2017 Vol. 31, No. 5

Research Review
Study on three dimensional laser-induced fluorescence (3DLIF) techniques and its instrument
Huang Zhenli, Zhou Weihu, Qu Zhaosong
2017, 31(5): 1-14. doi: 10.11729/syltlx20160173
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Abstract:
This paper introduces the principle of the LIF technique to measure the water concentration, temperature and velocity fields, summarizes the LIF technology development from 1D to 3D, reviews the key issues of LIF to measure the scalar field in water, including laser and light-sheet sources, fluorescence material selections and calibration methods, and finally reviews various correction methods of PLIF and 3DLIF. Based on the 3DLIF techniques, this paper proposes an overall technical scheme, technical route and overall technical indicators of 3DLIF instrument, and then provides solutions of 3DLIF key techniques to meet the demand of engineering and industrialization.
Fundamental Research and Application
Experimental and simulation study of aeroengine combustor based on CARS technology and UFPV approach
Xiong Moyou, Le Jialing, Huang Yuan, Song Wenyan, Yang Shunhua, Zheng Zhonghua
2017, 31(5): 15-23. doi: 10.11729/syltlx20170090
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Abstract:
Based on the Unsteady Reynolds Averaged Navier Stokes URANS) method, a three-dimensional two-phase turbulent combustion numerical software for aeroengine combustor has been developed. The physical and chemical processes taking place in the liquid fuel are simulated completely, including liquid film formation, breakup, evaporation and combustion. LISA and KH-RT are used as the primary and second atomization model respectively, and also the standard evaporation model is used to simulate the evaporation process. Besides, detailed chemical mechanism of kerosene is used for reaction kinetics, and the Unsteady Flamelet/Progress Variable (UFPV) approach in which the unstable combustion characteristics of the flame could be simulated is used as the combustion model. The temperature and species of the flow field and the diameter of fuel droplets in the aeroengine combustor are obtained. At the same time, the Coherent Anti-stokes Raman Scattering (CARS) technology is used to measure the temperature in the primary zone of the aeroengine combustor. Then the temperature of the simulation is compared with that measured by CARS technology, and the calculation error of numerical results is less than 7.3%. The studies have shown that the numerical method in this paper and UFPV approach can simulate the two-phase turbulent combustion process appropriately in the aeroengine combustor.
Experimental and numerical study on spray atomization in a double-swirler combustor
Liu Richao, Le Jialing, Chen Liujun, Yang Shunhua, Song Wenyan
2017, 31(5): 24-31, 45. doi: 10.11729/syltlx20170093
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Abstract:
Using the particle field pulsed laser holography imaging technique, the spatial distribution of droplet diameter in an aeroengine combustor is measured, the atomization process is studied, and the spatial distribution of droplets diameter in the combustor is obtained too. The numerical sprays models of the primary and secondary atomization are established, and a numerical software for the three-dimensional two-phase combustion in the aeroengine combustor is developed. Based on the LISA atomization model and KH-RT breakup model, the primary atomization process and secondary atomization process in the combustor are simulated numerically, obtaining the distribution of fuel spray droplets in the combustor. The simulation results are compared with experiments. The result indicate that the atomization models developed in this work can properly simulate the whole process of spray atomization under the conditions of high temperature, high pressure and strong swirling in aeroengine combustors.
Formation of confined free film in the window on a vertical perforated plate
Xie Hanguang, Hu Jianguang, Wang Cheng, Dai Gance
2017, 31(5): 32-38. doi: 10.11729/syltlx20160197
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Abstract:
Liquid film is a common contact way between gas/liquid and can be divided into wall-bounded film and free film according to the film formation process and the number of free surfaces. When a plate is perforated, both kinds of films exist. This paper describes some experimental observations of free-surface flows arising when a thin liquid film flows through the window on a vertical perforated plate. Dozens of rectangular windows (9~1152mm2) and six fluids (Ka from 52 to 3000) were used to investigate the flow mechanisms. Several typical flow patterns including pass-around flow, pass-through flow, bias flow and back-side flow are well defined under such a flow condition. Here a special focus is given to the window region, where various free-surface flow patterns composed of droplets, columns, sheets and their combinations were observed with increasing flow rate. Meantime, free film in the window is surface tension dominated and susceptible to disturbance, resulting in coalescence or break of liquid columns and films. At a critical flow rate, liquid film is able to full fill the window, forming a stable complete confined free film. Mutual influence between confined free film in the window region and wall-bounded film around shows special wavy trains, which is also called "twin liquid film". Based on experimental data and scaling analysis, an empirical equation which relates Reynolds number Re, Kapitza number Ka and a dimensionless length Nx is proposed to characterize the film formation conditions. It is found that critical film formation Reynolds number increases with Kapitz number and window size. And hysteresis phenomenon is manifested by obviously different flow transition Re for confined free film formation and breaking. The results can help window geometry optimization industrial processes to improve local heat and mass transfer. It can also enrich the traditional film flow investigations.
