2016 Vol. 31, No. 10

Display Method:
Review of the dry friction dampers in aero-engine and their design technologies
LI Lin, LIU Jiu-zhou, LI Chao
2016, 31(10): 2305-2317. doi: 10.13224/j.cnki.jasp.2016.10.001
Abstract:
Various typical dry friction dampers in aero-engine were summarized, and different typical dry friction models and contact kinematics models as well as their merit, demerit and range of application were introduced. Various computational methods to obtain the response of dry friction system were reviewed, and the multi-harmonic balance method combined with an alternating frequency-time domain method procedure was introduced in detail for particular interest. Furthemore, the key points of alternating frequency-time domain procedure, such as the arc-length continuation, were introduced. In the end, the difficulties and research directions in this research field were discussed.
Constitutive relation of metal-net rubber
ZOU Guang-ping, LIU Ze, CHANG Zhong-liang, LI Yu-lei
2016, 31(10): 2318-2324. doi: 10.13224/j.cnki.jasp.2016.10.002
Abstract:
Through analysis of the manufacturing process of the ring metal-net rubber and on the basis of the ring nesting model, in combination with nonlinear theory of dry friction and small curving beam model, the nonlinear constitutive relation of metal-net rubber was constructed, several metal-net rubber components of different relative density were taken on the compression experiment, and the experimental data were used to determine the coefficients on constitutive relation equation and compared with the experimental results. The results show that the model of the stiffness from nonlinear constitutive relation can correctly describe the nonlinear mechanical properties of metal-net rubber, and the theoretic calculations are consistent with the experimental data. The model can reflect the influences of the relative density, mesh size, mesh width and other such parameters, providing a theoretical basis for better design and application of metal-net rubber.
A creep model of nickel based single crystal superalloy at high temperature based on rafting mechanism
WANG Bai-zhi, FU Qiang, YU Hong-fei
2016, 31(10): 2325-2330. doi: 10.13224/j.cnki.jasp.2016.10.003
Abstract:
Mises stress method and interfacial energy method were used to predict the rafting type of nickel based single crystal superalloy in different orientations at 950℃. The rafting prediction results of above two methods were consistent. The rafting type is N-type in[001] orientation, P-type in[011] orientation and there is no rafting in[111] orientation. Based on the rafting type prediction results and crystal slip theory, a creep constitutive model of nickel based single crystal superalloy considering Kachanov-Robotnov (K-R) equation of damage evolution was introduced. This creep constitutive model was incorporated as a UMAT user defined subroutine in Abaqus and applied to description of the creep behaviors of CMSX-4 single crystal superalloy in[001],[011] and[111] orientations at 950℃,180~450MPa. This model could predict the rafting and slip type of nickel based single crystal superalloy and couple well with the creep deformation physical mechanism. Therefore, this model could simulate the second and third stages of creep curve of nickel based single crystal superalloy, as this has been verified by the experimental data.
Dual maximum entropy probability density function model and optimization
WU Fu-xian, WEN Wei-dong
2016, 31(10): 2331-2338. doi: 10.13224/j.cnki.jasp.2016.10.004
Abstract:
Based on high nonlinearity, hard convergence, low computational efficiency in the computational process by the classic maximum entropy probability density function model, a method called dual maximum entropy probability density function model+sequential updating method was proposed. Because of the unsteady optimization routine, a transformation formula of Lagrangian coefficient was rededuced. The probability density function and reliability of several common distributions and one complex distribution was calculated by classic and dual maximum entropy probability density function models. This shows that compared with classic maximum entropy probability density function model, the optimization function of dual maximum entropy probability density function model has advantages of low nonlinearity and simple form, the sequential updating method not only overcomes the sensitivity problem of initial value but exhibits high computational efficiency; dual maximum entropy probability density function model+sequential updating method has the highest computational accuracy, and can be well applied to the reliability problems of complex distribution.
