 1834-1840. doi: 10.13224/j.cnki.jasp.2015.08.006
Abstract:
For small electric-powered unmanned aerial vehicles (EPUAV), endurance performance largely depends on propulsion system. To improve EPUAV endurance, the electric-powered propulsion system was designed optimally. Meanwhile EPUAV endurance formula was presented. Based on vortex theory, a small screw propeller was designed optimally using genetic algorithm. A series of predicted motors were tested by dynamometer in order to match the optimized screw propeller effectively. The influences of discharged rating and voltage drop for lithium-ion battery were considered. Then a math model of battery discharge time was deduced while the battery output power was kept as constant. According to the optimal propulsion system and battery model, the EPUAV endurance formula was presented for cambered wing. Flight tests of a flying wing EPUAV indicate that optimized propulsion system operates more effectively after an optimal design. There exists approximately 12% error between flight tests and theoretical estimation. Within permissible error, good agreements have been obtained.
Study of start/unstart phenomenon of supersonic inlet in acceleration/deceleration process
ZHAO Hao, XIE Lü-rong, GUO Rong-wei, TNEG Yu-lin, ZHANG Jun
2015, 30(8): 1841-1852. doi: 10.13224/j.cnki.jasp.2015.08.007
Abstract:
In order to study start/unstart flow characteristic in the acceleration/deceleration process, an investigation of two-dimensional mixed-compression supersonic inlet was performed in steady/unsteady numerical simulation. The effect of absolute value of acceleration on inlet performance was analyzed at Mach number from 1.75 to 2.05 and four different absolute values of acceleration were considered. The results of steady and unsteady numerical simulations were compared. The results indicate: in both start and unstart processes, the flow characteristic of the unsteady case lags behind compared with the steady one's, and the larger absolute value of acceleration means more obvious phenomena. The performance in unsteady simulation obviously lags behind that in steady simulation. The start process of inlet spends more time than unstart process under the same absolute value of acceleration.
Measurement parameters selection method for gas path fault diagnosis of two-shaft split flow turbofan engine
HU Liang-quan, CHEN Min, TANG Hai-long, GUO Kun
2015, 30(8): 1853-1861. doi: 10.13224/j.cnki.jasp.2015.08.008
Abstract:
Aiming at measurement parameters optimal selection for gas path fault diagnosis in ground test bed, a four-step optimal method was presented. The four-step optimal method includes measurement parameters sensitivity analysis, component performance parameters correlation analysis, influence coefficient matrix condition number analysis and genetic algorithm validation. According to the first step, total air mass flow was picked out. In the second step, total temperature at fan exit and total temperature at compressor exit were picked out. In the third step, twelve measurement parameters combinations beneficial to fault diagnosis were picked out. In the final step, the best measurement parameters combination was obtained. Based on the genetic algorithm, the simulated diagnostic results show that, with these twelve measurement parameters combinations, all the fitness values for each single fault diagnosis are more than 0.85, which approximate the optimal fitness value 1. As to the most promising measurement parameter combination, all the fitness values are greater than 0.9 by genetic algorithm validation, which demonstrate the validity of this four-step optimal method.
Experiment on wing stall separation suppression by plasma aerodynamic actuation
WEI Biao, LIANG Hua, HAN Meng-hu, HUA Wei-zhuo
2015, 30(8): 1862-1868. doi: 10.13224/j.cnki.jasp.2015.08.009
Abstract:
Wind tunnel experimental investigation on wing stall separation suppression was performed and the influence of pulse frequency, voltage, duty cycle and actuation position on flow control effect was analyzed. The results showed that, at the free-stream velocity of 35m/s, the flow separation on the suction side of the wing under large angle of attack was suppressed effectively and the critical stall angle of attack increased from 17° to 19°. The maximum lift coefficient increased by 9.45% with a drag reduction of 20.9%. Experimental results demonstrate that control effect is best when frequency is 200Hz and the corresponding dimensionless actuation frequency is 1. Larger voltage is needed with the increase of the angle of attack because the separation becomes more serious. The best position of plasma aerodynamic actuation is right at the leading edge of the flow separation origin line. Power consumption can be reduced by decreasing the duty cycle at the same control effect.
