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学者姓名：席光
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Abstract ：
本文试图通过神经网络重构二维低雷诺数翼型绕流非定常流场.首先通过局部径向基函数(LRBF)求解器求解不可压缩流动控制方程得到计算域内流场信息,然后随机选取一些时空域内的数据点(包含位置信息和速度信息)作为训练数据代入神经网络进行训练.先学习训练得到流动的雷诺数后进行流场的重构,并与LRBF求解器得到的数值结果进行对比.流动计算中雷诺数设置为200,攻角为20°,计算域离散采用局部节点加密技术以减少计算量.
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| GB/T 7714 | 王同生 , 孙中国 , 黄柱 et al. 神经网络对于翼型绕流流场的重构 [J]. | 工程热物理学报 , 2021 , 42 (5) : 1205-1212 . |
| MLA | 王同生 et al. "神经网络对于翼型绕流流场的重构" . | 工程热物理学报 42 . 5 (2021) : 1205-1212 . |
| APA | 王同生 , 孙中国 , 黄柱 , 席光 . 神经网络对于翼型绕流流场的重构 . | 工程热物理学报 , 2021 , 42 (5) , 1205-1212 . |
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Abstract ：
Present paper attempts to reconstruct 2D unsteady flow field using neural network when fluid flows past airfoils at low Reynolds number. First of all, the details of fluid domain are obtained by solving incompressible fluid governing equation using our own developed fluid solver based on local radial basis function (LRBF) method, and then some randomly selected tempo-spatial points (with velocities and pressure information) are fed into neural network to train. The training process of first step is to learn Reynolds number, continuing with reconstruction of fluid field and comparison with numerical results. The flow Reynolds number is set as 200, while angle of attack is 20°. Besides, the locally refined nodes distribution of spatial domain is to globally reduce the computing resource. © 2021, Science Press. All right reserved.
Keyword ：
Airfoils Angle of attack Neural networks Reynolds number Unsteady flow
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| GB/T 7714 | Wang, Tong-Sheng , Sun, Zhong-Guo , Huang, Zhu et al. Reconstruction of Fluid Flows Past Airfoils Using Neural Network [J]. | Journal of Engineering Thermophysics , 2021 , 42 (5) : 1205-1212 . |
| MLA | Wang, Tong-Sheng et al. "Reconstruction of Fluid Flows Past Airfoils Using Neural Network" . | Journal of Engineering Thermophysics 42 . 5 (2021) : 1205-1212 . |
| APA | Wang, Tong-Sheng , Sun, Zhong-Guo , Huang, Zhu , Xi, Guang . Reconstruction of Fluid Flows Past Airfoils Using Neural Network . | Journal of Engineering Thermophysics , 2021 , 42 (5) , 1205-1212 . |
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In this paper, a finite volume WENO scheme on OpenFOAM, which can achieve arbitrary high order and be applied to unstructured grids, is used to simulate the viscous shock tube. The simulation is conducted on structured grids and triangular unstructured grids, in which the third-order and fourth-order WENO schemes are used to discretize the convection term. The results show that the accuracy and efficiency of the scheme on triangular unstructured grids are better than that on structured grids, and the efficiency of the third-order WENO scheme is higher than that of the fourth-order scheme. This work shows that the third-order WENO scheme with unstructured grids on OpenFOAM has more advantages and application potential in the simulation of complex flow fields such as internal flow of turbomachinery. © 2021, Science Press. All right reserved.
Keyword ：
Efficiency Shock tubes
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| GB/T 7714 | Chai, De-Lin , Xi, Guang , Sun, Zhong-Guo . Simulations of the Viscous Shock Tube With Finite Volume WENO Schemes [J]. | Journal of Engineering Thermophysics , 2021 , 42 (1) : 115-120 . |
| MLA | Chai, De-Lin et al. "Simulations of the Viscous Shock Tube With Finite Volume WENO Schemes" . | Journal of Engineering Thermophysics 42 . 1 (2021) : 115-120 . |
| APA | Chai, De-Lin , Xi, Guang , Sun, Zhong-Guo . Simulations of the Viscous Shock Tube With Finite Volume WENO Schemes . | Journal of Engineering Thermophysics , 2021 , 42 (1) , 115-120 . |
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The preliminary design and analysis methods of single-stage mixed-flow/centrifugal compressors were studied on the basis of the two-zone model, and the accuracy of the improved ODP problem iterative method based on SOA-TEIS mixed diffusion model in the preliminary design and analysis of the mixed-flow/centrifugal compressor was verified. The one-dimensional design and analysis of Krain high specific speed impeller and low specific speed impeller models were carried out using this method, and the results were compared with experimental data. The results show that the method presented in this paper could reduce the dependence on engineering experience parameter selection, and achieve accurate preliminary design calculations and off-design point performance predictions for mixed-flow/centrifugal compressors. The method was easy to implement programmatically, and the isentropic efficiency prediction deviation of the operating conditions near the design point obtained by the passive slip factor calculation method was within 1%. © 2021, Science Press. All right reserved.
