2018 Vol. 33, No. 2

Display Method:
Dynamic response of the aeroengine flexible rotor system under the bladeoff
2018, 33(2): 257-255. doi: 10.13224/j.cnki.jasp.2018.02.001
Abstract:
To reveal the dynamic response characteristics of the rotor under the bladeoff, the dynamic model of the flexible cantilever rotor system was established, by considering the distribution characteristics of the stiffness and mass, the load transfer, as well as the rotor/stator coupling of the low pressure rotor in turbofan engine. The dynamic response characteristics of the rotor system under sudden unbalance excitation and continuous rubimpact constraint were analyzed. The results showed that, the established rotor dynamic model can effectively reflect the rotor vibration under the bladeoff and the complex harmonic vibration response characteristics. The transient response of the rotor under the sudden unbalance excitation was aggravated, and the impact response characteristics were showed. The critical speed of rotor increased under the continuous rubimpact, while the amplitude of response decreased, and the frequency components and rotor vibration were inclined to be complex.
Analysis of powder alloy disks low cycle fatigue life with surface machining status
2018, 33(2): 265-272. doi: 10.13224/j.cnki.jasp.2018.02.002
Abstract:
The influence of surface machining status on fatigue characteristic was investigated. Based on MansonCoffin formula, a low cycle fatigue life analysis method considering surface machining status was presented. The low cycle fatigue life of FGH96 Powder alloy disk was analyzed considering surface machining status or not. The results showed that the influence on fatigue life was 30-40 percent when considering surface machining status.The low cycle fatigue life test on FGH96 Powder alloy disk was finished. Test results indicate that the forecasting life dispersion is big without considering surface machining status, and the dispersion is small with consideration of surface machining status.
Analysis on thermalstructure coupling for graphite circumferential seal
2018, 33(2): 273-281. doi: 10.13224/j.cnki.jasp.2018.02.003
Abstract:
The mechanical load and temperature load on the graphite circumferential seal ring were considered comprehensively, and the software ANSYS was utilized to complete the structure analysis, steadythermal analysis and thermalstructure coupling analysis of graphite circumferential seal ring. Results showed that stress distribution was uniform on the main sealing surface of graphite circumferential seal ring, the maximum equivalent stress appeared in lapping area of joints, becasue the structural characteristics of joints made gas unbalanced force higher in the lapping area of joints. The stress distribution was nonuniform on the auxiliary sealing surface because of the action of the load torque, and affected the sealing performance. Temperature field distribution was uniform, and the main sealing surface temperature was higher than the temperature on auxiliary sealing surface, and temperature had a significant rise in the lapping area of joints due to large contact area. Thermal effect should not be ignored for the properties of graphite circumferential seal. The value of stress had a tenfold rise in consideration of the thermal effect, and made the largest stress area move from edge to the center.
Experiment of random unbalance on vibration characteristics of highspeed double overhung rotor with oil bearing
2018, 33(2): 282-289. doi: 10.13224/j.cnki.jasp.2018.02.004
Abstract:
The rotor dynamic model of rotor supported with cylindrical slide bearings was built, and the relations between unbalance excitation and vibration were taken. The vibration characteristics influence of unbalance with typical amplitude, axial location, and phase difference on the double overhung disks was investigated by the ways of runup and constant speeds, and the running speed was up to the second order critical speed. Results showed that the first order vibration was sensitive to the unbalance on right disk and the second order sensitive to left disk. The inphase unbalance can excite more harmonic frequency than outphase unbalance, and suppress 12 subfrequency. A proper amount of unbalance can cause special phenomenon of highfrequency resonance band as the vibration amplitude exceeded the allowable error compensation value of coupling.