Blade shape optimization of multistage compressor using adjoint method with static pressure constraint at interfaces between rows
TANG Fang-ming, YU Jia, LI Wei-wei, JI Lu-cheng
2015, 30(8): 1869-1874. doi: 10.13224/j.cnki.jasp.2015.08.010
Abstract:

To solve the problem with the drift of operation condition during the optimization procedure when adjoint method applied in multistage compressor, based on the previous development work of multistage compressor blades optimization design using adjoint method and thin shear-layer N-S equations, the entropy production was selected as the objective function with given mass flow rate and total pressure ratio as imposed constraints, a new constraint was introduced, namely, the spanwise static pressure distribution at the interfaces between rows was imposed. Taking one 5 stage compressor as a test case, the new method was applied at inter-row interfaces behind the rotor and the stator of the first stage in environment of the first 1.5 stage and the whole 5 stage compressor. The results show that the drift problem of the operation condition during optimization procedure is resolved successfully by applying the constraint on spanwise static pressure distribution at the interfaces between rows and the efficiency of 5 stage compressor is got 0.4% improving.

Influences of meridional flowpath on the performance of swept blade in an axial compressor stage
YU Xian-jun, XU Peng-fei, ZHANG Yi-fei, LIU Bao-jie
2015, 30(8): 1875-1887. doi: 10.13224/j.cnki.jasp.2015.08.011
Abstract:
A series of numerical simulations were conducted in both a 1.5 stage axial compressor model and a simplified planar cascade model. The cases with different blade sweep schemes in the cascade model were simulated with free-slip endwalls to minimize the influence of endwall 3-D(three-dimensional) flows. The results obtained in the cascade model were discussed at first for getting a clear insight into the effects of blade sweep without other influences. And then the simulation results of the 1.5 stage compressor model were discussed accordingly. The discussions focused on the influences of different meridional flowpath designs, i.e. constant mid radius (CMR) design, constant outer radius (COR) design and constant inner radius (CIR) design, on the performance of the swept blade. The results showed that the most critical effect produced by blade sweep was attributed to the redistribution of local mass-flow-rate in blade spanwise direction. The change of meridional flowpath did not change the mass-flow-rate redistribution behaviors. However, the trends for local mass-flow-rate redistribution in compressor stage model showed some discrepancies compared with the results shown in the planar cascade model.
Numerical investigation of unsteady aerodynamics and aero-acoustics in a centrifugal fan
ZHANG Jian-hua, CHU Wu-li, ZHANG Hao-guang, DONG Xing-jie
2015, 30(8): 1888-1899. doi: 10.13224/j.cnki.jasp.2015.08.012
Abstract:
The Lighthill equation was transformed into Helmholtz equation in “weak integral form” and Galerkin method was applied to discretize the above equations. Based on acoustic finite element method (FEM), and considering the effects of scattering and reflection on the complex solid surface (impeller and volute), the Ffowcs Williams-Hawking (FW-H) equation coupling unsteady reynolds average Navier-Stokes (UANS) results were used to simulate the noise radiation of a centrifugal fan. There was a good agreement between the numerical results and dynamic pressure testing of volute casing at blade passing frequency (BPF). The results show that the BPF components dominate the acoustic sources characteristic and the volute tongue region close to shroud (belong to impeller exit width) is a primary acoustic sources region. A good agreement has been shown between acoustic FEM method and noise testing results, and the effects of complex solid surface on noise propagation cannot be neglected. The interaction noise induced by periodical impingement between non-uniform flow of impeller exit and volute casing is much bigger than blades dipole noise, serving as the primary noise component of centrifugal fan, and the primary propagation direction is fan outlet duct.
