bluuebunny/crossref_metadata_2025_split huggingface dataset:
Study on the Flow Field in Two-level and Staggered Back Vane and Its Impact on Desulfurization Pump
Authors: Zhang Yu 
Published: August 2021

Abstract
At present, the research on different kinds of the back vane of slurry pumps, such as desulfurization pumps, all focus on simple structures. Many new attempts have been applied in the design of back vane in engineering practice, and the two-layer staggered back vane is one of them. This study analyzes the influence of the new two-layer staggered back vane on the external characteristics, axial force balance, and solid impurities of the desulfurization pump. Based on the steady analysis of single-phase flow, the influence of the two-layer staggered back vane on external characteristics and axial force is studied. It is found that the design of the two-layer staggered back vane has negligible influence on the essential external characteristics of the pump. The design also has the function of balancing the axial force, which is more suitable for the situation that the axial force needed to be balanced is large. Therefore, it supports the two-layer staggered back vane to be widely used in solid-liquid two-phase impurity pumps. Furthermore, the unsteady analysis of two-phase flow is used to study the influence of the two-layer staggered back vane on solid-liquid two-phase flow. It is found that the design without back vane can not prevent the solid phase from depositing between the impeller rear cover and the rear pump cover, which may wear the pump shaft and even block the fluid flow in the rear pump chamber, which may have a severe impact on the mechanical life and performance. The single-layer back vane design can keep the solid concentrating at a low level near the shaft, thus reducing the friction between the solid and the shaft, avoiding the deposition in the rear pump chamber; The two-layer staggered back vane design keeps the solid concentration near the shaft at a lower level and more uniform, and has better protection effect on the shaft, the parts near the shaft, and the rear pump chamber than the traditional structure of the single-layer back vane.
Correction of Reynolds number effect for wind-tunnel model with flying wing
Authors: Yao Jieke , Li Wei , Xu Liang 
Published: August 2021

Abstract
A method of Re (Reynolds number, Re) effect correction based on data of wind-tunnel test for flying wing is proposed in this paper. By investigating change laws for longitudinal aerodynamic and moment coefficient, corrective parameters, correction equations and acquisition of correction quantity are introduced. And at the same time, CFD simulations at different Re are carried out to obtain the evidence of what Re does to aerodynamic characteristics and corrective parameters. To reduce fitting error based on polynomial functions, fitting equations of power exponential function are adopted to obtain correction for all corrective parameters. According to the correction quantities and correction equations, the data for wind-tunnel model is corrected to full-scale model. To verify the present method, the results will be compared with result of supercharging wind-tunnel test.
Optimization analysis for blades of artificial heart pump based on CFD
Authors: Li Tianrui , Zhou Junjie , Yu Yang 
Published: August 2021

Abstract
In this paper, computational fluid dynamics is used to simulate and analyse the flow field of a centrifugal artificial heart pump. First, the structural parameters of the centrifugal blood pump are initially determined, and the three-dimensional model of the flow field is established. The blood supply head of the pump is calculated based on the simulation results. The head of the centrifugal blood pump is 124.31mmHg under the design conditions (rotating speed is 2400rpm, flow rate is 6L/min), which meets the blood supply requirement of the heart pump. Then, by changing the blade profile length and blade shape, the performance of the centrifugal blood pump can be improved. The standard hemolysis index of the improved centrifugal blood pump dropped from 0.0508 to 0.0417, and its head is 119.65mmHg. It indicates that while reducing the destruction of blood cells by the heart pump, the requirement of blood supply head can still be met. The simulation results of this study can provide references for the design of centrifugal blood pump blades.
Numerical Simulation and Analysis of Air Duct of Microbar Air Quality Conditioning
Authors: Wang Hongliang , Shi Pidong 
Published: August 2021