Simulated test and numerical simulation of aeroengine whole engine response during blade out event
2018, 33(2): 290-298. doi: 10.13224/j.cnki.jasp.2018.02.005
Abstract:
Blade off test rig was designed according to the structures of typical big bypass ratio turbofan engine structure. A series of simulated blade off tests and numerical simulation using the explicit finite element method were carried out to investigate the whole engine response and load transmitting path. It was found that the released blade impacted the casing with its tip and body respectively, whilst two crests existed in the acceleration curves. The amplitude of acceleration increased with the blade release speed. The rotor unbalance load transmitted from the front bearing, to medium bearing, intermediate supporting plate, and finally the casing. The impact load caused by the released blade transmitted backward from the fan casing, and finally to the mounting structure. The impact load played the major role in engine load due to blade out event with respect to rotor unbalance load. The investigation can provide the modeling testing approach and numerical analysis tool for the study of whole engine response of aeroengine under blade out event condition.
Measurement error of noncontact rotor vibration displacement measurement system
2018, 33(2): 299-304. doi: 10.13224/j.cnki.jasp.2018.02.006
Abstract:
The measurement error of the noncontact rotor blade displacement measurement system (NRDMS) was assessed based on blade tiptiming. The displacements were obtained from the NRDMS using simulation signal of the blade vibration, and the influences of the number rotor blade, rotation speed and the timebase on the measurement deviation were researched. Theoretical and observed displacement analysis showed that, it was possible to detect measurement error due to the timebase and rotation, with the maximum quoted error of NRDMS up to 0.066%.
A small sample testability verification test scheme based onsequential and regression analysis
2018, 33(2): 305-312. doi: 10.13224/j.cnki.jasp.2018.02.007
Abstract:
A scheme based on sequential and regression analysis was presented in order to solve the problems in testability verification test schemes which might be difficult to meet the requirement of confidence level for testability evaluation while the sample size was small. First, a hypothesis of feasibility of sequential and regression analysis for the success or failure type test was presented and proved. Then, an improvement in sequential mesh test was achieved by the utilization of regression prediction estimation. Finally, the estimation of testability index satisfying the requirement of high confidence level under the condition of small sample size could be realized. Case study shows that this scheme can meet the requirement of bilateral risk and confidence level for testability evaluation, which requires smaller sample size in testability verification test. In the test of this case, the sample size could be decreased by 223% on average, and by 85% at utmost.
Structural optimization design of turbine blade with specialshroud
2018, 33(2): 313-319. doi: 10.13224/j.cnki.jasp.2018.02.008
Abstract:
Based on the structural design of specialshroud of lowpressure turbine blade, the optimization design method of specialshroud was explored. In order to achieve the purpose of weight reduction, specialshroud structure preliminary design program was put forward on the basis of the zigzag shroud. The model parameterized design was achieved using the platform of UG NX. By the sensitivity analysis of specialshroud structure parameters, the double objective optimization design process of specialshroud was established. It successfully achieved the goals of lightest mass and shroud centroid position optimal regulation under the precondition of ensuring its strength and stiffness by this procedure. The optimization result showed that the mass of shroud was reduced by 53.05%, the maximum stress decreased by 43.41%, and the maximum radial deformation decreased by 45.80%.
Trajectory design of launchingplane transforming orbitinjection of spacecraft based on engine twice ignition
2018, 33(2): 320-326. doi: 10.13224/j.cnki.jasp.2018.02.009
Abstract:
In order to solve the velocity deviation of orbitinjection question in space launch by the geographical location of launching site, the trajectory of zero velocity deviation orbit injection based on engine twice ignition and Launchingplane transforming for the liquid launch vehicle was designed. According to the characteristics of the Launchingplane transforming trajectory, the twice ignition and Launchingplane transforming flight program model for the secondstage was established in different sequences to simplify the control program of the engine, and the constraints of the trajectory were analysed to establish the trajectory optimization model. Then, the trajectory was simulated according to the optimization model. Results indicated that the orbitinjection position deviation of the spacecraft was 0391m and the velocity deviation was 1277m/s, and the velocity deviation was 737844m/s less than the optimum result of the fixed launchingplane orbitinjection trajectory, meeting the requirement of the zero velocity deviation orbit injection.