Effect of low cycle fatigue loading on the crack tip plastic zone of high cycle fatigue crack
LIU Hua-wei, WANG Rong-qiao, HU Dian-yin
2016, 31(10): 2339-2345. doi: 10.13224/j.cnki.jasp.2016.10.005
Abstract:
To ascertain the loading interaction mechanism of the crack growth under high and low combined cycle fatigue loading, the elastic-plastic finite element numerical simulation method was used to determine the plastic zone of crack tip of the specimens with center crack under high and low combined cycle fatigue loading. It was proven that the unloading of low cycle fatigue loading contributed to the reduction of reversed plastic zone of crack tip corresponding to high cycle fatigue loading. This resulted in the decrease of crack closure level and the increase of crack growth rate, as well as the reduction of crack growth life under high and low combined cycle fatigue loading. The effects of the stress ratio of low cycle fatigue loading, the stress ratio of high cycle fatigue loading, the high cycle fatigue loading number per low cycle fatigue loading on the reversed plastic zone of crack tip were also investigated in contrast. The unloading of low cycle fatigue loading gradually increased along with the decrease of low cycle fatigue loading stress ratios, the increase of high cycle fatigue loading stress ratios, and the decrease of high cycle fatigue loading numbers per low cycle fatigue loading.
Dynamic characteristics of aero-engine pipe system considering fluid-structure coupling
LI Zhan-ying, WANG Jian-jun, QIU Ming-xing
2016, 31(10): 2346-2352. doi: 10.13224/j.cnki.jasp.2016.10.006
Abstract:
For analysis of dynamic characteristics of aero-engine pipe system, a fluid-structure coupling dynamic model using the user-defined three-dimensional (3D) pipe element was proposed based on the finite element method. The flexural fluid-structure coupling, axial and torsional dynamic behavior of the pipe was considered in the user-defined pipe element. The support was modeled using the nonlinear spring element. The user-defined pipe element was verified through comparisons with the measured data and analytical results. The natural frequencies and responses of a pipe system were calculated. The results show that the natural frequencies and the critical velocity decrease as the fluid pressure increases. And the effects of the nonlinear stiffness coefficient and the excitation amplitude on the pipe system under harmonic base excitation can be obtained.
Vibration fatigue crack growth life prediction of TC4 titanium alloy by considering the influence of crack shape
YANG Shuo, ZHANG Jun-hong, LIN Jie-wei, FU Xi, KOU Hai-jun
2016, 31(10): 2353-2358. doi: 10.13224/j.cnki.jasp.2016.10.007
Abstract:
Based on the tests about vibration fatigue crack growth of TC4 plate, the relationship between crack growth life and crack length was got. Using the ultra-depth microscope to observe and analyze the crack shape, the crack shape parameter was fitted. The fitted parameter was applied to calculate the stress intensity factor range and predict the crack growth life. Comparing the test results with prediction results, it showed that the crack shape parameter greatly influenced the predicting results. When the parameter was given a constant value, the error between the prediction and tested results was large. However, the fitted crack shape parameter can be used to predicted the crack growth life much more conveniently and accurately.
Buckling and post-buckling performance of aeronautic carbon fiber reinforced resin composite stiffened panel under compression
TAN Xiang-fei, HE Yu-ting, FENG Yu, ZHANG Hao-yu, AN Tao
2016, 31(10): 2359-2369. doi: 10.13224/j.cnki.jasp.2016.10.008
Abstract:
Compressive experiments on aero composite stiffened panel were conducted to study the carrying capacity, failure modes and post-buckling failure characterization. The results showed that the composite stiffened panel had a high post-buckling carrying capacity. The failure load was almost 2.2 times of the buckling load. The skin bay initiated buckling first. However, the stiffeners had no buckling before failure, which worked as ‘skin buckling separated’. According to the theoretical analysis, theoretical buckling and failure load had an error less than 8% compared with the experimental results. Additionally, the variation of the out-of-plane displacement on skin center and distribution of the axial compressive load were determined in the post-buckling process.
A damage constitutive model for needled CMCs composites and stress analysis of components
XUE Jian-gang, GAO Xi-guang, FANG Guang-wu, ZHANG Sheng, SONG Ying-dong, WANG Fang
2016, 31(10): 2370-2375. doi: 10.13224/j.cnki.jasp.2016.10.009
Abstract:
An anisotropic damage constitutive model for needled ceramic matrix composites was proposed based on continuum damage mechanics. The effects of both tensile damage and shear damage were considered in the model. The stress-strain curves of the material were obtained by tensile and shear tests and the parameters of the constitutive model obtained by curving-fitting. Then the model was written into commercial finite element software by user subroutine. Both calculated tensile and shear curves agreed with the test curves, and the maximum errors were 5.62% and 1.47% respectively. With both damage constitutive model and elastic model, an adjustment sheet of an aero-engine exhaust nozzle was calculated to analyze the mechanical response under complex aerodynamic load and temperature load. The stress distributions calculated by the two models were similar, but the value of damage constitutive model was obviously lower than that of the elastic model.