Experimental and mechanism analysis of casing treatment with different axial angles
KUANG Hai-yang, CHU Wu-li, ZHANG Hao-guang
2015, 30(8): 1900-1908. doi: 10.13224/j.cnki.jasp.2015.08.013
Abstract:
Experimental and numerical simulations were performed on a subsonic compressor to investigate the stabilizing mechanisms of casing treatment with different axial angles at rotation speed of 8130r/min.Flow structures and static pressure distribution of rotor tip,flow structure in the slots(or grooves),loss distribution in rotor tip,axial momentum of the injected flow at different mass flows were studied.Results confirmed that the capability of the casing treatment of extending the compressor stall margin first increased and then decreased within the whole mass flow range,the loading of rotor tip increased and the isentropic efficiency decreased under large mass flow with the increasing axial angle of the casing treatment.
Numerical simulation of multi-diversion aero fuel centrifugal pump with ejector
LI Jia, LI Hua-cong, FU Jiang-feng, HAN Xiao-bao
2015, 30(8): 1909-1917. doi: 10.13224/j.cnki.jasp.2015.08.014
Abstract:
Targeting the multi-diversion aero fuel centrifugal pumps with ejector, the numerical simulation of the centrifugal pump was performed. By comparing the simulation data with test data, the simulation's accuracy was identified by Pumplinx. The inner flow characteristics of the model were calculated by analyzing the pressure of middle axial and middle radial areas. Then cavitation characteristic was simulated in the worst operating conditions; and the gas-liquid two-phase distribution of the pump's full cavitation state was given at its Δh values and Δh-H curve was acquired. Studies have shown that this centrifugal pump's head, efficiency and cavitation characteristic curve of numerical simulation meet the test data. Pressure of inner flow is steady, and could make high pressure at high efficiency under small flow states; meanwhile, it could not produce cavitation within its operating range at the input pressure of 0.018MPa, less than the input pressure of 0.027MPa for technical requirements at its full cavitation state.
Blade pattern optimization of the hydraulic turbine based onneural network and genetic algorithm
MIAO Sen-chun, YANG Jun-hu, WANG Xiao-hui, LI Ji-cheng, LI Tai-long
2015, 30(8): 1918-1925. doi: 10.13224/j.cnki.jasp.2015.08.015
Abstract:
A multi-condition optimization method, including the parameterization of blade pattern, the optimization of Latin hypercube experimental design, the CFD techniques, the genetic algorithm-back propagation (GA-BP) neural network and genetic algorithm, was presented for the blade pattern. Specifically, the non-uniform cubic B-spline curve was used to parameterize the blade pattern, and the optimized Latin hypercube experimental design method was employed for the acquirement of the sample points of GA-BP neural network. The performance analysis of each sample point was accomplished by the CFD techniques. Then, the learning and training of the GA-BP neural network was carried out. Finally, the optimization techniques combining the GA-BP neural network and genetic algorithm were used to solve the multi-condition optimization problems of the blade pattern. Based on the above method, the blade pattern of a hydraulic turbine was optimized and improved. The results show that the efficiency of the optimized hydraulic turbine specified in three conditions is increased by 3.91%, 3.59% and 3.09%, respectively, ensuring the constraints of the head are not less than initial head of the hydraulic turbine. This proves that using the above method to optimize the blade pattern is feasible.
Aerodynamic performance and losses mechanism of radial turbine intake components
SUN Guan-ke, LI Wen, ZHANG Xue-hui, ZHU Yang-li, CHEN Hai-sheng, TAN Chun-qing
2015, 30(8): 1926-1935. doi: 10.13224/j.cnki.jasp.2015.08.016
Abstract:
Using 2-D (two-dimensional) flow analysis methods, the rectangular cross-section scroll for a radial turbine was designed. A commercial computational fluid dynamics software CFX was used to caculate the flow losses within the radial turbine with the scroll. Then, the numerical caculation result was compared with that of the radial turbine with chamber. The results show that the loss within the scroll is less than that in chamber. The flow in the radial turbine with scroll is better than that of the turbine with chamber. The radial turbine with scroll has a higher efficiency than the radial turbine with chamber. The power of the radial turbine will increase by 1.7% when using the rectangular cross-section scroll. The inner flow field and losses mechanism is revealed by analyzing the flow field, in order to provide some reference for further development of radial turbine.