Development of liquid nitrogen injection cooling system of NF-6 wind tunnel
2018, 33(2): 327-337. doi: 10.13224/j.cnki.jasp.2018.02.010
Abstract:
The way of raising the Reynolds number in the NF6 pressurized continuous transonic wind tunnel was described by lowering the test gas total temperature. The wind tunnel pioneered the use of the cooling manner of injecting liquid nitrogen into the wind tunnel circuit, and achieved successful low total temperature operating at -20℃. The design indexes, overall scheme, NF6 wind tunnel liquid nitrogen injection cooling system components and debugging of the liquid nitrogen injection cooling system were discussed, paving the way for the design and construction of subsequent wind tunnels of the same kind in China.
Thrust performance optimization calculation and analysis of triple bypass variable cycle engine
2018, 33(2): 338-344. doi: 10.13224/j.cnki.jasp.2018.02.011
Abstract:
Based on the commercial software Isight, a steadystate performance optimization method was proposed for a triple bypass variable cycle engine, and the optimization design platform was built. In this way, the function of the steadystate performance procedures was expanded, especially in the parameter study and optimization. Utilizing the platform, performance optimization of the typical engine working points was conducted, and the results were compared with the traditional method. With the help of the platform, the engine steadystate performance in different working conditions and various modes was analysed. The study results show that the Isight based optimization design platform could obviously improve the design efficiency and optimization precision, and fully exert performance advantage of triple bypass variable cycle engine. For getting the maximal thrust in any conditions, the best order of the mode selection is as follows as the inlet temperature raises: the first is singlebypass adding thirdbypass mode, the second is singlebypass mode, the third is triple bypass mode and the last is doublebypass mode.
Unsteady numerical simulation of propeller slipstream based on unstructured chimera grid
2018, 33(2): 345-354. doi: 10.13224/j.cnki.jasp.2018.02.012
Abstract:
Numerical simulations of unsteady Reynolds averaged Navier-Stokes (URANS) equations were conducted for isolated-propeller and turboprops configurations based on anisotropic unstructured chimera grids. Walls criterion was used in the automatic hole-cutting procedure. Distance weight interpolation and tri-linear interpolation were developed to transmit variable value. The computation grids contained rotational subzone of propeller and stationary subzone of aircraft. The boundaries of chimera grids were optimized for fixed axis rotation. The equations were solved by dual-time method and lower upper-symmetric Gauss-Seidel (LU-SGS). The method and grid technology were validated by isolated-propeller and the computation results were compared with experimental data, showing good agreement with each other. Then turboprops configuration was simulated and the aerodynamic characteristics of aircraft with or without slipstream were compared. The effect of slipstream was analyzed by surface pressure and pressure distribution of sections. The results indicated that the slipstream increased drag and pitching moment coefficient. Slipstream affected the pressure distributions of wing and flat-tail, causing the airflow downwash.
General static aeroelasticity analysis method based on CFD/CSM coupling
2018, 33(2): 355-363. doi: 10.13224/j.cnki.jasp.2018.02.013
Abstract:
A fluid-structural interpolate points selection method suitable for finite element refined modeling was proposed. RBF (radial basis function) method was applied for the data exchange between fluid-structural coupling surface. And then a nonlinear computational static aeroelastic approach based on CFD/CSM (computational fluid dynamics/computational structural mechanics) coupling method was developed. A HIRENASD (high Reynolds number aero-structural dynamics) wind-tunnel model was investigated. The good agreement of the structural deformation and surface aerodynamic pressure distribution between numerical results and experiment data validated the accuracy of the CFD/CSM solver developed. The static aeroelastic characteristics and elastic deformation effects of HIRENASD model in high AOA (angle of attack) were studied. Result showed that, the lift of HIRENASD elastic model was less than the rigid model; in small AOA region, the lift difference between rigid and elastic model linearly increased with the increase of AOA. When the AOA was greater than 4 degree, the difference decreased with AOA increase firstly, then the difference remained unchanged with the AOA increase, showing a complicated nonlinear relationship.