Investigation of secondary flows near the endwall region in a single-stage axial-flow compressor
WU Yan-hui, LIU Jun, AN Guang-yao, CHEN Zhi-yang, PENG Wen-hui
2016, 31(10): 2376-2386. doi: 10.13224/j.cnki.jasp.2016.10.010
Abstract:
To determine the key factors influencing the efficiency and stability of a subsonic axial flow compressor stage at off-design speed, experimental and numerical investigations were conducted to analyze the evolution of its secondary flow near the end-wall over a full stable operating range. The results show that a hub corner stall and a tip leakage flow dominate the endwall region of the rotor at a large mass flow condition. However, the full-span blade stall due to the over-diffusion inhibite the hub corner stall at peak efficiency and near stall flow conditions. The flow separation in the corner region of the casing of the stator blade is three-dimensional, but don't evolve into a hub corner stall even at the near stall flow condition. The leakage flow of the stator near hub could decrease and energize the cross-flow due to the overturning of the fluid near the casing, thus inhibiting or mitigating the hub corner stall. However, the control effect is influenced by different flow conditions of the compressor. At the near stall condition, a decrease in the stage efficiency mainly comes from the fact that the leakage flow has not enough capability for suppressing the hub corner stall, while the compressor stage stability is limited by the flow blockage arising from the secondary flow near the rotor tip.
Mechanisms of affecting the performance of axial-flow compressor with athwart blade-angle slots casing treatment
ZHANG Hao-guang, TAN Feng, CHU Wu-li, WU Yan-hui, KUANG Hai-yang
2016, 31(10): 2387-2394. doi: 10.13224/j.cnki.jasp.2016.10.011
Abstract:
Influences of athwart blade-angle slots casing treatment on the performance of subsonic axial-flow compressor were investigated with the experimental and unsteady numerical simulation methods. The experimental and unsteady numerical calculation results showed that the rotor gained about 30.1% stall margin improvement at the cost of decreasing about 12% peak isentropic efficiency of smooth wall casing with athwart blade-angle slots casing treatment. The detailed analysis of rotor blade tip flow-field indicated that the tip clearance leakage flow was improved with athwart blade-angle slots casing treatment and the blockage created by low energy clearance leakage flow in blade tip was removed in blade tip with smooth wall casing,so the stability of rotor was improved. It was found that the ability to improve rotor stability of slot was affected by the relative position of blade and slot, and moreover, back flow in slot and the interaction of injecting flow brought by slot and blade tip mainstream resulted in serious flow loss, leading to decline of the rotor isentropic efficiency. The numerical calculation results also showed that the stall margin improvement and the level of decreasing isentropic efficiency reduced about 10.4% and 64% respectively by making the athwart blade-angle slots casing treatment move forward about the 55% axial chord of blade tip.
Influence of up- and downstream blade rows on aeroelastic stability of compressor rotor blade
YANG Hui, SHEN Zhen, ZHENG Yun
2016, 31(10): 2395-2404. doi: 10.13224/j.cnki.jasp.2016.10.012
Abstract:
Aeroelastic stability analysis of compressor rotor blades, including up- and downstream blade rows interaction, was conducted by self-developed fluid-structure coupled simulation programs. Blade aerodynamic damping values under different vibration modes were calculated through the time trace of the blade vibration amplitude induced by the unsteady flow field, using a whole assembly aeroelastic model. And the influence of wakes and potential waves on the aerodynamic damping values was studied for different axial gaps. Interaction effects on the flutter characteristics of rotor-stator and inlet guide vane-rotor configurations were assessed by comparing the damping data with that of the single rotor. The results show that the aeroelastic stability is not changed monotonically with the axial gap value for the first bending modal. The results also illustrate that the intensified wake and potential wave effects could destabilize the first torsional modal, but stabilize the first bending-torsion coupled modal.
