20211410344Low Reynolds Number Turbulence Models to Simulate the Bubble Plume Behavior with the Euler-Euler Method22This paper presents a comparative assessment of low Reynolds number k- models against standard k- model in an Eulerian framework. Three different low-Re number k- models: Launder-Sharma (LS), Yang-Shih (YS) and AbeKondoh-Nagano (AKN) have been used for the description of bubble plume behaviour in stratified water. The contribution of the gas phase movement into the liquid phase turbulence has been achieved by using the Dispersed with Bubble Induced Turbulence approach (DIS+BIT).The results reveal that the oscillation frequency of gas-liquid flow are correctly reproduced by standard k- and LS models. In fact, we found for standard K- and LS a clear dominant peak at a frequency equal to 0.1 Hz. On the other hand, YS and AKN models have predicted chaotic oscillations. The oscillation amplitude of the bubble plume predicted from LS model seems to be in good agreement with the PIV measurements of Besbes et al. (2015). However, for the standard K- model the oscillation amplitude is low. The air-water interface shows that the bubble plume mixing with the stratified water is predicted to be stronger compared to standard k- model. 110S.BesbesUniversity of Monastir, National School of Engineers of Monastir, Laboratory of Metrology and Energy Systems, Monastir, 5000, TunisiaUniversity of Monastir, National School of Engineers of Monastir, Laboratory of Metrology and Energy Systems, Monastir, 5000, Tunisiapayssoniabesbes767@gmail.comM.El HajemNational Institute of Applied Science Lyon, Laboratory of Fluid Mechanics and Acoustics, 20 Av. A. Einstein, 69621 Villeurbanne Cedex, FranceNational Institute of Applied Science Lyon, Laboratory of Fluid Mechanics and Acoustics, 20 Av. A. Einstein, 69621 Villeurbanne Cedex, Francepaysmahmoud.elhajem@insa-lyon.frH.Ben AissiaUniversity of Monastir, National School of Engineers of Monastir, Laboratory of Metrology and Energy Systems, Monastir, 5000, TunisiaUniversity of Monastir, National School of Engineers of Monastir, Laboratory of Metrology and Energy Systems, Monastir, 5000, Tunisiapayshabib.enim2017@gmail.comJ. Y.ChampagneNational Institute of Applied Science Lyon, Laboratory of Fluid Mechanics and Acoustics, 20 Av. A. Einstein, 69621 Villeurbanne Cedex, FranceNational Institute of Applied Science Lyon, Laboratory of Fluid Mechanics and Acoustics, 20 Av. A. Einstein, 69621 Villeurbanne Cedex, Francepaysjean-yves.champagne@insa-lyon.frBubble plume Computational fluid dynamics Euler-Euler modeling Hydrodynamics Low Reynolds number models Two-phase flow.[Besbes, S., M. El Hajem, H. Ben Aissia, J. Y. Champagne and J. Jay (2015) PIV measurements and Euleri-an-Lagrangian simulations of the unsteady gas-liquid flow in a needle sparger rectangular bubble column. Chemical Engineering Science 126, 560-572.##
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]A Numerical Study on the Performance of a Magnesium-Based Automotive Cooling Fan with Bead Structure22This paper presents the numerical analysis of three types of magnesium-based, axial-flow automotive cooling fans. The numerical modeling is conducted for geometrically modified fan designs with and without bead structure. The effect of geometric modifications of the fan blades on the fan performances (P-Q curve), fan efficiency, and energy efficiency is investigated using unsteady Reynolds-Averaged Navier-Stokes (URANS) equations with the sliding mesh methodology. The baseline fan having no-beads is fabricated using 3D printing technology and tested to measure the flow velocity and volumetric flow rate which shows good agreement to the numerical results. Subsequently, fans with beads are further optimized to achieve a significant increase in fan performances. To investigate the fan vibrations, modal analysis is also carried out using magnesium-alloy AZ31 as the fan material. The modal analysis gives natural frequencies of all types of fans which are beyond the fan rotational frequency and seems satisfactory. 1121K. H.HurSchool of Mechanical Engineering, Kyungpook National University, Daegu, 41566, KoreaSchool of Mechanical Engineering, Kyungpook National University, Daegu, 41566, Koreapayshor0514@naver.comB. A.HaiderSchool of Mechanical Engineering, Kyungpook National University, Daegu, 41566, KoreaSchool of Mechanical Engineering, Kyungpook National University, Daegu, 41566, Koreapaysbahaider@knu.ac.krC. H.SohnSchool of Mechanical Engineering, Kyungpook National University, Daegu, 41566, KoreaSchool of Mechanical Engineering, Kyungpook National University, Daegu, 41566, Koreapayschson@knu.ac.krAxial-flow cooling fan Bead structure CFD Fan performance Modal analysis Passive control.[Adeeb, E., A. Maqsood, A. Musthaq and C. H. Sohn. (2016) (2016). Parametric Study and Optimization of Ceiling Fan Blades for Improved Aerodynamic Performance. Journal of Applied Fluid Mechanics 9(6): 2905-16.##