Keyword ：
Compressors Design Impellers Iterative methods
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| GB/T 7714 | Tang, Yong-Hong , Wang, Zhi-Heng , Ji, Cheng et al. Research on Preliminary Design and Analysis Method of Mixed-flow/Centrifugal Compressor [J]. | Journal of Engineering Thermophysics , 2021 , 42 (2) : 393-398 . |
| MLA | Tang, Yong-Hong et al. "Research on Preliminary Design and Analysis Method of Mixed-flow/Centrifugal Compressor" . | Journal of Engineering Thermophysics 42 . 2 (2021) : 393-398 . |
| APA | Tang, Yong-Hong , Wang, Zhi-Heng , Ji, Cheng , Xi, Guang . Research on Preliminary Design and Analysis Method of Mixed-flow/Centrifugal Compressor . | Journal of Engineering Thermophysics , 2021 , 42 (2) , 393-398 . |
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The propagation characteristics of inlet total-pressure distortion in a centrifugal compressor are investigated by fullannulus unsteady three-dimensional numerical simulation. The inlet distortions considered in the paper are the total-pressure distortions covering a 60-deg sector (60deg distortion) and three 20-deg sectors (3∗20deg distortion), respectively. One is the classical distortion form, and the other is to simulate the downstream flow of the axial section of a centrifugal-axial combined compressor. By analyzing the distributions of flow parameters, the propagation of the total-pressure distortion in the centrifugal compressor is interpreted. The results show that, with the distortion propagating to the downstream, the lowpressure region produces a phase deviation along the streamwise direction relative to the opposite direction of impeller rotation direction, and the range of distortion region is reduced. Additionally, the propagation of the inlet distortion makes the three-dimensional characteristics of airflow more complex. The flow angle increases with different amplitudes along the direction of blade height corresponding to the distorted sector. The distortion region affects the location of blades which are in a low-pressure area, and the intensity of the distortion affects the increase of the flow angle. The distortion region causes more local relative flow losses, especially near the leading edge of blade suction surface. © 2021 American Society of Mechanical Engineers (ASME). All rights reserved.
Keyword ：
Centrifugal compressors Centrifugation
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| GB/T 7714 | Wang, Mingyi , Wang, Zhiheng , Xi, Guang et al. Numerical investigation on propagation characteristics of inlet total-pressure distortion in a centrifugal compressor [C] . 2021 . |
| MLA | Wang, Mingyi et al. "Numerical investigation on propagation characteristics of inlet total-pressure distortion in a centrifugal compressor" . (2021) . |
| APA | Wang, Mingyi , Wang, Zhiheng , Xi, Guang , Li, Yurun . Numerical investigation on propagation characteristics of inlet total-pressure distortion in a centrifugal compressor . (2021) . |
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In this paper, a numerical model of gas flow, heat transfer, mass transfer and electrochemical reaction multi-physics field coupling of a planar SOFC is established and solved. According to the calculation results, the distribution of velocity, temperature and concentration inside the SOFC cell is analyzed. The influence of cathode inlet flow rate, porosity, rib width and other parameters on the performance of SOFC is also discussed. The results show that within a certain range, increasing the cathode inlet flow rate can significantly increase the average current density of the cell. Increasing the porosity of the electrode can improve the gas diffusion of the porous electrode, thereby increasing the rate of the electrochemical reaction. Increasing the width of the ribs will result in a significant decrease in cell performance. Therefore, the rib width should be reduced as much as possible within the allowable range to optimize the working performance of the cell.