Experimental investigation on the aerodynamics of tunnel-passing for high speed train with a moving model rig
Song Junhao, Guo Dilong, Yang Guowei, Yang Qiansuo
2017, 31(5): 39-45. doi: 10.11729/syltlx20170002
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Abstract:
When a high speed train enters a tunnel, a compressed wave occurs and propagates along the tunnel to the tunnel port, and transforms to be a micro pressure wave. Using the moving model rig experiment system, pressure waves and the micro pressure wave were measured in the double-track tunnel (60m in length) within the speed range of 200-350km/h. Firstly, the validity of experimental data was verified. Secondly, the reduction principle of the initial compression wave propagating in the tunnel and the relationship between the micro pressure wave and the train speed were drawn out. The effect of the streamlined nose shape on the micro pressure wave was studied at last. The experimental results show that in the speed ranges, the dimensionless values of the pressure wave and micro pressure wave are the same with different speeds. However, the relationship between the micro pressure wave and the streamlined nose length is only analyzed qualitatively, with quantitative relationship difficult to determine.
Propeller slipstream effect on longitudinal aerodynamic characteristics of airplane
Li Xingwei, Li Cong, Gao Jing, Li Shengwen
2017, 31(5): 46-52, 87. doi: 10.11729/syltlx20160185
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Abstract:
Using the dynamic simulation and PIV test technology for propeller aircraft, research on the propeller slipstream effect on the longitudinal aerodynamic characteristics of the conventional layout twin-engined turboprop aircraft is conducted. Wind tunnel test is used to study the slipstream effect on longitudinal characteristics as the propeller position changes, such as the aircraft lift and drag characteristics, moment characteristics and horizontal tail downwash. PIV test is used to setting out typical section of aircraft components, mainly focus on the position conformed by slipstream wind tunnel test. Slipstream has bad effect especially on lift and drag characteristics when the propeller position sinkage. Both extending the propeller position forward and changing the propeller installation angle can improve the aerodynamic characteristics of the aircraft, while the aircraft lift characteristic is improved obviously especially around the stall angle when the propeller position extends forward.
Experimental study on drag-reduction mechanisms based on the physical characteristic of tip vortex
Huang Wentao, Xiang Yang, Wang Xiao, Liu Hong, Gu Dingyi
2017, 31(5): 53-59. doi: 10.11729/syltlx20160194
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Abstract:
The drag-reduction mechanisms based on the physical characteristic of the tip vortex are investigated through experiments in the wind tunnel. Through 3DPIV (3D Particle Image Velocimetry) experiments, the physical characteristic of tip vortex is obtained, and the induced drag of wing is calculated based on the aerodynamic force measurement setup of wingtip proposed in this paper. Experimental results show that the non-dimensional circulation of the tip vortex increases with the increasing angle of attack and the wind speed. Meanwhile, with the decrease of the non-dimension circulation of the tip vortex or the increase of the spacing between the wing and the tip vortex, the induced drag becomes smaller and smaller. Specifically, the induced drag reduction can be achieved by inhibiting the non-dimensional intensity of the tip vortex, which weakens the interaction between the main wing and the tip vortex.
Effects of balance holes diameter on cavitation characteristics of centrifugal pump under low flow rates
Zhao Weiguo, Lu Weiqiang, Liu Zailun
2017, 31(5): 60-66. doi: 10.11729/syltlx20170067
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Abstract:
In order to investigate the cavitation characteristics of low specific speed centrifugal pumps under low flow rates, rotation rate reduction IS80-50-315 centrifugal pump is taken as the experimental object, and a device is especially designed so as to replace the balance holes of different diameters. Cavitation characteristics were measured and analyzed at 0.4Qd, 0.5Qd, 0.6Qd, and 0.8Qd when the balance hole diameter is equal to 4, 6, 8, and 11mm. The results show that with the increase of the balance hole diameter, the pump head and its efficiency reduce. Both the torque-drop and head-drop curves of impellers with different balance hole diameters have the same shape of dropping and the torque-drop has obvious creeping change, with the corresponding break-down points occurring asynchronously under the low flow rate condition. It is caused by the rotor-stator interaction between the volute and the impeller. When the balance hole diameter increases under the same cavitation number condition, the head coefficient increase, the axial forces acting on impellers decrease and the anti-cavitation characteristics of centrifugal pump are enhanced. The slower the flow with the same balance hole diameter is, the harder the cavitation of centrifugal pump becomes. But the descent speed of the fluid pressure in the pump chamber of the centrifugal pump increases first and then decreases, the axial forces acting on impellers tend to flat and then increase sharply with the development of cavitation. In order to suppress cavitation and decrease the axial thrust, it is proposed that the most appropriate balance hole diameter is in the range of 6mm to 8mm.