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]CFD Analysis and Optimization of Effect of Shroud with Multi-outlets on Airflow Uniformity in a Frost-Free Refrigerator22The shroud is a key component of the frost-free refrigerator and its geometric parameters have great influence on the aerodynamic performance of the whole system. Previous researches mainly focused on the effect of other components, such as the fan, shelves, or plate-evaporator. In this paper, the influence of the shroud with multi-outlets on the flow distributions of a frost-free refrigerator is studied thoroughly with the help of Computational Fluid Dynamics (CFD) tools. A 1/2 3-D CFD model is developed, where the verification of turbulence models and mesh independence tests are performed by comparing the mass flow rate obtained by different model configurations. The standard k-epsilon is deemed as the most suitable turbulence model choice and a mesh with Fine level is considered as mesh independence. To obtain the boundaries of the developed CFD model, an airflow velocity test rig is built and constructed. To convert the measured data to CFD model, Structural Response Vector (SRV) method is implemented for velocity profile fitting, and the fitted surface is assigned by User Defined Functions (UDF) macros in simulations. A series of simulations are carried out with the developed model, and the results indicates that no streamline in the middle two cavities of the original freezer compartment and the airflow velocities at the three outlets of the investigated shroud show a certain difference. To optimize the flow distribution, the agent model based on the BP neural network is established, in which four critical parameters of the shroud are adopted as design variables. The results show that the velocity streamlines in the middle two cavities are significantly increased after optimization and the value of the mean square error model constructed in optimization has a reduction of 61.09% compared with the original design.3748X. F.DuSchool of Mechanical Engineering, Southeast University, Nanjing 211189, ChinaSchool of Mechanical Engineering, Southeast University, Nanjing 211189, Chinapaysduxiaofei@seu.edu.cnC. Y.ZongSchool of Mechanical Engineering, Dalian University of Technology, Dalian 116023, ChinaSchool of Mechanical Engineering, Dalian University of Technology, Dalian 116023, Chinapayszong_chaoyong@mail.dlut.edu.cnQ. D.FuSchool of Mechanical Engineering, Southeast University, Nanjing 211189, ChinaSchool of Mechanical Engineering, Southeast University, Nanjing 211189, Chinapaysqidi_fu@163.comJ. R.ZhangSchool of Mechanical Engineering, Southeast University, Nanjing 211189, ChinaSchool of Mechanical Engineering, Southeast University, Nanjing 211189, Chinapayszhangjr@seu.edu.cnShroud CFD simulation Test rig Airflow uniformity Optimization.[Abe, K., M. Nishida, A. Sakurai, Y. Ohya, H. Kihara, E. Wada and K. Sato (2005). Experimental and numerical investigations of flow fields behind a small wind turbine with a flanged diffuser. Journal of Wind Engineering and Industrial Aerodynamics 93(12), 951-970.##
Abu-Thuraia, H., C. Aygun, M. Paraschivoiu and M. A. Allard (2018). Computational fluid dynamic analysis of roof-mounted vertical-axis wind turbine with diffuser shroud, flange, and vanes. Transactions of the Canadian Society for Mechanical Engineering 42(4), 404-415.##