Abstract
A microbar air conditioning duct was taken as the research object, and the flow field characteristics of air conditioning duct were numerically simulated based on CATIA and ANASYS software. According to the numerical simulation results, the pressure field and velocity distribution of the air duct were analysed in detail. The analysis results show that the increase of the inlet velocity of the left air duct is conducive to the increase of the velocity of the air outlet, but the flow resistance is increased. By changing the inner wall structure and inlet area of the air duct on the right side, the wind speed of the rear air outlet can be improved effectively.
Numerical analysis report on fluids in floating photovoltaic power plants
Authors: Bei Yaoping , Yuan Bingqing , Yu Yang , Zhu Liang , Cao Dongmei 
Published: August 2021

Abstract
In this paper, Xihe solar floating photovoltaic power station unit. Simulation analysis is carried out for the structure, strength analysis is carried out for a single solar structure support, analysis is carried out for photovoltaic array structure, and analysis is carried out for rectangular and square structures with different wind directions.
Research on Model Validation and Uncertainty Quantification of Airfoil Flow
Authors: Zhang Chao , Chen Jiangtao , Zhao Jiao , Wu Xiaojun 
Published: August 2021

Abstract
Numerical simulations and wind tunnel tests are both basic methods for aerodynamic research and application. They are the modeling and simulation of real world system. There are various uncertainties in the implementation process. In Computational Fluid Dynamics (CFD), the main sources of uncertainty are the model form, model parameters and numerical solution methods. In wind tunnel tests, there are many uncertainties sources, such as geometric model, test environment, test devices and instrumentation, test methods, data recording and processing, etc. This paper takes NACA0012 airfoil as an example. Bayesian model averaging method (BMA) and grid convergence study are used to analyse model form and numerical solution uncertainty in CFD. For the geometric configuration uncertainty in wind tunnel test, regression analysis and bootstrap method are used to carry out data fusion. Finally, model validation research is conducted.
Research on shock-vortex interaction of fairings based on dynamic unstructured overset grid
Authors: Cui Pengcheng , Chen Jiangtao , Li Bin , Li Huan , Ma Mingsheng , Tang Jing 
Published: August 2021

Abstract
The fairing is used to protect the aircraft from aerodynamic heat and force at high-speed, while there exists strong shock-vortex interaction during fairing separation. The unsteady shock-vortex interaction is numerically studied based on dynamic unstructured overset grid in this paper, where the N-S equations and 6-DOF equations are couple solved. Due to the blocking effect of fairings and shocks, there is a strong vortex inside the fairings. With the separation of fairings, the vortex is strongly compressed by the shock of fairing. When the shock is very close to fairing, the vortex is forced into the Mach cone of aircraft and enlarges the Mach cone. There exists a strong shock-vortex interaction of shock-vortex compressing, transforming of vortex boundary and vortex-shock compressing during fairing separation.
A Review of the influence of active aerodynamic tail on vehicle handling stability
Authors: Yu Wei , Gao Wei 
Published: August 2021

Abstract
In order to improve the safety of road vehicles, various active safety systems have been proposed and developed. These active safety systems include active forward / backward steering, differential braking, active roll moment control, etc. In essence, the longitudinal, transverse and vertical dynamics of the vehicle are controlled from the perspective of tire mechanics, which has the disadvantage that the tire is easy to be saturated under limit conditions. This paper summarizes the control schemes of active aerodynamics to improve vehicle handling stability. When the vehicle is running at high speed, aerodynamics has a great influence on the vehicle, which greatly reduces the handling stability of the vehicle. Low handling stability may lead to unstable motion patterns. In order to improve the lateral stability, various control schemes considering relevant performance measures are designed and evaluated by numerical simulation or experimental methods. This paper focuses on the active aerodynamic control scheme, analyzes its characteristics, and determines the future research work.
Study on trim optimization for an oil tanker
Authors: Gao Xianjiao , Shi Shengzhe , Wang Mingzhen , Zhang Jiaxu 
Published: August 2021