Numerical investigation for control of shock wave and boundary layer interactions flow separation with plasma actuation
2018, 33(2): 364-371. doi: 10.13224/j.cnki.jasp.2018.02.014
Abstract:
A method of low-power and multi-pulse jet actuation was proposed to solve the problem of control of shock wave and boundary layer interactions flow separation in hypersonic inlet, and based on the Reynolds averaging Navier-Stokes(N-S) equations, the plasma actuation was simplified to power density source term in terms of phenomenology. A comparative study for control effect and mechanism of actuation of steady and unsteady low-power and multi-pulse plasma actuation was carried out. Results showed that, the energy deposition of steady actuation was effective for control of shock wave, and could induce an oblique shock wave, however, the energy deposition was strong to worsen the flow separation, and could not satisfy the need for control; for the unsteady low-power and multi-pulse actuation, there were optimum actuation duration and frequency at different power densities; when the power density was 5.0×109(W/m3), the maximum of jet velocity could reach 895m/s, which could alleviate the shock wave and boundary layer interactions flow separation to some extent.
Characteristic of shock wave/boundary layer interactions induced by bumps with different shock wave system arrangements
2018, 33(2): 372-382. doi: 10.13224/j.cnki.jasp.2018.02.015
Abstract:
In order to analyze the flow field characteristics of conical shock wave/boundary layer interactions induced by bumps with different shock wave system arrangements, three different bump compression surfaces were designed from the single cone, bipyramid and isentropic cone basic flow fields, respectively, by using the streamline tracing method. And such three basic flow fields had the same total deflection angle with the free stream Mach number 2.0. With the help of the numerical method, the three-dimensional shock wave/boundary layer interactions flow fields of such three bumps at different Mach numbers were compared. The results show that compared with single cone bump, the vorticity concentration regions in the flow fields of the bipyramid and isentropic bumps decrease evidently, the same with the vorticity values in the vortex core. Due to the interference of subsequent compression wave system, the flow patterns of the bipyramid and isentropic bumps dont perform in the quasiconical similarity manner. Besides, the bipyramid and isentropic bumps have the same level of ability with the single cone bump in diverting the boundary layer, and such ability keeps invariant with the change of the free stream Mach number. Furthermore, the multi-wave system arrangement can improve the total pressure recovery coefficient of the bump external compression system. And the total pressure recovery coefficient will go higher with the increase of the wave number, particularly at high Mach number.
Individual cylinder imbalance analysis of two-stroke engine
2018, 33(2): 383-391. doi: 10.13224/j.cnki.jasp.2018.02.016
Abstract:
Targeting individual cylinder imbalance problem of two-stroke aircraft engine, the reasons of individual cylinder imbalance were analyzed by experiment combined with simulation, the engine Gamma technologies-power (GT-Power) one-dimensional simulation model was built, and the individual cylinder imbalance of different operating conditions was simulated and analyzed by cylinders pressure. The engine bench test was conducted, the two cylinders pressure and air-fuel ratio were analyzed comparatively, showing that the reasons of individual cylinder imbalance were inlet and fuel injection difference of cylinders, the main influential factor of small load was fuel injection difference, and the main influential factor of partial load was air inlet difference subjecting to decrease with the increase of throttle position. This has provided a theoretical basis for the realization of software and hardware of individual cylinder imbalance control.
Effects of bypass ratio on the matching performance between core driven fan stage and high pressure compressor
2018, 33(2): 392-401. doi: 10.13224/j.cnki.jasp.2018.02.017
Abstract:
A prediction equation and the related prediction program were developed according to the aerodynamic matching between core driven fan stage(CDFS) and high pressure compressor (HPC). Through the experimental data of CDFS and HPC, typical matching bypass ratio prediction and characteristic analysis were carried out. The effect of bypass ratio change on the matching performance and their respectively working conditions were discussed. The four following conclusions were drawn: (1) The right bypass ratio should be set to ensure the normal operation of CDFS, HPC and their matching. (2) With the increase of bypass ratio, CDFSs working condition moves from the near stall point to the near choke point, and HPC does in the opposite way. As the working range of CDFS is smaller than that of HPC, the matching massflow-total pressure ratio performance curve is very steep. (3) There exists an optimum bypass ratio that the matching can have the maximum stall margin, total pressure ratio at the near stall condition and the peak efficiency. (4) With the increase of rotating speed, typical matching bypass ratio decreases. Flow through the bypass at 85% corrected rotating speed reaches the maximum, so the bypass flow capacity cannot be designed without the design parameter of the matching between CDFS and HPC.