Numerical simulation and experimental study on aerodynamics of the micro coaxial rotors
Lei Yao, Ji Yuxia, Wang Changwei
2017, 31(5): 67-73. doi: 10.11729/syltlx20160193
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Abstract:
In order to study the effect of rotor spacing on the aerodynamic performance of small-scale coaxial rotor in hover, a platform is designed to test the aerodynamic characteristics of the coaxial rotor system with different rotor spacing ratios h/r of 0.32, 0.38, 0.45, 0.51, 0.58, 0.65 and 0.75. Rotor thrust and power obtained from measurement with different rotary speeds are used to estimate the aerodynamic characteristics of the rotor system. In the meantime, the uncertainty of the thrust coefficient, power coefficient and power loading (PL), and the calculated errors are all less than 2%. Distributions of streamline and pressure with different rotor spacing ratios are obtained from numerical simulation to analyze the interference between top and bottom rotors. Finally, in comparison with test results, the aerodynamic configuration is optimized with the rotor spacing ratio of 0.38. The results prove that the performance of coaxial rotor in hover can be improved with proper rotor spacing. With certain rotor spacing, aerodynamic performance at higher rotational speed is more prominent when the interference between the rotors is beneficial for the aerodynamics, and greater power loading is obtained at lower rotational speed with smaller interference.
Application of a smart material structure in the study of aerodynamic characteristics of a morphing wing
Lei Pengxuan, Wang Yuanjing, Lyu Binbin, Yu Li, Yang Zhenhua
2017, 31(5): 74-80. doi: 10.11729/syltlx20160166
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Abstract:
In order to verify the feasibility and deformation capability of the intelligent material structure in the study on aerodynamic characteristics of the flexible variable trailing edge wing, the videogrammetric model deformation technique is used to measure the deflection of the trailing edge in the transonic wind tunnel, and the dynamic process of deflection is recorded. The pressure distribution on the upper wing surface is also measured. The Mach number is between 0.4 and 0.8, and the model's angle of attack is between 0° and 6°. The influence of flow condition on the structure deformation is analyzed. The test result shows that the flexible structure of the model can bear the aerodynamic load of the transonic flow and achieve the deflection. When the driving force is constant, the deformation is influenced by the Mach number and the angle of attack. The increase of Mach number weakens the deformation ability of the intelligent structure, which leads to the decrease of the deformation speed and the decrease of the trailing edge deflection angle. The influence of the angle of attack is more complex, and couples with the influence of the Mach number. The higher the Mach number, the stronger the influence of attack angle. Finally, through the analysis of the pressure distribution, it is concluded that the flow separation is the key factor to influence the deformation capacity of the intelligent material structure.
Measuring Technique
A fast method of extracting the laser light bar's centerline in the ice model
Kang Hanyu, Liu Guihua, Wang Bin, Niu Qian
2017, 31(5): 81-87. doi: 10.11729/syltlx20170058
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Abstract:
The laser centerline extraction is an important step in the measurement of the ice cross sectional profile, and the extraction accuracy directly affects the accuracy of the measurement system. Especially the ice on the structural light transmission is serious, the center line extraction algorithm is put forward a higher requirement. A fast centerline extraction method based on frequency domain transform is proposed to extract the center line in the three-dimensional measurement of ice. First, the image is subjected to noise reduction based on the technique of Block-matching and 3D filtering. Second, in order to reduce the computational complexity, the visual significance of the image is calculated by using the quaternion Fourier transform of phase spectrum, and then extract the optical band's region. Third, obtain the gradient map and convert to the frequency domain space, according to the image spectrum characteristics, we can obtain the center line position. The experimental results show that the algorithm is 28.57FPS, and the accuracy of ice contour reconstruction is 0.017mm.
Experimental Equipment and Method
Design and application of digital valve in gas supply control system for wind tunnel
Kang Hongming, Huo Guo, Chen Fuzheng, Liu Xiaolin
2017, 31(5): 88-92. doi: 10.11729/syltlx20160086
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Abstract:
As the required indicators of air supply experiments in the wind tunnel become more rigorous, the analog control valve is unable to meet the demands. Considering the drawback of PCM digital valve and PWM digital valve, the PCM+PWM digital valve is put forward to meet the gas supply requirements, where the PWM digital valve regulates the flow under the benchmark which is provided by the PCM digital valve. The research status and design index of the digital valve, the selection and design of the nozzle, the distribution of the throat area, the calculation and selection of the magnetic valve, and the flow control method based on PID are introduced in detail. By repeated debugging, parameters optimizing and performance testing, several gas supply experiments are conducted. Experimental results show that the application of the digital valve is successful, the measuring accuracy of the mass flow control is superior to ±3g/s, and the characteristics of fast response, large range, and high reliability are achieved to provide strong support for gas supply experiments.