Abstract
The purpose of this paper is to study the influence of trim on resistance performance for an oil tanker. First, the three-dimensional ship model, calculation basin and structural mesh were obtained. Commercial code of computational fluid dynamics was utilized to calculate the resistance of target ship under various trim conditions and drafts. Then, we compared the results calculated by numerical simulation with the towing tank test results to validate effectiveness of CFD method. Finally, influence of trim on ship resistance performance was analysed. It is concluded that this method can find the optimal trim value and provide practical advice for actual operation of the real ship. Consequently, it can be used to improve the efficiency of energy-saving and emission reduction, which provides a new direction for the development of green ships.
Analysis of the seakeeping performance for Unmanned Underwater vehicle using STAR-CCM+
Authors: Song Lihua , Wang Zhuo , Xu Yongze 
Published: August 2021

Abstract
In this paper, the seakeeping performance of unmanned underwater vehicle (AUV) under the action of transverse waves is calculated and analyzed, based on the commercial CFD software STAR-CCM+. The test data verifies the reliability of the numerical calculation method. The roll and heave response of the vehicle under different working conditions provide a reference for the overall parameter design of the unmanned underwater vehicle.
Visualization of Vortices Generated by Flapping Wing Device by Schlieren Method
Authors: Zeng Zhixiang , Ye Yongjie , Jiang Hongpei , Jiang Jiajun , Wang Zitao , Yuan Shijia , Deng Jianjie 
Published: August 2021

Abstract
Visualization and measurement of airflow detail structures is a difficult problem. In the past few years, high-speed DPIV has been used to capture the vortex structures on flapping robotic insect wings. Due to the inherent limitation in DPIV technique, important airflow activity in small scale vortical flow structures may be missed. In this paper, high-speed Schlieren photography was applied to vortical flow Visualization on a flapping robotic insect wings and then provided more information of vortical flow structures in detail. Based on the Schlieren image, quantified velocity vectors field was obtained by applying the variational optical flow method, which is able to be extending the potential applications to development flapping wings aircraft.
Hybrid Flow Control on Boundary Layer Ingestion Inlet
Authors: Shang Yinhui , Ge Changjie , Xiao Lianghua , Hu Xiao 
Published: August 2021

Abstract
For the boundary layer ingestion (BLI) inlet, how to control the flow is very important to improve the quality of the air flow at the outlet. In this paper, the research on the passive flow control is carried out by using rectangular straight spoiler blades, and the active flow control is carried out by using the blowing pipes. Finally, the effect of hybrid flow control is explored by combining the passive flow control device and the active flow control device. The results show that the spoiler blades can squeeze the low pressure zone to both sides of the outlet and reduce the area of the low pressure zone. The steady-state circumferential distortion coefficient of the outlet can be reduced by 66.7% by adopting the appropriate passive flow control scheme. The blowing rate of active flow control has a significant effect on the flow control effect. The optimal hybrid flow control scheme is obtained by optimization and the steady-state circumferential distortion coefficient can be reduced by 76.8% when the blowing flow rate is 0.67% of the inlet flow.
Analysis on flow induced vibration of main steam bypass valve in a nuclear power plant
Authors: Liu Junfeng , Chen Xudong , Han Chuangao , Ma Xiaolong , Wu Fangjie 
Published: August 2021

Abstract
Based on the fact that the main steam bypass system of a nuclear power plant vibrates violently during operation, the failure of couplings and other parts of the bypass valve occurs many times, which seriously affects the safe operation of the unit. According to bypass discharge system, and the bypass valve related drawings bypass valve fluid dynamics model is established, on the opening of the bypass valve interior flow field in CFD numerical simulation analysis, combining with the field vibration test results, for the opening of the bypass valve interior flow field in CFD numerical simulation analysis and vibration mechanism research, found that the structure of the piping system vibration and vortex shedding in the valve to inspire the chattering of the valve stem and even the axis of the main causes of fracture and valve is the high degrees of vortex-induced resonance is the main reason of the turbulent flow hood.
Numerical Investigation of the Inlet with Different Lip-plane Shapes under Ground Running
Authors: Ge Changjie , Hu Xiao , Shang Yinhui , Xiao Lianghua 
Published: August 2021

