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| 1 | A CFD/CSD model for aeroelastic calculations of large-scale wind turbines显示文摘In this paper,a CFD/CSD model coupling N-S equations and structural equations of motion in the time domain is described for aeroelastic analysis of large wind turbines.The structural modes of blades are analyzed with one-dimensional beam models.By combining point matched sliding grid for wind turbine rotation and deforming grid for structural vibrations,a hybrid dynamic grid strategy is designed for the multi-block structured grid system of a wind turbine.The dual time-stepping approach and finite volume scheme are applied to the three-dimensional unsteady preconditioned N-S equations,and DES approach is employed to simulate the unsteady massively separated flows.A modal approach is adopted to calculate the structural response,and a predictor-corrector scheme is used to solve the structural equations of motion.CFD and CSD solvers are tightly coupled via successive iterations within each physical time step.As a result,a time-domain CFD/CSD model for aeroelastic analysis of a large wind turbine is achieved.The presented method is applied to the NH1500 large wind turbine under the rated condition,and the calculated aeroelastic characteristics agree well with those of the prescribed vortex wake method. | GUO TongQing LU ZhiLiang TANG Di WANG TongGuang DONG Lu | 2013 | Science China(Technological Sciences)2013，56，1： | 11 |
| 2 | Numerical method of static aeroelastic correction and jig-shape design for large airliners显示文摘In this paper,a coupled CFD-CSD method based on N-S equations is described for static aeroelastic correction and jig-shape design of large airliners.The wing structural flexibility matrix is analyzed by a finite element method with a double-beam model.The viscous multi-block structured grid is used in aerodynamic calculations.Flexibility matrix interpolation is fulfilled by use of a surface spline method.The load distributions on wing surface are evaluated by solving N-S equations with a parallel algorithm.A flexibility approach is employed to calculate the structural deformations.By successive iterations between steady aerodynamic forces and structural deformations,a coupled CFD-CSD method is achieved for the static aeroelastic correction and jig-shape design of a large airliner.The present method is applied to the static aeroelastic analysis and jig-shape design for a typical large airliner with engine nacelle and winglet.The numerical results indicate that calculations of static aeroelastic correction should employ tightly coupled CFD-CSD iterations,and that on a given cruise shape only one round of iterative design is needed to obtain the jig-shape meeting design requirements. | HUANG Wei LU ZhiLiang GUO TongQing XUE Fei ZHANG Miao | 2012 | Science China(Technological Sciences)2012，55，9： | 4 |
| 3 | Andrographolide and Its Derivative Potassium Dehydrographolide Succinate Suppress PRRSV Replication in Primary and Established Cells via Differential Mechanisms of Action显示文摘Porcine reproductive and respiratory syndrome virus(PRRSV) continues to cause significant economic loss worldwide and remains a serious threat to the pork industry. Currently, vaccination strategies provide limited protection against PRRSV infection, and consequently, new antiviral strategies are urgently required. Andrographolide(Andro) and its derivative potassium dehydrographolide succinate(PDS) have been used clinically in China and other Asian countries as therapies for inflammation-related diseases, including bacterial and viral infections, for decades. Here, we demonstrate that Andro and PDS exhibit robust activity against PRRSV replication in Marc-145 cells and primary porcine alveolar macrophages(PAMs). The two compounds exhibited broad-spectrum inhibitory activities in vitro against clinically circulating type 2 PRRSV GD-HD, XH-GD, and NADC30-like HNhx strains in China. The EC_(50)values of Andro against three tested PRRSV strain infections in Marc-145 cells ranged from 11.7 to 15.3 lmol/L, with selectivity indexes ranging from 8.3 to10.8, while the EC_(50)values of PDS ranged from 57.1 to 85.4 lmol/L, with selectivity indexes ranging from 344 to 515.Mechanistically, the anti-PRRSV activity of the two compounds is closely associated with their potent suppression on NFj B activation and enhanced oxidative stress induced by PRRSV infection. Further mechanistic investigations revealed that PDS, but not Andro, is able to directly interact with PRRSV particles. Taken together, our findings suggest that Andro and PDS are promising PRRSV inhibitors in vitro and deserves further in vivo studies in swine. | Lizhan Su Yarou Gao Mingxin Zhang Zexin Liu Qisheng Lin Lang Gong Jianying Guo Lixia Chen Tongqing An Jianxin Chen | 2021 | Virologica Sinica2021，36，6： | 4 |