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]Reacting Flow Simulations of a Dual Throat-Dual Fuel Thruster22Numerical simulation of the supersonic turbulent reacting flow field in a dual throat- dual fuel rocket thrust chamber is presented. Future single stage to orbit and high lift space transportation missions aspire a reliable, efficient, and cost-effective propulsion systems. The dual throat-dual fuel concept is a simple altitude compensating propulsion alternative with reusable possibilities. Turbulent reacting supersonic flow field emanating from independent thrust chambers needs to be resolved for a better understanding of the flow structures and design modifications for the performance improvement. The operation of a dual throat nozzle brings about a unique shock train in reacting supersonic flow. Two-dimensional axis-symmetric compressible reacting flow field has been solved using HLLC (Harten, Lax, van Leer, with Contact wave) scheme based finite volume Riemann solver with multi-step finite rate chemistry model for hydrocarbon/hydrogen-oxygen combustion. The computational procedure has been validated with experimental data for species distribution of a coaxial supersonic combustor. Chemical species distribution in the supersonic free shear layer is analyzed in detail to explore the nature of active reaction zones in the flow field. 4959S.JayakrishnanDepartment of Aerospace Engineering, Indian Institute of Space Science and Technology, Thiruvananthapuram - 695 547, Kerala, IndiaDepartment of Aerospace Engineering, Indian Institute of Space Science and Technology, Thiruvananthapuram - 695 547, Kerala, Indiapaysjayakrishnans9@gmail.comM.DeepuDepartment of Aerospace Engineering, Indian Institute of Space Science and Technology, Thiruvananthapuram - 695 547, Kerala, IndiaDepartment of Aerospace Engineering, Indian Institute of Space Science and Technology, Thiruvananthapuram - 695 547, Kerala, Indiapaysdeepunss@gmail.comAdvection Upstream Splitting Method Single-stage to orbit mission Reusable propulsion systems Turbulent-reacting flows Finite-rate chemistry model.[Cheng, T., J. Wehrmeyer, R. Pitz, J. R. O. Jarret and G. Northam (1991). Finite-rate chemistry effects in a Mach 2 reacting flow, in ‘27th Joint Propulsion Conference. 2320.##
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]Design of an Axial Transonic Rotor by Modified Spanwise Loading Distribution22Improving the aerodynamic performance of the transonic fan in a turbofan engine can be beneficial for both the fuel consumption and maneuverability of an airplane. Deep insight into the supersonic aerodynamics is needed for the simultaneous improvement of all operating parameters of a transonic rotor, including the pressure ratio, efficiency, and surge margin. A design method was developed for an axial transonic rotor by using a combination of radial equilibrium theory, the free vortex method, and a distributed span-wise diffusion factor. The loading distribution obtained by this method was the highest in the hub section and gradually decreased in the tip section. To evaluate the method, a transonic rotor was designed using the geometric parameters and operating conditions of NASA rotor 67. A code was developed to determine a geometry for the new rotor and to modify it. The code was coupled with a RANS flow solver for 3D modification of the new designed rotor. Only standard multi- and double-circular arc airfoils were applied in different radial sections of the new rotor with no blade profile optimization. The results of the RANS equations solution for the new designed rotor showed 1.5% higher efficiency, 3% higher pressure ratio, and more than 1.5 times larger operating range in comparison to NASA rotor 67. The new designed method seems to be an efficient approach that not only improved the efficiency and pressure ratio but also increased the operating range of an axial transonic rotor.6172A.ShahsavariDepartment of Mechanical Engineering, Isfahan University of Technology, Isfahan 8415683111, IranDepartment of Mechanical Engineering, Isfahan University of Technology, Isfahan 8415683111, Iranpaysshahsavari.ali@ut.ac.irM.Nili-AhmadabadiDepartment of Mechanical Engineering, Isfahan University of Technology, Isfahan 8415683111, IranDepartment of Mechanical Engineering, Isfahan University of Technology, Isfahan 8415683111, Iranpaysm.nili@cc.iut.ac.irE.ShiraniDepartment of Mechanical Engineering, Isfahan University of Technology, Isfahan 8415683111, IranDepartment of Mechanical Engineering, Isfahan University of Technology, Isfahan 8415683111, Iranpayseshirani@cc.iut.ac.irK.Chun KimPusan National University, Busan 609-735, South KoreaPusan National University, Busan 609-735, South Koreapayskckim@pusan.ac.krAxial Fan De-Haller number Numerical simulation Radial equilibrium Rotor design procedure.[Benzakein, M. J. (2014). What does the future bring? A look at technologies for commercial aircraft in the years 2035–2050. Propulsion and Power Research 3(4), 165–174.##