Effect of pitchwise position of inlet swirl on aerodynamic characteristics of high-pressure turbine IGV
2018, 33(2): 402-310. doi: 10.13224/j.cnki.jasp.2018.02.018
Abstract:
In order to reveal the impact mechanism of pitchwise position of inlet swirl on the aerodynamic characteristics of downstream IGV(inlet guide vane), the interaction mechanism between upstream inlet swirl and secondary flow in the channel with swirl in different pitchwise positions was analyzed and simulated by computational fluid dynamics method. The details of secondary flow, vortex system structure and entropy increase were discussed respectively for three typical position cases. Results indicated that viscous dissipation and the interaction of swirl and secondary flow led to the majority of aerodynamics loss. The maximum passage loss appeared when the inlet swirl was located towards the pressure-side near the head of IGV, instead of the accurate IGV head. Moreover, the interaction of swirl and passage vortex could induce a shed vortex around the trailing-edge if the intensity of inlet swirl was up to a certain extent.
Numerical investigation on unsteady characteristics oftip leakage vortex of transonic compressor rotor
2018, 33(2): 411-421. doi: 10.13224/j.cnki.jasp.2018.02.019
Abstract:
In order to study the unsteady characteristics of tip leakage vortex in a single compressor rotor system,a series of unsteady simulations of Rotor 67 were carried out at different back pressures and rotating speeds. The results showed that there was an unsteadiness boundary for each characteristic curve, which was divided into two parts, steady and unsteady. When the rotor operated at unsteady part, the increase of back pressure led to the decrease of frequency of tip leakage vortex. This was attributable to the decrease of tip blade loading near leading edge, finally bringing about the decrease of driving power of tip leakage vortex inception. The frequency of tip leakage vortex was related to the rotating speed of rotor. When the rotating speed was high, the tip leakage vortex showed lower frequency. When the rotating speed was low, the tip leakage vortex showed higher frequency. This was attributable to the detached degree of detached shock wave which was related to the rotating speed, leading to the differences of excitation positions where shock wave stimulated tip leakage vortex. At any rotating speed, there was a strong regularity of circumferential velocity of pressure wave induced by tip leakage vortex. With the decrease of massflow factor, the wave velocity decreased. And the decreasing rates were almost the same at any rotating speeds. In addition, the initial points of unsteadiness at every rotating speed almost stood in a straight line.
Circumferential mode characteristic of rotating instability and its decomposition method of compressor
2018, 33(2): 431-439. doi: 10.13224/j.cnki.jasp.2018.02.021
Abstract:
Unsteady pressure fluctuations near tip region in an axial compressor were studied using experimental and numerical methods. A circumferential mode decomposition method based on spatial Fourier transform was used to deal with the circumferential pressure data. Spectrum analysis of experimental and numerical results was performed, proving the existence of circumferential modes which can be continuously numbered. The temporal evolution of these circumferential modes were resolved, showing a stable circumferential propagating structure near tip region of the dominate mode of rotating instability, and the other mode components presented a more fluctuating characteristic. Besides, a prediction method for circumferential modes of higher orders was given using two sets of measuring points to deal with the aliasing effect. The method improved the upper bound of the mode number that can be analyzed for several times, and much fewer sensors would be required when applying it to experimental measurements.
Management, verification standards and validation process of aviation biofuel
2018, 33(2): 440-447. doi: 10.13224/j.cnki.jasp.2018.02.022
Abstract:

For establishing the self-certification process of non-petroleum based aviation fuel, the specification ASTM D4054 and ASTM D7566 issued to guarantee the utilization of aviation biofuel by foreign airworthiness authorities were introduced.“Civil Aviation Jet Fuel Containing Synthesized Hydrocarbons”(CTSO-2C701) was issued, which defined the process and minimum standards of alternative fuels by reference to the compliance certification method. Accordingly, the Chinese airworthiness authorities took Chinese Technical Standard Order Approval (CTSOA) to approve the use of alternative aviation fuel. For obtaining the approval, the physical and chemical properties and fit-for-purpose properties test shall be certificated after completion of engine bench test and flight test. Compared with the aviation fuel management, certification standard and process at home and abroad, the certification technology and the requirements of engine bench test and flight test in China were summerised, and Sinopec No.1 biofuel certification based on this verification technology were highlighted in detail. The novel management processes for aviation biofuel and other alternative fuels provided technical support for special approval in China.