Influence on compressor characteristic of inlet swirl flow distortion
ZHOU You-tian, LI Jun, LI Cheng-long, LIU Dong-jian, LI Jing
2015, 30(8): 1936-1943. doi: 10.13224/j.cnki.jasp.2015.08.017
Abstract:
To investigate the influence of inlet swirl flow distortion on compressor characteristic, a swirl flow producer was installed onto a single-stage axial compressor test bench. By using swirl flow producer to produce swirl flow distortions with different directions of rotation and different intensities, the inflences of swirl flow distortions on compressor characteristic and stability were analyzed.Results show that, the bulk co-swirl flow distortion can reduce the pressurized ability but increase stability margin of compressor under some swirl flow distortion intensities, bulk counter-swirl flow distortion has a small influence o pressurized ability but obvious influence on stability of compressor, by contrast. Twin swirl flow distortion has a small influence o pressurized ability,which can be ignored,but has some influence on stability of compressor.
Tip clearance flow structures in ultra-highly load turbine cascades and effects of clearance height
YI Xiao-lan, ZHANG Hua-liang, SU He, GAO Qing, CHEN Hai-sheng, TAN Chun-qing
2015, 30(8): 1944-1949. doi: 10.13224/j.cnki.jasp.2015.08.018
Abstract:
Numerical simulation was performed to investigate the tip clearance flow structures in ultra-highly load turbine cascades. Flow details of leakage vortex, tip separation vortex and upper passage vortex were analyzed, then on this basis,the effects of clearance height on flow characteristics and blade loads were analyzed. Results show that, there are several forms of flow separation in tip clearance region of ultra-highly load turbine cascades,leakage flow is very strong, which not only affects the formation and development of upper passage vortex directly and makes passage vortexes move to blade root, but also causes some of leakage flow to enter into the lower passage vortex. As clearance height increases, tip separation vortex and leakage vortex get stronger, blade load especially tip load decreases.
Dynamic characteristic analysis of rotor-blade-casing system with rub-impact fault
MA Hui, WU Zhi-yuan, TAI Xing-yu, WEN Bang-chun
2015, 30(8): 1950-1957. doi: 10.13224/j.cnki.jasp.2015.08.019
Abstract:
Taking a rotor-blade-casing coupling system as the research object, finite element model of the rotor-blade-casing coupling system was established by ANSYS software, and then the validity of the model was verified by the natural frequencies obtained from experimental measurement. A point-point contact element was used to simulate the fixed-position rubbing fault between the blade and the casing, and further the validity and feasibility of the method adopted were also verified by the testing response data. Finally, the influences of different penetrations at a certain rotate speed, the constant penetration at different rotate speeds and the constant clearance at different rotate speeds on system vibration responses were analyzed. The results show that rubbing on the tip of blade mainly excites high multiple frequency components, and the amplitude of the multiple frequencies near the pitching rigid model increases. Under the constant penetration at different rotating speeds, the frequency components of the system is reduced at high speed rubbing conditions, and the normal rubbing force also changes with the increase of rotating speed. Under the constant clearance at different rotating speeds, the amplitudes of some multiple-frequency components are greater than those of rotating frequency when the rubbing appears at high speed, and repeatedly collision rebound can be observed during continuous rubbing.
Dynamic analysis of the robust test data on rolling bearing vibration based on chaos theory
XU Yong-zhi, XIA Xin-tao, NAN Xiang
2015, 30(8): 1958-1966. doi: 10.13224/j.cnki.jasp.2015.08.020
Abstract:
The improved Huber M method which fuse to two robust processings of median and Huber M method was proposed to solve the robust processing of data. The similarity of the median and average value was given to judge whether the variation data exist, the variation rate were determined by trend of the variation rate. Within the variation rate range of 0%-10%, the continuity and credibility of the rolling bearing vibration data increase with the increasing of the variation rate. The dynamic characteristics of rolling bearings were analyzed by using chaos theory. Time delay, embedding dimension and the maximum Lyapunov index of vibration data are the same on the same batch of rolling bearing. And the maximum Lyapunov index which is bigger than 0, show that the dynamic characteristic on rolling bearing vibration belongs to chaos characteristics, moreover the maximum forecast cycle are calculated, namely 667 unit. The nonlinear and monotonicity of the median of physical space and estimated correlation dimension of phase space on rolling bearing vibration time series is the inner running mechanism on rolling bearing vibration, which provide reliable basis for further analysis.