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Yang, Y., A. Sciacchitano, L. L. M. Veldhuis and G. Eitelberg (2018). Analysis of propeller-induced ground vortices by particle image velocimetry. Journal of Visualization 21, 39–55##]Numerical Study of Fluidic Thrust Vector Control Using Dual Throat Nozzle22Compared to a variety of mechanical vectoring nozzles, fluidic vectoring nozzles possess more research value nowadays. The dual throat nozzle is gradually developing into an outstanding technology to handle supersonic and hypersonic aircraft deflections. Three-dimensional, steady, compressible, and viscous flows in rectangular dual throat nozzles are numerically investigated by resolving Reynolds-averaged Navier-Stokes equations and shear stress transport k-omega turbulence model. Computational fluid dynamics results are verified against the existing experimental data, where a good consistency is gained. The impacts of nozzle pressure ratio, injection-to-mainstream momentum flux ratio, and setup angle of the slot injector on the systemic performance are examined. Useful conclusions are summarized for engineering designers. Firstly, pitching angles decline along with an increasing nozzle pressure ratio, while systemic thrust ratio and thrust efficiency increase. Secondly, thrust vector angles enlarge with an increase of the injection-to-mainstream momentum flux ratio, whereas both systemic thrust ratio and thrust efficiency decay. Finally, the setup angle of the slot injector impacts the systemic performance remarkably. Although the pitching angle for the setup angle of 120° is highest, comprehensive characteristics in terms of systemic thrust efficiency and systemic thrust ratio for the setup angle of 150° are more excellent.7387K. X.WuMechanical Engineering, Andong National University, Andong, 760-749, South KoreaMechanical Engineering, Andong National University, Andong, 760-749, South Koreapayskexin@pyunji.andong.ac.krT. H.KimMechanical Engineering, Andong National University, Andong, 760-749, South KoreaMechanical Engineering, Andong National University, Andong, 760-749, South Koreapayskimth@pyunji.andong.ac.krH. D.KimMechanical Engineering, Andong National University, Andong, 760-749, South KoreaMechanical Engineering, Andong National University, Andong, 760-749, South Koreapayskimhd@anu.ac.krVector control Jet deflection Shock wave Compressible flow Internal flow.[Bellandi, E. G. and A. J. Slippey (2009). Preliminary analysis and design enhancements of a dual-throat FTV nozzle concept. In 39th AIAA fluid dynamics conference, 3900.##
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Deere, K. A. (2003). Summary of fluidic thrust vectoring research conducted at NASA Langley Research Center. In 21st AIAA applied aerodynamics conference, 3800. ##
Deere, K. A., J. D. Flamm, B. L. Berrier and S. K. Johnson (2007). Computational study of an axisymmetric dual throat fluidic thrust vectoring nozzle concept for supersonic aircraft application. In 43rd AIAA/ASME/SAE/ASEE joint propulsion conference & exhibit, 5085.##
Deere, K. A., B. L. Berrier, J. D. Flamm and S. K. Johnson (2003). Computational study of fluidic thrust vectoring using separation control in a nozzle. In 21st AIAA applied aerodynamics conference, 3803.##
Deng, R. Y. and H. D. Kim (2015). A study on the thrust vector control using a bypass flow passage. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 229(9), 1722-1729.##
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Flamm, J. D., K. A. Deere, B. L. Berrier and S. K. Johnson (2006). Design enhancements of the two-dimensional, dual throat fluidic thrust vectoring nozzle concept. In 3rd AIAA flow control conference, 3701.##
Flamm, J. D., K. A. Deere, M. L. Mason, B. L. Berrier and S. K. Johnson (2007). Experimental study of an axisymmetric dual throat fluidic thrust vectoring nozzle for a supersonic aircraft application. In 43rd AIAA/ASME/SAE/ASEE joint propulsion conference & exhibit, 5084.##
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Raman, S. K., K. X. Wu, T. H. Kim and H. D. Kim (2020). Effects of flap on the reentry aerodynamics of a blunt cone in the supersonic flow. International Journal of Mechanical Sciences 176, 105396.##