Keyword ：
multiphysics coupling parameter study physical fields distribution solid oxide fuel cells work performance
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| GB/T 7714 | Dang Zheng , Shen Xin , Ma Jinyan et al. Multiphysics Coupling Simulation and Parameter Study of Planar Solid Oxide Fuel Cell. [J]. | Frontiers in chemistry , 2021 , 8 . |
| MLA | Dang Zheng et al. "Multiphysics Coupling Simulation and Parameter Study of Planar Solid Oxide Fuel Cell." . | Frontiers in chemistry 8 (2021) . |
| APA | Dang Zheng , Shen Xin , Ma Jinyan , Jiang Zhaoyi , Xi Guang . Multiphysics Coupling Simulation and Parameter Study of Planar Solid Oxide Fuel Cell. . | Frontiers in chemistry , 2021 , 8 . |
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The periodic unsteady natural convection flow and heat transfer in a square enclosure containing a heated circular cylinder with different vertical locations is numerically studied. The temperature of the enclosure keeps lower constant while the temperature of the inner circular cylinder oscillates periodically with time at higher averaged value, the natural convection in the enclosure is driven by the temperature difference. The two-dimensional natural convection is simulated with high accuracy temporal spectral method and local radial basis functions method at Rayleigh number Ra = 10(5). The location of inner circular cylinder varies from -0.25 to 0.25 vertically, the temperature pulsating amplitudes are a = 0.5, 1.0 and 1.5 and the temperature pulsating period ranges from 0.01 to 100. Numerical results show that the heat transfer is strongly dependent on the vertical location and the pulsating temperature of inner cylinder. The heat transfer is enhanced generally for the time-periodic unsteady natural convection comparing with its steady state natural convection, and the local maximum heat transfer rate is observed for some locations. Moreover, the phenomenon of backward heat transfer is discussed and the quantity of back heat transfer rate is presented. Finally, the influence of the vertical locations and pulsating temperature on the unsteady fluid flow and heat transfer are discussed and analyzed.
Keyword ：
Backward heat transfer Different vertical locations Heat transfer enhancement Time-periodic natural convection Time pulsating temperature
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| GB/T 7714 | Wang, Zhiheng , Wang, Tongsheng , Xi, Guang et al. Periodic unsteady natural convection in square enclosure induced by inner circular cylinder with different vertical locations [J]. | INTERNATIONAL COMMUNICATIONS IN HEAT AND MASS TRANSFER , 2021 , 124 . |
| MLA | Wang, Zhiheng et al. "Periodic unsteady natural convection in square enclosure induced by inner circular cylinder with different vertical locations" . | INTERNATIONAL COMMUNICATIONS IN HEAT AND MASS TRANSFER 124 (2021) . |
| APA | Wang, Zhiheng , Wang, Tongsheng , Xi, Guang , Huang, Zhu . Periodic unsteady natural convection in square enclosure induced by inner circular cylinder with different vertical locations . | INTERNATIONAL COMMUNICATIONS IN HEAT AND MASS TRANSFER , 2021 , 124 . |
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Dealing with complex geometry boundaries is a challenge for particle boundary conditions. Since the effective area of the fluid particle is cut off by the boundary, it is difficult to obtain accurate results near the boundary, especially for complex geometry shapes. Things become more complicated when dealing with multiple sizes of particles in multi-resolution particle methods. In this paper, a generic smoothed wall (GSW) boundary is proposed by using single layer particles to accurately discretize the boundary. The boundary weight function is transformed to a distance function to fill the vacancy of the particle number density of fluid particles. The GSW boundary can be applied in the static, moving and non-linear deforming wall conditions. It also can be used to effectively handle complex geometric boundaries, since simulation results are not affected by changes in the number and size of wall particles. In addition, the GSW boundary also shows good results when combined with multi-resolution methods solving problems with multiple sizes of particles. In this paper, the MPS–DEM coupling method with GSW boundary model is applied to solve non-linear FSI problem. Several cases have been calculated to validate the accuracy, convergency and stability of the GSW boundary model. Compared with dummy particle boundary, results show that the proposed GSW boundary model can improve the numerical accuracy near the boundary, and handle arbitrary moving boundaries with high efficiency. © 2021 Elsevier B.V.