Flow and heat transfer mechanism of film cooling influenced by “jet phenomenon” in film hole
2018, 33(2): 448-455. doi: 10.13224/j.cnki.jasp.2018.02.023
Abstract:
In order to reveal the flow and heat transfer mechanism of film cooling influenced by “jet phenomenon” in film hole, seven cooling air ducts with different inlet angles were chosen to conduct a comparative study with different blowing ratios, and induce the “injection phenomenon” in film cooling hole under the conditions of the same injection angle. Results showed that the “injection phenomenon” in film cooling hole only occurred at different inlet angles when the inlet angle was not equal to 0°. At low blowing ratio, obvious influence on adiabatic cooling effectiveness wasn't observed with different inlet angles. With the increase of blowing ratio, the cooling effectiveness was different when the inlet angles were different. When the blowing ratio was 1.5 and the inlet angle was not more than 0°, strong kidney vortex was formed outside the film cooling hole, causing a low cooling effectiveness; when the inlet angle was more than 0°, the coolant in this region interacted with high temperature mainstream, and the cooling air in the low momentum region of upstream could bypasses the large downstream jet momentum coolant to attach cooling surface. This increased the distance between the vortexes to weaken mutually reinforcing effect. Compared with the original cooling air duct, when the inlet angles were 15° and 30°, the average adiabatic film cooling effectiveness was increased by 130% and 70% when the blowing ratio was 1.5.
Minimum ignition energy of n-heptane/air mixtures and its affecting factors
2018, 33(2): 456-462. doi: 10.13224/j.cnki.jasp.2018.02.024
Abstract:
The minimum ignition energy (MIE) at different conditions of n-heptane/air mixtures can be obtained by the experimentation in constant volume combustion bomb. The experimental results showed that:MIE decreased and then increased with the increase of equivalence ratio. When the equivalence ratio was 1.1,MIE reached the minimum value. At the condition of the initial pressure 0.1MPa and initial temperature 450K,MIE was 0.3904mJ. Initial pressure and initial temperature of premixed gas had a major influence on MIE, and their effect was consistent with the effect on flame propagation speed. The impact of initial temperature and initial pressure on flame propagation speed and MIE is related to the chemical reaction rate of mixture, the faster reaction rate means the greater flame propagation speed and smaller the MIE.
Semi-empirical prediction on spray characteristics of dual-orifice atomizers
2018, 33(2): 463-469. doi: 10.13224/j.cnki.jasp.2018.02.025
Abstract:
With the purpose of giving an insight into the interaction between inner sheet and outer sheet, and obtaining the predictive tools of the dual-orifice atomizers, the spray characteristics of the dual-orifice atomizers were investigated with experimental and theoretical analysis. The range of fuel injection pressure difference was covered within 0.05-3MPa. Semi-empirical predictive correlations were obtained to predict the spray characteristics, including breakup length and Sauter mean diameter (SMD). The predicted results were validated with the experiment results from three dual-orifice atomizers with different geometry parameters, and the uncertainty of the breakup length and SMD semi-empirical correlation was ±20%. These semi-empirical correlations can be employed in the dual-orifice atomizer design stage as predictive tools and boundary conditions in simulation.
Numerical simulation on a type of the integrated afterburner
2018, 33(2): 470-476. doi: 10.13224/j.cnki.jasp.2018.02.026
Abstract:
To meet with the design requirement of the new-generation aero-engine having high thrust-mass ratio, a type of integrated afterburner was designed to replace the traditional combination of flame holder with a composite structure containing truncated strut and splitter lip with cavity. Numerical simulation and test research were conducted. The results show that the integrated afterburner has three low-speed recirculation zone in the inner channel; the truncated strut is not only a guide vane, but also a flame holder; the combustion efficiency of the integrated afterburner is 90%-93%, the flow drag coefficient is about 0.26; all of the total pressure recovery coefficient in the research are higher than 0.975, the main total pressure loss is concentrated in truncated strut and cavity of splitter lip.