| 4 | Simulation of Viscous Flows Around A Moving Airfoil by Field Velocity Method with Viscous Flux Correction显示文摘Based on the field velocity method,a novel approach for simulating unsteady pitching and plunging motion of an airfoil is presented in this paper.Responses to pitching and plunging motions of the airfoil are simulated under different conditions.The obtained results are compared with those of moving grid method and good agreement is achieved.In the conventional field velocity method,the Euler solver is usually used to simulate the movement of the airfoil.However,when viscous effect is considered,unsteady Navier-Stokes equations have to be solved and the viscous flux correction must be taken into account.In this work,the viscous flux correction is introduced into the conventional field velocity method when non-uniform grid speed distribution is occurred.Numerical experiments for the flow around NACA0012 airfoil showed that the proposed approach can well simulate viscous moving boundary flow problems. | Ning Gu Zhiliang Lu Tongqing Guo | 2012 | Advances in Applied Mathematics and Mechanics2012，4，3： | 1 |
| 5 | Aeroelastic prediction and analysis for a transonic fan rotor with the“hot”blade shape显示文摘This paper focuses on aeroelastic prediction and analysis for a transonic fan rotor with only its“hot”(running)blade shape available,which is often the case in practical engineering such as in the design stage.Based on an in-house and well-validated CFD solver and a hybrid structural finite element modeling/modal approach,three main aspects are considered with special emphasis on dealing with the“hot”blade shape.First,static aeroelastic analysis is presented for shape transformation between“cold”(manufacturing)and“hot”blades,and influence of the dynamic variation of“hot”shape on evaluated aerodynamic performance is investigated.Second,implementation of the energy method for flutter prediction is given and both a regularly used fixed“hot”shape and a variable“hot”shape are considered.Through comparison,influence of the dynamic variation of“hot”shape on evaluated aeroelastic stability is also investigated.Third,another common way to predict flutter,time-domain method,is used for the same concerned case,from which the predicted flutter characteristics are compared with those from the energy method.A well-publicized axial-flow transonic fan rotor,Rotor 67,is selected as a typical example,and the corresponding numerical results and discussions are presented in detail. | Di ZHOU Ziliang LU Tongqing GUO Guoping CHEN | 2021 | Chinese Journal of Aeronautics2021，34，7： | 1 |
| 6 | An Efficient Dynamic Mesh Generation Method for Complex Multi-Block Structured Grid显示文摘Aiming at a complex multi-block structured grid,an efficient dynamic mesh generation method is presented in this paper,which is based on radial basis functions(RBFs)and transfinite interpolation(TFI).When the object is moving,the multi-block structured grid would be changed.The fast mesh deformation is critical for numerical simulation.In this work,the dynamic mesh deformation is completed in two steps.At first,we select all block vertexes with known deformation as center points,and apply RBFs interpolation to get the grid deformation on block edges.Then,an arc-lengthbased TFI is employed to efficiently calculate the grid deformation on block faces and inside each block.The present approach can be well applied to both two-dimensional(2D)and three-dimensional(3D)problems.Numerical results show that the dynamic meshes for all test cases can be generated in an accurate and efficient manner. | Li Ding Zhiliang Lu Tongqing Guo | 2014 | Advances in Applied Mathematics and Mechanics2014，6，1： | 1 |
| 7 | Development of a Synchronization Method for Fluid-Thermal Study of Hypersonic Flow显示文摘A synchronization method is developed for the fluid-thermal study of hypersonic flow.Different from conventional loosely/tightly coupled methods which separately deal with the flow field and the structure temperature field,the presented method expresses the governing equations in a unified framework so that the two fields can be calculated simultaneously.For efficiently solving the unified equations,the finite volume method together with the dual-time stepping approach is employed.Like in the flow field,the local time step is also used in the temperature field,which is determined from thermal conductivity spectral radii.In order to treat the fluid-structure interface more conveniently,an expanded virtual boundary is introduced.For validation,several fluid-thermal hypersonic flow problems are simulated.The computed results are compared with those obtained from the coupled methods and the experiment.In the continuous heating problems,the stagnation temperatures predicted by both the coupled and synchronization methods are in good agreements with the experimental data.In the unsteady flowthermal hypersonic flows,the stagnation heat fluxes predicted by the presented method and tightly coupled method are basically the same,which agree better with the experimental data than those predicted by the loosely coupled method.In terms of prediction of the stagnation temperature,the synchronization method shows better accuracy than the tightly coupled method. | ShenEnnan Lu Zhiliang Zhou Di Guo Tongqing | 2018 | Transactions of Nanjing University of Aeronautics and Astronautics2018，35，6： | 0 |