Modification of Spalart-Allmaras model with pressure gradientaiming for corner separation flow
MA Li, SUN Jin-jing, LU Li-peng
2016, 31(10): 2405-2414. doi: 10.13224/j.cnki.jasp.2016.10.013
Abstract:
For the problem in predicting the corner separation, the Spalart-Allmaras (S-A) model was modified by introducing a normalized pressure gradient into the production term of the eddy viscosity in the model equation. Through the calibration in two series of low-speed compressor cascade cases with corner separation, it was found that compared with the experimental results, the original S-A model got a stronger corner separation and lower wall pressure in the separation zone, while the modified model's results were closer to the experience in the size of the separation zone, the pressure coefficient on the suction and pressure sides, etc. The analysis on the production and dissipation terms of the eddy viscosity in S-A model indicates that the normalized pressure gradient introduced to the production term can recognize the separation zone effectively. It can also change the transportation of the eddy viscosity of the model and enhance the eddy viscosity in the corner separation, bringing about a smaller separation zone, while the prediction in the main flow area in the modified S-A model remains the same as the original S-A model. Thus a better prediction is got.
Effect of rim seal purge flow on performance and thermal loading of turbine
AN Yu-ge, LIU Huo-xing, ZOU Zheng-ping
2016, 31(10): 2415-2423. doi: 10.13224/j.cnki.jasp.2016.10.014
Abstract:
The effect of rim seal purge flow on flow field, performance and thermal loading for a two-stage turbine was studied by utilizing conjugate heat transfer. It was found that under the effect of purge flow and main flow interaction, a nonlinear relationship between cooling effect and coolant flow rate was observed. In this case, utilizing the conjugate heat transfer could observe the dramatical change in the temperature field and aerodynamic losses simultaneously. Moreover, the operation point shifted along performance map due to the blockage effect of coolant flow in the adjacent stage, a 2.5% coolant flow rate could result in a 0.6% variation of main flow rate and a 1.2% reduction of expansion ratio for upstream turbine stage. In the main passage, the coolant flow could reduce the aerodynamic loading at the root forming the viscous shear layer, and significantly modify the secondary vortex, eventually resulting in performance penalty.
Multi-objective optimization design of centrifugal compressor impeller based on BP artificial neural network
LUO Ming, ZUO Zhi-tao, LI Hong-yang, LI Wen, CHEN Hai-sheng
2016, 31(10): 2424-2431. doi: 10.13224/j.cnki.jasp.2016.10.015
Abstract:
The database of the centrifugal compressor impeller performance was given by Concept NREC software. The relationship of the impeller's main design parameters and performance was established by BP (back propagation) artificial neural network. Then the optimal array of main design parameters was acquired by the multi-objective genetic algorithm. This design method was used to satisfy Krain impeller's performance objective; the optimized impeller's efficiency and pressure ratio increased by 1.4% and 10.9%, respectively. Through discussion of artificial neural network model's reliability, multi-objective optimization model's principal component analysis and the impellers' CFD numerical simulation verification, the validity of objective functions and Pareto optimal solutions was proved, the effectiveness of the present centrifugal compressor design method was well confirmed.
Numerical simulation of flow transition in microchannel
YUAN Xing, TAO Zhi, LI Hai-wang
2016, 31(10): 2432-2436. doi: 10.13224/j.cnki.jasp.2016.10.016
Abstract:
Numerical simulation was conducted with CFD software ANSYS CFX to investigate the characteristics of gas flow in a rectangular microchannel with a hydraulic diameter of 0.4mm. Three flow models, namely, γ-Reθt model, laminar model and shear stress transport (SST) model, were taken in the simulation. The simulation results were compared with the experimental data. Results indicate that laminar model and SST model are incapable of predicting transition. γ-Reθt model forecasts the critical Reynolds number well and the relative errors of friction factor keep under 20%. Before Reynolds number reaches the critical value, local turbulent regions appear at the rear of the microchannel and the regions expand with the growing Reynolds number. The streamwise position where the inlet and the rear turbulent regions meet is almost identical with the position where the skin friction reaches its minimum value.