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Tao, J. Y., Z. Lin, C. J. Ma, J. H. Ye, Z. C. Zhu, Y. Li and W. Mao (2020). An experimental and numerical study of regulating performance and flow loss in a v-port ball valve. Journal of Fluid Engineering 142(2), 172-182.##
Vignesh, R. P. S., S. Das and H. D. Kim (2016). Influence of vortex generator on cylindrical protrusion aerodynamics at various Mach numbers. Aerospace Science and Technology 58: 267-274.##
Vignesh, R. P. S., T. H. Kim and H. D. Kim (2019). Numerical study on shock train characteristics in divergent channels. Journal of Applied Fluid Mechanics 13(4): 267-274.##
Wang, Y. S., J. L. Xu and S. Huang (2017). Study of starting problem of axisymmetric divergent dual throat nozzle. Journal of Engineering of Gas Turbines and Power 139, 1-13.##
Wang, Y. S., J. L. Xu, S. Huang, Y. C. Lin and J. J. Jiang (2019a). Computational study of axisymmetric divergent bypass dual throat nozzle. Aerospace Science and Technology 86, 177-190.##
Wang, Y. S., J. L. Xu, S. Huang, Y. C. Lin and J. J. Jiang (2019b). Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234(3), 563-572.##
Wu, K. X. and H. D. Kim (2019a). Fluidic thrust vector control using shock wave concept. Journal of the Korean Society of Propulsion Engineers 23(4), 10-20.##
Wu, K. X. and H. D. Kim (2019b). Numerical study on the shock vector control in a rectangular supersonic nozzle. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233(13), 4943-4965.##
Wu, K. X. and H. D. Kim (2019c). Study on fluidic thrust vector control based on dual-throat concept. Journal of the Korean Society of Propulsion Engineers 23(1), 24-32.##
Wu, K. X., G. Zhang, T. H. Kim and H. D. Kim (2020a). Numerical parametric study on three-dimensional rectangular counter-flow thrust vectoring control. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering.##
Wu, K. X., H. D. Kim and Y. Z. Jin (2018). Fluidic thrust vector control based on counter-flow concept. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233(4): 1412-1422.##
Wu, K. X., S. K. Raman, R. P. S. Vignesh, G. Zhang and H. D. Kim. (2020b). Effect of the wall temperature on Mach stem transformation in pseudo-steady shock wave reflections. International Journal of Heat and Mass Transfer 147: 118927.##
Wu, K. X., T. H. Kim and H. D. Kim. (2020c). Theoretical and numerical analyses of aerodynamic characteristics on shock vector control. Journal of Aerospace Engineering 33(5), 1-26.##
Wu, K. X., T. H. Kim, J. K. James and H. D. Kim. (2020d). Assessment of the counter-flow thrust vector control in a three-dimensional rectangular nozzle. Journal of the Korean Society of Propulsion Engineers 24(1), 34-46.##
Wu, K. X., Y. Z. Jin and H. D. Kim (2019). Hysteresis behaviors in counter-flow thrust vector control. Journal of Aerospace Engineering 32(4), 1-9.##
Yagle, P. J., D. N. Miller, K. B. Ginn and J. W. Hamstra (2001). Demonstration of fluidic throat skewing for thrust vectoring in structurally fixed nozzles. Journal of Engineering of Gas Turbines and Power 123(3), 502–507.##
]Analysis of Unsteady Flow Structures in a Centrifugal Impeller Using Proper Orthogonal Decomposition22The occurrence and development of the dominant unsteady flow structures in a vanless centrifugal pump impeller are revealed by the proper orthogonal decomposition (POD) method. The pressure and velocity data of four radial surfaces is selected as the variables of decomposition. The results show that this method is beneficial to the analysis of flow field when there is no strong interaction of flow structures. When the flow rate starts to decrease from the design flow rate, unstable flow phenomenon such as flow separation and wake begin to appear and develop in the impeller. The POD analysis reveals the influence of the main unsteady structures on the flow field when there is no mixed or have little interaction among flow structures. It outlines the development of flow separation near the suction side of impeller and the wake near the trailing edge as the flow rate changes. However, the flow field inside the impeller becomes more and more complex as the operation condition is far away from the design condition, which needs to be combined with other methods to better analyze the flow field.89101Z. Y.LiaoSchool of Energy and Power Engineering, University of Shanghai for Science and Technology, No. 516 Jungong Road, Shanghai, 200093, ChinaSchool of Energy and Power Engineering, University of Shanghai for Science and Technology, No. 516 Jungong Road, Shanghai, 