Abstract
The inlet of the UAV is usually designed on the back of the aircraft in order to give consideration to the overall arrangement and stealth performance. Under ground running, there are often severe vortices in the duct of the backpack inlet, which leads to low total pressure recovery and large circumferential distortion index at the AIP. Different shapes of the lip-plane produce different vortices, which have great impact on circumferential distortion index at the AIP. In this paper, the characteristics of three different lip-plane shapes were studied under the ground running. Results indicate: (1) W-shaped inlet has lowest circumferential distortion index and the flow distribution is the most uniform at the AIP; (2) Λ-shaped inlet has the weakest of the vortex strength and the largest total pressure recovery, which means the thrust loss caused by the inlet is smallest; (3) V-shaped inlet has the strongest vortex strength and the lowest total pressure recovery.
Fixed Boundary transition effect on transport aircraft aerodynamic characteristics under different Reynolds numbers
Authors: Wang Yuanjing , Lv Binbin , Liu Dawei 
Published: August 2021

Abstract
Scale differences between test models and real aircraft result in Reynolds number effect, which made it impossible to simulate boundary layer conditions and obtain accurate aerodynamic characteristics of vehicles, especially of transport aircraft, by wind tunnel tests. Normally, laminar flow would exit over super critical wing during wind tunnel tests. Fixed transition effect on super critical wing aerodynamics characteristics was investigated in traditional wind tunnels. The relative experiments were conducted in a transonic wind tunnel. Force/moment and surface pressure distribution were measured with a full model and a half model respectively. Test Mach number ranged from 0.7 to 0.86, and Reynolds number ranged from 3.3 million to 16.5 million. Experiment results showed that surface pressure distribution would be changed significantly by fixed transition when shock wave and induced boundary layer separation appeared on upper surface. With the increasing of test Reynolds numbers, its effect became weakened, and the effect was ignorable when test Reynolds number exceeded 15 million. To obtain credible wind tunnel results, fixed boundary layer transition of super critical airfoil were recommended when test Reynolds numbers were less than 15 million.
Detached eddy simulation of the release progress of moving body separating from a cavity
Authors: Li Huan , Jia Hongyin , Cui Pengcheng , Chen Jiangtao , Zhou Guiyu , Zhang Yaobing 
Published: August 2021

Abstract
Aiming at the complex unsteady flow during the release progress of moving body separating from a cavity, combined with the overlapping grid technique and Spalart Allmaras equation turbulence model, the three-dimensional unsteady flow solver is presented. On this basis, the validity of the simulation method is verified by M219 cavity example and WPFS example. Then the released moving body is conducted with SA-IDES. The research results show that upward force and pitch down moment of the moving body are affected by the fluctuating flow near the cavity and the SA – DES simulation is good in predicting high frequency flow. In conclusion, the outside shear layer and the inside fluctuating flow of the cavity has a significant impact on the aerodynamic loads and the trajectory of the moving body during the initial separation stage.
Experimental study of underwater vehicle’s dissolved gas wake
Authors: Wang Yun , Zhu Haixiong , Wu Jianwei , Dong Liang 
Published: August 2021

Abstract
In order to maintain the internal environment, underwater vehicles continue to emit carbon dioxide. Carbon dioxide dissolves in water to form dissolved carbon dioxide wake characteristics. Based on a self-designed and built experimental bench, a model experiment of dissolved carbon dioxide produced by the underwater vehicle was carried out. The effects of carbon dioxide emission flow and speed of the vehicle on the characteristics of dissolved carbon dioxide wake are analysed. The results showed that, due to the carbon dioxide emissions of the underwater vehicle, the area passed by the underwater vehicle formed a wake containing dissolved carbon dioxide. The dissolved carbon dioxide wake of the underwater vehicle lasts for a long time, that is, in the area far behind the underwater vehicle, the characteristic of dissolved carbon dioxide is still obvious enough to be detected by the detector. In addition, the wake characteristics of dissolved carbon dioxide when the propeller is rotating and when it is not moving are compared. The results show that the mixing action of the propeller has a great influence on the characteristic distribution of dissolved carbon dioxide.
Multi-Objective Optimization Design of Liftbody Aircraft Using Kriging Model
Authors: Xu Liang , Zhang Bin , Chen Bin , Wu Peng 
Published: August 2021