Effects of radiation on the coupled heat transfer in a high temperature tube filled with porous media
CHEN Xue, LI Yang, XIA Xin-lin, SUN Chuang
2016, 31(10): 2437-2442. doi: 10.13224/j.cnki.jasp.2016.10.017
Abstract:
The effects of radiation from solid matrix on the temperature distribution and heat transfer were numerically investigated by simulating the coupled heat transfer in a tube filled with porous media. The energy equations of fluid and solid phases were built with the local thermal non-equilibrium model. Monte Carlo method was used to solve the radiative heat transfer of solid matrix. The temperature discrepancy and effects of wall emissivity and structure parameters of porous media were analyzed without radiation. The results show that radiation strongly affects the temperature of the entrance region and a substantial discrepancy occurs when the radiation is neglected. The maximum deviation is 16% at the wall temperature of 1500K. The effect of wall emissivity on the temperature is small, which is less than 3% at the wall temperature of 1500K. In addition, when the porosity is high and pore diameter increases, the ratio of wall radiative heat flux increases and the effects of radiation become obvious.
Experiment of effect of nozzle shapes on the performance of rotating detonation engine
GAO Jian, MA Hu, PEI Chen-xi, WU Xiao-song, XU Can
2016, 31(10): 2443-2453. doi: 10.13224/j.cnki.jasp.2016.10.018
Abstract:
In order to study the effect of different nozzles on the performance of rotating detonation engine(RDE), a thrust test bed of RDE was designed. The inside and outside diameters of RDE combustor were 70mm and 80mm, respectively. The length of the combustor was 40mm. H2 and air were used as fuel and oxidant respectively. The fuel and oxidizer were separately supplied through arrays of orifices and slot, respectively with impinging jets to promote the mixing. The RDE was ignited by the high-energy spark plugs and the thrust was measured with a piezoelectric force sensor. In these experiments, the working performance of the engine with converging nozzle, diverging nozzle and the Laval nozzle was studied. The results show that: within RDE stability work scope, the converging nozzle is better than others in improving thrust performance when inlet mass flow rate is less than 0.126kg/s. Detonation wave velocity and the thrust performance of RDE increases with the increase of inlet mass flow rate. Detonation wave velocity and thrust of RDE all reach maximum when equivalence ratio reaches an optimal value. Specific impulse of RDE based on the mixture can reach 95.21s.
Numerical simulation of film-cooling for the adjustable nozzle of the tandem TBCC
ZHAO Lin, XU Jing-lei, QIU Yun, ZHAO Lei, GUO Xiao-shun
2016, 31(10): 2454-2463. doi: 10.13224/j.cnki.jasp.2016.10.019
Abstract:
In view of the problem that the higher inlet total temperature of tandem TBCC nozzle can reduce the ablation of the wall material, a film-cooling scheme adapted to different flight Mach numbers in the flight envelope was presented, showing a significant effect on the thermal protection of the nozzle. The cooling effect for different flight Mach numbers based on the CFD method was calculated. The research indicates that there will be a more noticeable change of the flow field conditions nearby the rhomboid slots than annular slots. After film-cooling, the temperature of nozzle has a 1000K's decline than before. The film-cooling adiabatic efficiency of the downstream wall centerline can reach to 0.9 at most flight Mach numbers. The downstream wall temperature of the slot is mainly distributed symmetrically along the span of the nozzle, and the temperature uniformity gradually declines with x's increment.
Numerical investigation on atomization characteristics of liquid jet in crossflow
WANG Ya-jun, YAN Ying-wen, DANG Long-fei, LI Jing-hua
2016, 31(10): 2464-2471. doi: 10.13224/j.cnki.jasp.2016.10.020
Abstract:
In order to investigate the atomization process of a liquid jet injected into a crossflow, the Euler-Euler method in Fluent was used by numerical simulation. The VOF (volume of fluid) model coupled with level-set method was applied to simulate two-phase flow, and the numerical results showed the atomization process of liquid jet in crossflow and the flow field. The effects of flow fields on atomization process of a jet liquid column were studied. Breakup point and liquid jet penetration depth were gained and also compared with the experimental data. The numerical results show that:(1) The coupled level-set and VOF model can be used to simulate the atomization processes of liquid jet injected into crossflow.(2) Because of the counter-rotating vortex, the liquid film and the droplets are transported along the development direction (y), playing a promoting role for secondary atomization. (3) The jet liquid column is always broken at about 8 times the diameter of the injector, and the location of the broken point is determined by the geometrical characteristics of the injector.