200093, Chinapaysusst_lzy@163.comJ.YangSchool of Energy and Power Engineering, University of Shanghai for Science and Technology, No. 516 Jungong Road, Shanghai, 200093, ChinaSchool of Energy and Power Engineering, University of Shanghai for Science and Technology, No. 516 Jungong Road, Shanghai, 200093, Chinapaysyangjun@usst.edu.cnX. H.LiuSchool of Aeronautics and Astronautics, Shanghai Jiao Tong University, No. 500 Donchuan Road, Shanghai 200240, ChinaSchool of Aeronautics and Astronautics, Shanghai Jiao Tong University, No. 500 Donchuan Road, Shanghai 200240, Chinapaysxiaohua-liu@sjtu.edu.cnW. L.HuSchool of Energy and Power Engineering, University of Shanghai for Science and Technology, No. 516 Jungong Road, Shanghai, 200093, ChinaSchool of Energy and Power Engineering, University of Shanghai for Science and Technology, No. 516 Jungong Road, Shanghai, 200093, Chinapaysmilehu117@163.comX. R.DengSchool of Energy and Power Engineering, University of Shanghai for Science and Technology, No. 516 Jungong Road, Shanghai, 200093, ChinaSchool of Energy and Power Engineering, University of Shanghai for Science and Technology, No. 516 Jungong Road, Shanghai, 200093, Chinapaysdxr3839719@163.comProper orthogonal decomposition RANS simulation Unsteady flow structure Centrifugal pump impeller.[Bistrian, D. A. and R. F. Susan-Resiga (2016). Weighted proper orthogonal decomposition of the swirling flow exiting the hydraulic turbine runner. Applied Mathematical Modelling 40 (5), 4057-4078.##
Brun, K. and R. Kurz (2005). Analysis of Secondary Flows in Centrifugal Impellers. International Journal of Rotating Machinery 2005 (1), 45-52. ##
Cheah, K. W., T. S. Lee, S. H. Winoto and Z. M. Zhao (2007). Numerical Flow Simulation in a Centrifugal Pump at Design and Off-Design Conditions. International Journal of Rotating Machinery , 83641.##
Christensen, E. A., M. Brøns and J. N. Sørensen (1999). Evaluation of Proper Orthogonal Decomposition--Based Decomposition Techniques Applied to Parameter-Dependent Nonturbulent Flows. SIAM Journal on Scientific Computing 21 (4), 1419-1434. ##
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]Effect of Pipeline External Geometry on Local Scour and Self-Burial Time Scales in Current22Changes in the external geometry of the pipeline laid on the erodible beds may affect the local scour around pipe. If the scouring process below the pipe is accelerated, the pipe buries on the bed (known as self-burial of the pipe) and can be used as a cheap alternative to mechanical trench digging. In this study, the effect of changes in the external geometry of the pipe in order to accelerate the scouring and self-burial pipe processes by spoiler and piggy back under unidirectional flow on the erodible bed is investigated. The results showed that the time scale of self-burial process is less than that of the scouring process. At the angles of 180, 135 and 225°, the Spoiler and piggy back reduced the time scale of self-burial and scouring process and increased the scour and self-burial depths, as well as the lee erosion length as compared with the simple pipe. At angles of 90 and 270°, the scale time of scour and self-burial processes are increased, the scour and self-burial depths and the lee erosion length are decreased as compared with the simple pipe. It can be concluded that the performance of piggy back is similar to the spoiler, therefore, they are of similar application and could be a suitable alternative for the spoiler.103115M.DamroudiDepartment of Civil Engineering, Najafabad Branch, Islamic Azad University, Najafabad, Isfahan, 8514143131, IranDepartment of Civil Engineering, Najafabad Branch, Islamic Azad University, Najafabad, Isfahan, 8514143131, Iranpaysmojtaba.damroudi@yahoo.comK.EsmailiDepartment of Water, Science and Engineering, Ferdowsi University of Mashhad, Mashhad, Khorasan Razavi ,9177948974, IranDepartment of Water, Science and Engineering, Ferdowsi University of Mashhad, Mashhad, Khorasan Razavi ,9177948974, Iranpaysesmaili@um.ac.irS. H.RajaieKhorasan Razavi Agriculture and Natural Resources Research and Education Center, Mashhad, Khorasan Razavi ,6641691659, IranKhorasan Razavi Agriculture and Natural Resources Research and Education Center, Mashhad, Khorasan Razavi ,6641691659, Iranpaysshrajaie@yahoo.comLocal scour Pipeline Spoiler Piggy back Self-Burial.[Abbasi, S., M. Masoomi and S. A. Arjmandi, (2018). Impact of a Single Spoiler on Scouring Depth Status Beneath a River Crossing Inclined Pipeline. Engineering, Technology & Applied Science Research 8(5), 3316-3320.##