| 8 | COMPUTATION OF UNSTEADY AERODYNAMIC FORCES ON WINGS WITH NAVIER-STOCKS EQUATIONS显示文摘A 'dual time' method for the solution of unsteady three dimensional Navier Stocks equations is described in this paper. An implicit real time discretisation is used, and then the equations are integrated in a fictitious pseudo time. When marching in a pseudo time, the finite volume method, multi grid scheme and other acceleration techniques used in steady flow calculations can be used. Balwin Lomax turbulence model is applied to simulate the turbulence. | Guo Tongqing Lu Zhiliang College of Aerospace Engineering,NUAA29 Yudao Street Nanjing 210016,P.R.China | 2001 | Transactions of Nanjing University of Aeronautics and Astronautics2001，18，z1： | 0 |
| 9 | CFD/CSD-based flutter prediction method for experimental models in a transonic wind tunnel with porous wall显示文摘To predict the flutter dynamic pressure of a wind tunnel model before flutter test,an accurate Computational Fluid Dynamics/Computational Structural Dynamics(CFD/CSD)-based flutter prediction method is proposed under the conditions of a 2.4 m×2.4 m transonic wind tunnel with porous wall.From the CFD simulations of the flows through an inclined hole of this wind tunnel,the Nambu's linear porous wall model between the flow rate and the differential pressure is extended to the porous wall with inclined holes,so that the porous wall can be conveniently modeled as a boundary condition.According to the flutter testing approach for the current wind tunnel,the steady CFD calculation is conducted to achieve the required inlet Mach number.A timedomain CFD/CSD method is then employed to evaluate the structural response of the experimental model,and the critical flutter point is obtained by increasing the dynamic pressure step by step at a fixed Mach number.The present method is applied to the flutter calculations for a vertical tail model and an aircraft model tested in the current transonic wind tunnel.For both models,the computed flutter characteristics agree well with the experimental results. | Tongqing GUO Daixiao LU Zhiliang LU Di ZHOU Binbin LYU Jiangpeng WU | 2020 | Chinese Journal of Aeronautics2020，33，12： | 0 |
| 10 | Time-Domain Analysis of Body Freedom Flutter Based on 6DOF Equation显示文摘The reduced weight and improved efficiency of modern aeronautical structures result in a decreasing separation of frequency ranges of rigid and elastic modes.Particularly,a high-aspect-ratio flexible flying wing is prone to body freedomflutter(BFF),which is a result of coupling of the rigid body short-periodmodewith 1st wing bendingmode.Accurate prediction of the BFF characteristics is helpful to reflect the attitude changes of the vehicle intuitively and design the active flutter suppression control law.Instead of using the rigid body mode,this work simulates the rigid bodymotion of the model by using the six-degree-of-freedom(6DOF)equation.A dynamicmesh generation strategy particularly suitable for BFF simulation of free flying aircraft is developed.An accurate Computational Fluid Dynamics/Computational Structural Dynamics/six-degree-of-freedom equation(CFD/CSD/6DOF)-based BFF prediction method is proposed.Firstly,the time-domain CFD/CSD method is used to calculate the static equilibrium state of the model.Based on this state,the CFD/CSD/6DOF equation is solved in time domain to evaluate the structural response of themodel.Then combinedwith the variable stiffnessmethod,the critical flutter point of the model is obtained.This method is applied to the BFF calculation of a flyingwing model.The calculation results of the BFF characteristics of the model agree well with those fromthe modalmethod andNastran software.Finally,the method is used to analyze the influence factors of BFF.The analysis results show that the flutter speed can be improved by either releasing plunge constraint or moving the center ofmass forward or increasing the pitch inertia. | Zhehan Ji Tongqing Guo Di Zhou Zhiliang Lu Binbin Lyu | 2024 | Computer Modeling in Engineering & Sciences2024，138，1： | 0 |
| 11 | Primary Search for New Neutron-rich Nuclide ^(209)Hg显示文摘Primary Search for New Neutron-rich Nuclide ^(209)HgPrimarySearchforNewNeutron-richNuclide^(209)Hg￥ZhangLi;ZhaoJinhua;ZhengJiw... | Zhang Li Zhao Jinhua Zheng Jiwen Wang Jicheng Qin Zhi Yang Younsfeng Zhang Chun Guo Guanghui Jin Ganging Du Yifei Guo Tianrui Wang Tongqing Guo Bin and Tan Jinfeng | 1995 | IMP & HIRFL Annual Report1995，，0： | 0 |