Energy supply platform design of wireless power transmission based on intensive sunlight
TIAN Shao-ping, LI Yun-ze, LIU Jia, ZHONG Ming-liang, ZHANG Hong-sheng
2016, 31(10): 2472-2478. doi: 10.13224/j.cnki.jasp.2016.10.021
Abstract:
An energy supply platform was designed to meet the needs of rapid development of micro-satellites formation flying technology. In this configuration, Fresnel lens (solar energy gathering device) collected space sunlight and coupled the focusing light into fiber bundles (flexible steering device); then a lens group composed of three thin lens (secondary emission device) collimated the intensive sunlight for energy transmission, powering formation flying wirelessly in the form of intensive sunlight. The power collection and transmitting efficiency of the platform was up to 70%, and the qualitative evaluation of the application, the advantages and disadvantages of the platform has finally been conducted.
Self-start characteristics test of 2-D hypersonic inlet
NAN Xiang-jun, ZHANG Meng-zheng
2016, 31(10): 2479-2484. doi: 10.13224/j.cnki.jasp.2016.10.022
Abstract:
In order to study the self-start characteristics of 2-D hypersonic inlet, a mixed compression 2-D inlet with swept side wall was tested in a wind tunnel at free stream Mach number 4 and 3.5. The start, unstart and self-start phenomenona were obtained with back pressure simulation system. Results showed that the inlet alllowed for self-start at Mach number 4 and 3.5, rather than at Mach number 3.5 with 2 degree angle of attack. With the inlet unstart by high back pressure, separated bubble and separated shock appeared on top wall near the bottom of side wall, and spillage was induced. After analysis of the phenomena and data from test, it indicated the inlet's unstart behavior was soft, and different from classic self-start theory. But the test data showed that the self-start Mach number was lower than the value from classic self-start thoery slightly. When the Mach number of internal compression part was below 2.5, its self-start Mach number could be approximately estimated by classic self-start theory.
New constitutive relation for eddy viscosity models
JIANG Li-jun, GAO Ge
2016, 31(10): 2485-2492. doi: 10.13224/j.cnki.jasp.2016.10.023
Abstract:
A new turbulent constitutive relation was directly derived from Boussinesq's hypothesis and mixing length theory, and then implemented in the standard k-ε model. The performance of this constitutive relation was validated in zero pressure gradient flat-plate boundary layer flow, fully-developed turbulent channel flow and separated flow in a plane asymmetric diffuser. The investigation demonstrated that, this new constitutive relation gave very accurate results in the former two basic cases and provided significant improvement in prediction of separated and reattachment points in the plane asymmetric diffuser. Separation and reattachment points at x/H=7.5 and 29 were calculated accurately in comparison to experimental results, and the static pressure coefficient of 0.82 was very close to large eddy simulation calculation. These results are very encouraging but further verification and extensive application of the new constitutive relation to other two-equation eddy viscosity model are needed.
Calculating single static and dynamic derivatives of aircraft with step response method
MI Bai-gang, ZHAN Hao, CHEN Sen-lin, RAO Dan
2016, 31(10): 2493-2499. doi: 10.13224/j.cnki.jasp.2016.10.024
Abstract:
Based on step response method and rigid moving mesh techniques, the fine single static and dynamic derivatives of aircraft were simulated. Longitudinal derivatives were taken as examples to represent these methods. Firstly a constant additional angle of attack was applied on the aircraft, and the unsteady aerodynamic force was calculated during the step response process, then the static derivative can be identified from the derivation of aerodynamic force; similar to static derivative, a constant pitching angular velocity was used to force the aircraft pitching around the reference point, and also a translate speed should be considered at the same time to eliminate the effect of additional angle of attack generated from the pitching angular velocity. NACA0012 airfoil and SACCON fly wing unmanned combat aerial vehicle were used to test the methods, both the static and dynamic derivatives of the two configurations agreed well with the reference and wind tunnel test results,with the maximum error no more than 5%. The research shows that the computational time of direct single static and dynamic derivatives simulation methods based on step response is nearly 21% of the of traditional oscillation method, with relatively higher effectiveness; this can be used in analysis of lateral and directional derivatives as well as longitudinal ones, providing technical reference for aircraft stability.