Keyword ：
Computational methods Computer applications Geometry
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| GB/T 7714 | Sun, Yijie , Xi, Guang , Sun, Zhongguo . A generic smoothed wall boundary in multi-resolution particle method for fluid–structure interaction problem [J]. | Computer Methods in Applied Mechanics and Engineering , 2021 , 378 . |
| MLA | Sun, Yijie et al. "A generic smoothed wall boundary in multi-resolution particle method for fluid–structure interaction problem" . | Computer Methods in Applied Mechanics and Engineering 378 (2021) . |
| APA | Sun, Yijie , Xi, Guang , Sun, Zhongguo . A generic smoothed wall boundary in multi-resolution particle method for fluid–structure interaction problem . | Computer Methods in Applied Mechanics and Engineering , 2021 , 378 . |
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A full-range prediction model for turbomachinery based on the flow-field information code is established in this article to solve the problems that traditional models do not have enough prediction accuracy and cannot reflect the complete performance characteristics of the impeller. The model, which can predict the complete performance curve of the impeller with higher accuracy, consists of two multilayer artificial neural network (ANN) submodels. Different from the traditional model, the ANN submodel uses the flow-field information code for pretraining layer by layer. The flow-field information code is the characteristic information extracted from the impeller flow field through the proper orthogonal decomposition (POD) method. By implicitly learning the flow-field information, the prediction error of the model is reduced by 29.7% compared with the single hidden layer ANN. Based on this model, the nonaxisymmetric, but periodic, hub optimization of a centrifugal impeller with 30 variables is carried out, with the goals of the higher efficiency and the wider flow range at the specified pressure ratio and the massflow rate at the design point. The result shows that, after the optimization, the isentropic efficiency at the design point increases by 1% and the flow range increases by 2% compared to the baseline. Copyright © 2021 by ASME
Keyword ：
Centrifugation Efficiency Flow fields Forecasting Impellers Multilayer neural networks Predictive analytics
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| GB/T 7714 | Ji, Cheng , Wang, Zhiheng , Tang, Yonghong et al. A flow information-based prediction model applied to the nonaxisymmetric hub optimization of a centrifugal impeller [J]. | Journal of Mechanical Design, Transactions of the ASME , 2021 , 143 (10) . |
| MLA | Ji, Cheng et al. "A flow information-based prediction model applied to the nonaxisymmetric hub optimization of a centrifugal impeller" . | Journal of Mechanical Design, Transactions of the ASME 143 . 10 (2021) . |
| APA | Ji, Cheng , Wang, Zhiheng , Tang, Yonghong , Xi, Guang . A flow information-based prediction model applied to the nonaxisymmetric hub optimization of a centrifugal impeller . | Journal of Mechanical Design, Transactions of the ASME , 2021 , 143 (10) . |
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Abstract ：
Previous publications have summarized that three special morphological structures of owl wing could reduce aerodynamic noise under low Reynolds number flows effectively. However, the coupling noise-reduction mechanism of bionic airfoil with trailing-edge serrations is poorly understood. Furthermore, while the bionic airfoil extracted from natural owl wing shows remarkable noise-reduction characteristics, the shape of the owl-based airfoils reconstructed by different researchers has some differences, which leads to diversity in the potential noise-reduction mechanisms. In this article, three kinds of owl-based airfoils with trailing-edge serrations are investigated to reveal the potential noise-reduction mechanisms, and a clean airfoil based on barn owl is utilized as a reference to make a comparison. The instantaneous flow field and sound field around the three-dimensional serrated airfoils are simulated by using incompressible large eddy simulation coupled with the FW-H equation. The results of unsteady flow field show that the flow field of Owl B exhibits stronger and wider-scale turbulent velocity fluctuation than that of other airfoils, which may be the potential reason for the greater noise generation of Owl B. The scale and magnitude of alternating mean convective velocity distribution dominates the noise-reduction effect of trailing-edge serrations. The noise-reduction characteristic of Owl C outperforms that of Barn owl, which suggests that the trailing-edge serrations can suppress vortex shedding noise of flow field effectively. The trailing-edge serrations mainly suppress the low-frequency noise of the airfoil. The trailing-edge serration can suppress turbulent noise by weakening pressure fluctuation.
Keyword ：
flow control noise reduction owl trailing-edge serration
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| GB/T 7714 | Li, Dian , Liu, Xiaomin , Wang, Lei et al. Numerical study on the airfoil self-noise of three owl-based wings with the trailing-edge serrations [J]. | PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING , 2021 , 235 (14) : 2003-2016 . |
| MLA | Li, Dian et al. "Numerical study on the airfoil self-noise of three owl-based wings with the trailing-edge serrations" . | PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING 235 . 14 (2021) : 2003-2016 . |
| APA | Li, Dian , Liu, Xiaomin , Wang, Lei , Hu, Fujia , Xi, Guang . Numerical study on the airfoil self-noise of three owl-based wings with the trailing-edge serrations . | PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING , 2021 , 235 (14) , 2003-2016 . |
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