| 12 | Progress of Isotope Separator On-line in Lanzhou显示文摘ProgressofIsotopeSeparatorOn-lineinLanzhou￥WangTongqing;GuoBing;FanHongmei;ZhaoJinghuaandGuoYingXiangTheIsotopeSeparatorOn-li... | Wang Tongqing Guo Bing Fan Hongmei Zhao Jinghua and Guo YingXiang | 1996 | IMP & HIRFL Annual Report1996，，1： | 0 |
| 13 | A Three-Dimensional Gas-Kinetic BGK Scheme for Simulating Flows in Rotating Machinery显示文摘This paper focuses on the development and application of a threedimensional gas-kinetic Bhatnagar-Gross-Krook(BGK)method for the viscous flows in rotating machinery.For such flows,a rotating frame of reference is usually used in formulating the Navier-Stokes(N-S)equations,and there are two major concerns in constructing the corresponding BGK model.One is the change of the convective velocities in the N-S equations,which can be reflected through modification of the gas streaming velocity.The other one is the necessity to account for the effect of the additional Coriolis and centrifugal forces.Here,a specifically-designed acceleration term is added into the modified Boltzmann equation so that the source effects can be naturally included into the gas evolution process and the resulted fluxes.Under the finitevolume framework,the constructed BGK model is locally solved at each cell interface and then the numerical fluxes can be evaluated.When employing the BGK scheme,it is sometimes found that the calculated spatial derivatives of the initial and equilibrium distribution functions are sensitive to the mesh quality especially in complex rotating flow applications,which may significantly influence flux evaluation.Therefore,an improved approach for computing these slopes is adopted,through which the modeling capability for viscous flows is enhanced.For validation,several numerical examples are presented.The computed results show that the present method can be well applied to a wide range of flows in rotating machinery with favorable accuracy. | Di Zhou Zhiliang Lu Tongqing Guo | 2019 | Advances in Applied Mathematics and Mechanics2019，11，1： | 0 |
| 14 | CFD-Based Load Calculation Method for Monopile Support Configuration of Offshore Wind Turbine显示文摘An unsteady load calculation method for the support configuration of a monopile-supported offshore wind turbine is developed based on the Fluent software platform.Firstly,the water wave is generated by imposing the inlet boundary conditions according to the exact potential flow solution.Then the wave evolution is simulated by solving the unsteady incompressible Navier-Stokes(N-S)equations coupled with the volume of fluid method.For the small amplitude wave with reasonable wave parameters,the numerical wave result agrees well with that of the given wave model.Finally,a monopile support configuration is introduced and a CFD-based load calculation method is established to accurately calculate the unsteady load under the combined action of wave and wind.The computed unsteady wave load on a small-size monopile support located in the small amplitude wave flow coincides with that of the Morison formula.The load calculations are also performed on a large-size monopile support and a monopile-supported offshore wind turbine under the combined action of small amplitude wave and wind. | Guo Tongqing Tong Xiaolong Lu Zhiliang | 2016 | Transactions of Nanjing University of Aeronautics and Astronautics2016，33，1： | 0 |
| 15 | A New D-GCL for Unidirectional Motion with Large Displacement显示文摘Numerical simulations of unsteady flow problems with moving boundaries commonly require the use of geometric conservation law(GCL).However,in cases of unidirectional large mesh deformation,the cumulative error caused by the discrete procedure in GCL can significantly increase,and a direct consequence is that the calculated cell volume may become negative.To control the cumulative error,a new discrete GCL(D-GCL)is proposed.Unlike the original D-GCL,the proposed method uses the control volume analytically evaluated according to the grid motion at the time level n,instead of using the calculated value from the D-GCL itself.Error analysis indicates that the truncation error of the numerical scheme is guaranteed to be the same order as that obtained from the original D-GCL,while the accumulated error is greatly reduced.For validation,two challenging large deformation cases including a rotating circular cylinder case and a descending GAW-(1)two-element airfoil case are selected to be investigated.Good agreements are found between the calculated results and some other literature data,demonstrating the feasibility of the proposed D-GCL for unidirectional motions with large displacements. | Zhu Yixi Lu Zhiliang Guo Tongqing | 2018 | Transactions of Nanjing University of Aeronautics and Astronautics2018，35，1： | 0 |
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