Abstract
The evolutionary algorithm combined with Kriging surrogate model is applied to aerodynamic optimization design of high-altitude hypersonic aircraft. In this paper, a 3D liftbody aircraft in cruise flight state is designed which divided into forebody/inlet, engine and after-body/nozzle parts, and its variable parameterization method is studied by considering the multi-disciplinary coupling effect of airframe/engine integration; four disciplines analysis model, i.e. engine propulsion performance, the forebody/inlet air-breathing performance, aerodynamic force and thermodynamics, are established and the appropriate objective parameters are selected, then genetic algorithms are used to optimize the design. The single-objective optimization results show that the performance of aircraft is effectively improved; the multi-objective optimization results reveal that the total trade-off is achieved.
Hydrodynamic Engineering Calculation of Hull Suction Volume in the Backflow of Cascade Angle Region
Authors: Hui Jie 
Published: August 2021

Abstract
This article uses computational fluid dynamics (CFD) method to carry out a numerical study on a rectangular high-load diffuser cascade of a ship hull with a full-blade high suction trough unit at different chord positions, and analyses the chord position and other parameters of the suction trough. The influence on the distribution law of the suction volume; the effect of the local extended suction scheme is explored through the cascade experiment. The computational domain of the numerical simulation includes the vacuum cavity inside the suction blade, and the boundary conditions are set according to the experimental conditions. The distribution law of the suction volume along the span is affected by the combined effect of the cascade flow path and the flow field of the blade cavity. Therefore, the suction surface suction groove/hole should be refined according to the specific characteristics of the three-dimensional high-load diffuser cascade flow field design.
Numerical Simulation Coupling on Fluid Flow and Heat Transfer in Nozzle and Equipment Cabin of Solid Rocket Motor during Operation Process
Authors: Ni Zheng , Wu Yue , Liu Yang , Zhu Pengfei 
Published: August 2021

Abstract
Driven by the goal of studying the temperature changes in the nozzle and equipment cabin of solid rocket motor during the whole process of ignition starting, working, cooling and decompression, this paper uses the fluid dynamics software which uses the RNG k-ε turbulence model to simulate the mixing of the fuel and oxidant and the Sutherland law to describe the viscosity of gas and air, and the controlling equation is the two-dimensional axisymmetric viscous compressible URANS equation. In this paper, the temperature field of the nozzle and equipment cabin in the working process of solid rocket motor during 0 ∼ 60s is numerically simulated, and the ground experiment is carried out. The results show that (1) the numerical simulation results are in good agreement with the ground test results, and the absolute value of the maximum error appears at the time of 60s, which is 5.9k. indicating that the numerical calculation method and heat source equivalent method established in this paper are suitable for the temperature field simulation of composite structure nozzle and equipment cabin, (2) the unsmooth surface of the nozzle formed by high temperature ablation makes the flow situation in the divergent section of the nozzle complex and affects the heat transfer coefficient of the wall contacting with the equipment cabin, (3) due to the insulation design of the equipment cabin, only a small part of the heat is transferred to the equipment cabin. During the whole working process of solid rocket motor, the temperature field of equipment cabin increases sharply at both ends and gently in the middle.
Review of state of the art in active aerodynamic control research for vehicles
Authors: Gao Wei , Kong Xinxin , Deng Zhaowen , Yu Wei , Wu Yongxing , Luo Jintao 
Published: August 2021

Abstract
Various active safety systems have been developed and applied to improve the driving safety of road vehicles under emergency scenarios. However, the functions of these active safety systems are limited due to the forces saturation between the tires and the road under high lateral accelerations or on low adhesion roads. To further enhance the safety of high-speed vehicles, the active aerodynamic control system was proposed and studied by engineers and researchers. An overview of the state of the art and present status of active aerodynamic control research for vehicles is presented in this paper. The influence of the active aerodynamic control on the dynamic properties of road vehicles, vehicle models used for active aerodynamic control systems, the control system and controller are summarized in this paper. The future research efforts are discussed. The paper is to provide some guidance for the further investigations of the active aerodynamic control system.