Dynamic property of spindle bearing considering the effect of thermal deformation
2018, 33(2): 477-486. doi: 10.13224/j.cnki.jasp.2018.02.027
Abstract:
A lot of heat will be produced inside an angular-contact ball bearing under high speed conditions, and high temperature rise will cause thermal deformation, leading to the changes of geometric position relationship of bearing internal channel curvature center and ball bearing center. Finally, the bearing dynamic state, in turn, will be affected. On the basis of the analysis of the bearing quasi-statics theory, the heat production caused by the bearing internal friction and the thermal deformation of bearing components were considered. Using thermal network, the spindle unit was divided into network nodes, and the node hot impedance was defined, thereafter, the steady state thermal network model was established. The thermal deformation of bearing components, caused by each node temperature rising under different working speeds and loads, was analyzed. The coupling relationship model between the bearing dynamic properties and thermal properties was established, and the bearing internal dynamic properties were analyzed. The results showed that considering the thermal deformation or not, the bearing contact load and contact angle with the change of bearing working speed and the load were significantly different. Under the condition of high speed, the bearing internal thermal deformation has a significant impact on bearing dynamic properties, becoming one of the main causes of bearing faults during normal use.
Analysis of cages stability in a cylindrical roller bearing with elastic support
2018, 33(2): 487-496. doi: 10.13224/j.cnki.jasp.2018.02.028
Abstract:
Based on the roller bearing dynamics and structural theory, the dynamic model of a cylindrical roller bearing with flexible outer ring and groove elastic support was established. And then, the impact of working condition and structural parameters of elastic support on the stability of bearing cage was investigated theoretically. The findings are as following: (1) Compared with the rigid support, elastic support can effectively improve the cages stability. When the bearing is on elastic support with less number of groove and thinner of arc beam, the cage motion is more stable characterized by regular phase plot, lower vibration and slip ratio. (2) Cages stability is sensitive to the load and rotation speed. Under the larger load and low speed of revolution, cage of the bearing with elastic support shows more stability. Otherwise, under the lighter load and higher rotation speed, cage of the bearing with elastic support shows more unstability.
Numerical investigations of water-spray cooling effect on test stands deflector based on DPMA
2018, 33(2): 497-507. doi: 10.13224/j.cnki.jasp.2018.02.029
Abstract:
Numerical investigations of a large launch vehicles stage test were conducted by computational fluid dynamics(CFD) technique. The uni-step hydrogen-oxygen(H-O) reaction model and standard k- turbulence model were employed to obtain the flow field, and discrete phase model(DPM) was used to simulate the water-spray system of test stand. Subsequently, the design parameters of a test stand were studied and compared. Results showed that DPM could simulate the water-spray system effectively, both of the noise suppressor system and water cooling system could improve the heat circumstance of flame-deflector, offering an enhanced effect when working together. The similar enhanced effect would be offered with the increase of the depth of deflector or the amount of water.
Performance of very low-power nitrogen arcjet thruster
2018, 33(2): 508-512. doi: 10.13224/j.cnki.jasp.2018.02.030
Abstract:
Very low-power arcjet thrusters with natural-radiation-cooled nozzle can stably operate for a long period of time by using nitrogen as the propellant. Thrust was measured indirectly using impinging force method, the end-on photos of discharge status within the nozzle were taken through a 45° inclined copper mirror. Performance and discharge characteristics of the very low-power arcjet thruster were analyzed according to the experimental data of thrust, specific impulse, thrust efficiency, arc voltage and arc current. Results showed that the maximum thrust was up to 24mN and the maximum specific impulse was close to 175s, when the gas flow rate was within the range of 100-700mL/min and input power of 35-55W; with the increase of arc current from 80-120mA, the arc voltage varied from 420-520V, and the arc voltage showed the rising trend after falling with the increase of gas flow rate.