Subcritical instability of Stokes layer induced by wall surface roughness
KONG Wei, LUO Ji-sheng
2016, 31(10): 2500-2506. doi: 10.13224/j.cnki.jasp.2016.10.025
Abstract:
The subcritical instability problem of a finite Stokes layer over two-dimensional wall surface roughness was investigated by numerical simulations. Results indicated that infinitesimal height of roughness led to a quite large deviation of the response curves from the linear cases. With the increasing height of wall roughness, the evolution of the disturbance at one order spectrum displayed the sub-harmonic component, and then the evolution entered into the irregular state, indicating the subcritical instability. According to the correlation between the height of roughness and the disturbance at one order spectrum evolution, the critical height of roughness was defined, and the relation curve was given as a result. Results shows that the critical height of roughness becomes smaller as the Reynolds number increases. At the Reynolds number around 300, the height of roughness of just the level of micrometer would be able to trigger the subcritical instability and transition in Stokes layer. That is why transition often occurs in experimental observations at Reynolds number around 300.
Aerothermodynamic analysis of spacecraftduring its atmospheric reentry flight
LUO Zu-fen, SONG Bao-yin
2016, 31(10): 2507-2514. doi: 10.13224/j.cnki.jasp.2016.10.026
Abstract:
Based on existing OREX (orbital reentry experiment vehicle) flight experiment data and the CFD numerical results, the OREX reentry trajectory and heat flux at the stagnation point under thermal non-equilibrium and equilibrium conditions were analyzed respectively with heat transfer theory and corresponding formulas. The calculation results of the trajectory and the temperature as well as the heat flux at the stagnation point under the thermal non-equilibrium condition agreed well with the experiment data and CFD numerical results,including that the corresponding calculation method might be used in the thermal analysis of spacecraft's stagnation point. However under the equilibrium condition, although the calculated heat flux at the stagnation point showed little difference to the former CFD numerical results, the calculated temperature under this condition didn't match the experiment data, which should be attributed to the insensitivity of the heat flux to the variation of the temperature at the stagnation point. The comparison of calculations under thermal non-equilibrium and equilibrium conditions shows that merely focusing on heat flux of spacecrafts in its reentry flight is risky, paying attention to its temperature might be more important.
Streak artifacts correction of solid rocket motor's CT image
LU Hong-yi, CHEN Qing-gui, ZHOU Hong-mei, ZHAO Ru-yan, ZHANG Zong-wei, YU Zhou
2016, 31(10): 2515-2521. doi: 10.13224/j.cnki.jasp.2016.10.027
Abstract:
To correct streak artifacts in the computed tomography (CT) image of solid rocket motor (SRM), scanned by narrow fan-beam industrial CT (ICT), the reason for the streak artifacts was analyzed. Considering the streak artifacts were caused by the inconsistency of projection data of SRM after rebinning and data shake-up processes, two algorithms for the correction of streak artifacts were proposed. The two algorithms used the projection data in the half of the translation steps as the reference for the rebinning of projection data. For one algorithm, rebinning process and data shake-up process were considered as two processes. For the other, rebinning and data shake-up processes were considered as one process. To prove the effectiveness of the two algorithms, one SRM was scanned by narrow fan-beam ICT with three different scanning step sizes and SRM CT images were reconstructed by the two algorithms. Results show that the algorithm using rebinning and data shake-up as two processes performs well only if the scanning step size is small, and there are few streak artifacts in this situation. The other algorithm using rebinning and data shake-up as one process performs well and generates few streak artifacts in the situations of three different step sizes.
Experiment on dynamic fracture initiation toughness of CMDB propellant based on Hopkinson technology
ZHENG Jian, WANG Wen-qiang, CHEN Xiong, ZHOU Chang-sheng, XU Jin-sheng
2016, 31(10): 2522-2529. doi: 10.13224/j.cnki.jasp.2016.10.028
Abstract:
To obtain the dynamic fracture initiation toughness of composite modified double-base (CMDB) propellant, impact experiments of notched semi-circular bend (NSCB) specimens were performed by Hopkinson experimental technology. Pulse shaping technology was applied to obtain the load-displacement curve of CMDB propellant. The modified compliance changing rate method was used to determine the crack initiation point of the NSCB specimen. Finite element software ABAQUS was adopted to calculate the dimensionless structure factor of the NSCB specimen, and the dynamic fracture initiation toughness of the CMDB propellant was determined. The scanning electron microscope imaging technique was used to investigate the fracture micro-mechanisms of the NSCB specimen. Research results show that the dynamic fracture initiation toughness is dependent on the loading rate sensitivity significantly within the range of 5.41×105~8.94×105MPa·m1/2·s-1. With the increase of the loading rate sensitivity, the failure morphology of the particles in the cross section is gradually deteriorated, and the energy consumption is increased through the analysis of the scanning electron microscope.