Stay bolt assembly tightness identification method for dismountable disk-and-drum rotor of aero-engine
ZHANG Xiao-li, WANG Bao-jian, CHEN Xue-feng, CHENG Li, CHEN Wei
2015, 30(8): 1967-1974. doi: 10.13224/j.cnki.jasp.2015.08.021
Abstract:
Aiming at a major factor affecting dismountable disk-and-drum rotor vibration characteristic of an aero-engine by stay bolt assembly tightness along the circumferential wheel disks, a stay bolt assembly tightness identification method was proposed. By means of vibration excitation test for dismountable disk-and-drum rotor, relative energy feature was extracted from lifting wavelet package decomposition reconstruction signal and a definition of stay bolt assembly tightness entropy was defined by mapping relative energy feature into stay bolt assembly tightness identification space. Three assembly tightness conditions of stay bolt from looseness to tightness were studied in test. The results showed that assembling tightness entropy had consistent monotone decrease rule. The assembly tightness of a dismountable disk-and-drum rotor of an aero-engine commissioned in field was tested and the assembly tightness of stay bolt was identified as degradation and looseness conditions.
Metering valve abrasion life prediction
LIU Jing, ZHU Liang, FENG Gang
2015, 30(8): 1975-1979. doi: 10.13224/j.cnki.jasp.2015.08.022
Abstract:
Given the complicated traditional abrasion computing process, the opposite direction to model the abrasion loss of the metering valve was studied. Three ways to compute the abrasion loss were found. The result of some model of the aero-engine fuel control unit's metering valve test data shows that, the model of the differential equation of first order based on the time series can accurately calculate the abrasion loss of the metering valve, with the relative error less than 5%. This had the practical meanings to the life prediction of abrasion in the fuel control unit metering valve, providing a basis for the useful life of the fuel control unit.
Reliability analysis for aircraft bearing with zero-failure data
GAO Pan-dong, SHEN Xue-jin, CHEN Xiao-yang, ZHANG Tao
2015, 30(8): 1980-1987. doi: 10.13224/j.cnki.jasp.2015.08.023
Abstract:
For the zero-failure conditions of the aircraft bearing that may occur during the process of reliability test, on the basis of analysis about distribution of the aircraft bearing life, the problem of the test groupings was firstly analyzed according to the hierarchical Bayesian method; it was found that when the number of groupings in 6-9 was chosen, the effects of evaluation were relatively better. And the longer life of aircraft bearing indicated less number of groupings. Second, based on the optimum groupings, by analyzing the hierarchical Bayesian method and E-Bayes method, it was proved that the estimation results of the two methods were similar, but from the point of comprehensive reliability, E-Bayes method was better by comparing the estimation results based on the zero-failure data from the simulation values by Monte Carlo. Finally, the selected values of parameter c of the super prior distribution were discussed. Through comparison analysis, the relatively appropriate parameter values suitable for the aircraft bearing were found, providing a theoretical guidance for the reliability analysis of zero-failure data. An enterprise case was given to verify the conclusion.
Effects of funnel-shaped mixer on thrust and infrared radiation characteristics of turbofan engine
LIU Jian, JI Hong-hu, LI Ning, YU Ming-fei
2015, 30(8): 1988-1996. doi: 10.13224/j.cnki.jasp.2015.08.024
Abstract:
The flow fields, thrust coefficient and infrared radiation characteristics of exhaust systems with funnel-shaped mixer were analyzed, and compared with annular mixer. The flow fields were calculated by Fluent commerical software, and the infrared radiation characteristics were calculated by by reverse Monte-Carlo method. Effects of funnel-shaped mixer on thrust coefficient and infrared characteristics of exhaust system were analyzed. The results show that: (1) When the funnel-shaped mixer is used, low temperature bypass stream is easy to eject into high temperature core stream, and the temperature distribution on cross section of exhaust system is similar to chrysanthemum. (2) When the funnel-shaped mixer is used, the infrared thrust coefficient of exhaust system decreases by 0.2%. (3) When the funnel-shaped mixer is used, the infrared radiation of plume decreases at all detection angles, down by 44.6% at detection angle of 90 degree, meanwhile the infrared radiation of wall increases little at large detection angles.
Comparison of two fuel-rich combustion schemes in air/kerosene gas generator
KANG Zhong-tao, LI Qing-lian, ZHANG Xin-qiao, CHENG Peng
2015, 30(8): 1997-2003. doi: 10.13224/j.cnki.jasp.2015.08.025
Abstract:
Two fuel-rich combustion schemes in air/kerosene gas generator were provided, and two gas generators with flame stabilized by bluff-body, swirling air and second air injection respectively were designed based on the fuel-rich combustion characteristics of air/kerosene. A series of hot fire experiments were conducted with two gas generators to compare the ignition and combustion characteristics of the two schemes. The results show that excess oxidizer coefficient is the most important working parameter in gas generator. With the increase of excess oxidizer coefficient, the states of gas generators vary from start failure to abnormal shut up, and finally to normal start. The range of stable working excess oxidizer coefficient in bluff-body stabilized gas generator is 0.518, and can be expanded to 0.237 by stabilizing flame through swirling air and second air injection, which greatly increases the working range of gas generator. The fuel-rich combustion efficiency of swirling air and second air injection stabilized gas generator is 20% higher than that of bluff-body stabilized gas generator. As the complexity of the two schemes is comparable, swirling air and second air injection stabilized gas generator could have a longer working time without cooling the flame holder.
Transient performance analysis of finger seal considering compressed fluid in the leakage gap effect
WANG Li-na, CHEN Guo-ding, SU Hua, LU Fei
2015, 30(8): 2004-2010. doi: 10.13224/j.cnki.jasp.2015.08.026
Abstract:
In order to solve the problem that the influence of compressed fluid in the leakage gap was neglected in previous work and the results compared with the practical test had poor consistency, the transient performance analysis model of finger seal (FS) considering compressed fluid in the leakage gap effect was proposed; and then the calculated results of FS performance were compared with those without having considered the effect of compressed fluid. The results indicate that it's necessary to consider the compressed fluid effect about the performance analysis of FS. The FS leakage rate with consideration of compressed fluid has a maximal increase of 234.7% compared with that neglecting the effect of compressed fluid. The compressed fluid makes the trend of FS leakage rate rise remarkably with the increasing rotor speed. In addition, the FS average contact pressure is decreased by compressed fluid, so the wear extent is lower.
Effects of interfacial contact area and streamwise vortices on pumping ratio of lobed mixer
YE Yu-chen, HUANG Yong, LIU Lei, WEI Fu-qing
2015, 30(8): 2011-2017. doi: 10.13224/j.cnki.jasp.2015.08.027
Abstract:
Numerical computations of the lobed mixer were conducted to study the effects of interfacial contact area and streamwise vortices on the pumping ratio of lobed mixer. The numerical results showed that the greater interfacial contact area of primary flow and second flow caused the better performance of the lobed mixer, and the pumping ratio grew linearly with the increase of lobe perimeter ratio. The same effects were found in streamwise vortices, but the pumping ratio grew sharply and then gently with the increase of non-dimensional streamwise vortices intensity; and an index relationship was found between them. In case no flow separation occurred, the streamwise vortices angular kinetic energy of nozzle outlet increased with the increase of lobe angle, and there was a parabolic relationship between them. Moreover, the increase of lobe diffusion angle not only can increase the vorticity of streamwise vortices, but also enlarge the streamwise vortices distribution area.