Structural mechanics analysis and optimization design of thrust chamber
LI Yi, SUN Bing, FANG Jie
2016, 31(10): 2530-2535. doi: 10.13224/j.cnki.jasp.2016.10.029
Abstract:
A parameterized model of a liquid rocket engine thrust chamber was established. Natural frequencies and vibration modes of structure were obtained by finite element method, and verified by modal experiment. Computer numerical design of experiments was conducted by optimal Latin hypercube design in order to get sensitivity of design variables for structural mass and first order natural frequency, which had a guiding significance for the process of optimal design. Multi-objective optimization was carried out using NSGA-Ⅱ algorithm, and the optimal structural parameters were obtained, satisfying both static and dynamic requirements. The mass decrease of the optimal design was 9.1%, meanwhile the first order natural frequency increase was 22.6%. The results show that the proposed method improves the mechanical property of thrust chamber effectively.
Dynamic strain monitoring technique for the rim of cylinder gear in the aero-engine
JIANG Ping, LI Gang, CHEN Qing-lan, XIAO Xin-hong, LEI Dun-cai, HUANG Xiang-yang, CHEN Da-li, RAO Gang
2016, 31(10): 2536-2543. doi: 10.13224/j.cnki.jasp.2016.10.030
Abstract:

The dynamic strain monitoring technique for the rim of cylinder gear was studied based on the principle of dynamic stress measurement for high speed rotor structure. The dynamic stress data of the gear was measured by using the test system designed specifically for the accessory gearbox in a certain aero engine. The analysis results showed that the gear had one order and three order vibration modes based on actual conditions, and the maximum frequency amplitude was 21MPa. The dynamic stress of the rim of cylinder gear with improved design was decreased by 43.8% compared with that before improvement.

Fluid-structure interaction investigation on the flow field and mechanical characteristic in brush seals with bristle deflections
SUN Dan, LIU Ning-ning, HU Guang-yang, AI Yan-ting, WANG Ke-ming
2016, 31(10): 2544-2553. doi: 10.13224/j.cnki.jasp.2016.10.031
Abstract:
Bristle deflections have important influence on the flow field characteristic and mechanical characteristic. The problems of the leakage, hysteresis and bristle fracture produced by the deflections of bristle are very prominent. The flow field characteristic and dynamic characteristic in brush seal were predicted using a three-dimensional computational model with consideration of bristle deflections depending on two-way fluid-structure interaction and moving grids techniques. Firstly, based on the cantilever beam theory, the mechanics model of bristle was analyzed. Secondly, based on the fluid solid coupling method verified with the theoretical model and experimental results, the flow field characteristic, the law of bristle deflections, the mechanical characteristic and hysteresis characteristic were predicted. The research results show that the bristle deflections caused by forward flow impact is oscillating gradually, and the maximum stress of the bristle root is also oscillating gradually depending on the bristle deflections. Bristle deflections increase the clearance between the bristle and the rotor surface, which leads to the increases of leakage; as the bristle row number increases, the leakage decreases rapidly, then decreases slowly, and finally tends to be a stable value. The increase of the axial clearance between the last row bristle and the back plate makes the relative pressure coefficient decrease, and the axial clearance can effectively reduce the hysteresis characteristic.
Fault detection for liquid-propellant rocket engine based on improved inductive monitoring system
GAO Ke-han, ZHANG Su-ming, WANG Xiao-lin, AN Xue-yan
2016, 31(10): 2554-2560. doi: 10.13224/j.cnki.jasp.2016.10.032
Abstract:
The problem of high false alarm rate when inductive monitoring stystem (IMS) was applied to monitor the system during trials or flights was analyzed, and an improved IMS method was proposed. The improved algorithm processed outliers that may occur during the test, reducing interference evoked by outliers of test data. The experiment was conducted by taking the trial data of a certain type of liquid-propellant rocket engine as an example. Simulation was performed and the result verified that the original IMS had a high false alarm rate, yet the improved IMS can decrease false alarm rate from 37.5% to 0 while ensuring timeliness, reliability and accuracy of fault detection.