Parameter optimization design of air-ducted rocket for airborne missile
CAO Jun-wei, HE Guo-qiang, WANG Xi-liang, SHAN Rui-zi, HE Yong-jie
2015, 30(8): 2018-2024. doi: 10.13224/j.cnki.jasp.2015.08.028
Abstract:
To obtain high overall performance of airborne missile in a broad flight envelope,the method with overall performance of airborne missile as object of optimization and the design parameters of unchoked air-ducted rocket (ADR) as variables had been proposed. The integrated performance of the airborne missile at height of 5km, 10km and 15km was used as the objective function to establish the optimization model for ADR design. Genetic algorithms (GA) was introduced to obtain optimized ADR parameters. Numerical results show that reasonable performance can be achieved for the airborne airborne missile with unchoked ADR as the power system in a broad flight envelope. At the height of 5km, 10km and 15km, the corresponding airborne missile range are 62.9km, 89.2km and 133.1km. At the same time,the average flight velocity has been increased.
Supersonic non-equilibrium ionization magnetohydrodynamictechnical experimental system
FAN Hao, ZHANG Bai-ling, LI Yi-wen, YANG Peng-yu, GAO Ling, ZHANG Yi-ning
2015, 30(8): 2025-2032. doi: 10.13224/j.cnki.jasp.2015.08.029
Abstract:
Design methods and composition of supersonic non-equilibrium ionization magnetohydrodynamic (MHD) technical experimental system were introduced; the aspirated double-throat wind tunnel operated in Mach number 3.5 flow was designed and made. The large-scale, stable and uniform plasma was obtained continuously in supersonic flow through the capacitively coupled radio-frequency (CCRF) barrier discharge, in which the ceramic plate was taken as the barrier dielectric. Main conclusions are made as follows: the stable working time of the wind tunnel and the static pressure of experimental section are approximately 18s and 650Pa, respectively. Besides, when tunnel works in typical conditions of CCRF discharge, the conductivity of plasma is estimated to be 1.27×10-3S/m in supersonic air.
Research on processing method of grinding face gear with involute disc wheel
WANG Yan-zhong, HOU Liang-wei, LAN Zhou, ZHONG Yang, ZHAO Hong-pu, LÜ Qing-jun, ZHAO Xing-fu
2015, 30(8): 2033-2041. doi: 10.13224/j.cnki.jasp.2015.08.030
Abstract:
A method of face gear grinding by involute disc wheel was proposed for precision machining. Tooth surface equation of face gear with disc wheel grinding was derived in accordance with the surface forming process and grinding principles. A special CNC (computerized numerical controlled) machine was developed for face gear grinding, and the method was given for face gear grinding based on the structure of the machine, the tool path generation of meshing points was also calculated. Grinding process of face gear was simulated by VERICUT. Finally, the processing experiments of grinding were conducted, and the coordinate values of tooth surface points were detected, by which the maximum deviation of-10.1-12.1μm was obtained. The results verify that the processing method of face gear grinding with involute disc wheel is correct.
Research on life-extending optimization control in acceleration control of turbo-shaft engine
WANG Yun-zhi, CHENG Ben-lin, HUANG Xiang-hua
2015, 30(8): 2042-2048. doi: 10.13224/j.cnki.jasp.2015.08.031
Abstract:
In the acceleration control of turbo-shaft engine, life-extending control was designed by the acceleration schedule optimization by taking into consideration engine performance as well as life usage. Constraints such as aerodynamic stability margins, structural strength, combustion stability and power limitation were considered, sequence quadratic program (SQP) optimization algorithm was adopted to optimize the fuel flow of the acceleration schedule. Given that the major influential factors of engine life are the maximum temperature of the turbine first stage cooled stator and the maximum temperature difference between the airfoil and the endwall, two life-extending control methodologies were studied. The first methodology was used to modify the maximum temperature limitation to reduce the temperature of the first stage stator of turbine. The second methodology was performed by an optimization between turbine inlet temperature and shaft speed, and proper trade-offs were provided between them. Simulation of dynamic load process of a kind of turbo-shaft engine showed that both optimization methodologies can drastically reduce turbine stator temperature with minimum sacrifice in performance, then the optimized acceleration schedule can effectively prolong the life of engine.