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]Investigation on Stability and Galloping Characteristics of Iced Quad Bundle Conductor22The stability and galloping characteristics of iced quad bundle conductor are studied in this paper. Firstly, the aerodynamic coefficients of iced quad bundle conductor and single conductor under four different working conditions are obtained by wind tunnel test. Secondly, the equivalent aerodynamic coefficients at the central axis of the quad bundle conductor are obtained, and the equivalent aerodynamic coefficients are compared with the aerodynamic coefficients of each sub-conductor of the quad bundle conductor. Then, based on the Den Hartog instability mechanism and Nigol instability mechanism, the stable and unstable range of the equivalent coefficients of the quad bundle conductor are analyzed. Finally, the galloping characteristics of the quad bundle conductor are studied by combining with the equivalent aerodynamic coefficients at the central axis of quad bundle conductor. The results of the wind tunnel test show that the aerodynamic coefficients increase with the decreasing of the wind speed. The stability analyses show that the higher the wind speed is, the smaller the Den Hartog coefficient is the easier the Den Hartog’ galloping would occur. Furthermore, the higher the wind speed is, the smaller the Nigol coefficient is, the easier the Nigol’ galloping would occur. The analysis of galloping characteristics shows that when the conductor is located at stable state, the displacement in the y-axis direction would be much greater than the displacement in the z-axis direction.117129X.LiuState Key Laboratory of Mountain Bridge and Tunnel Engineering, Chongqing Jiaotong University, Chongqing, 400074, ChinaState Key Laboratory of Mountain Bridge and Tunnel Engineering, Chongqing Jiaotong University, Chongqing, 400074, Chinapayscqdxlxh@126.comG.MinSchool of Civil Engineering, Chongqing Jiaotong University, Chongqing, 400074, ChinaSchool of Civil Engineering, Chongqing Jiaotong University, Chongqing, 400074, Chinapays942070703@qq.comC.SunSchool of Civil Engineering, Chongqing Jiaotong University, Chongqing, 400074, ChinaSchool of Civil Engineering, Chongqing Jiaotong University, Chongqing, 400074, Chinapayssunces@hnu.edu.cnM.CaiSchool of Architecture and Civil Engineering, Chengdu University, Chengdu, 610106, ChinaSchool of Architecture and Civil Engineering, Chengdu University, Chengdu, 610106, Chinapaysmq.cai@foxmail.comQuad bundle conductor Aerodynamic coefficients Stability galloping Wind tunnel test. [Braun, A. L. and A. M. Awruch (2005). Aerodynamic and aeroelastic analysis of bundled cables by numerical simulation. Journal of Sound and Vibration 284(1-2), 51-73.##
Cai, M., Q. Xu, L. Zhou, X. Liu and H. Huang (2019) Aerodynamic Characteristics of Iced 8-bundle Conductors under Different Turbulence Intensities. KSCE Journal of Civil Engineering 23(6). ##
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Zhang, Q., N. Popplewell and A. H. Shah (2000). Galloping of bundle conductor. Journal of Sound and Vibration 234(1), 115-134.##]Experimental Investigation of Multi-Jet Air Impingement in Various Conditions and Analysis using Desirability Based Response Surface Methodology22This experimental analysis encapsulates the influence of Reynolds number (Re), diameter of nozzle, height to diameter (H/D) ratio and position of nozzle such as in-line and staggered over the responses heat transfer coefficient, temperature and Nusselt number of a hot flat plate exposed to cooling by multi-jet air impingement. For this analysis, a 15 x 10 cm flat plate is being heated using a heating coil having a heat flux of 7666.67 W/m2 which is maintained as constant through entire experiment. An H/D ratio of 2D, 4D and 6D is considered along with pipe diameters of 4, 6 and 8 mm and Reynolds number are changed between 18000 to 22000. Experimental design was performed with response surface methodology based central composite design. For all output responses, a quadratic model is chosen for analysis and a second order mathematical model is evolved for predicting with a higher R2 value. Desirability analysis is performed for multi-objective optimization and the optimum input parameters obtained are Reynolds no. of 20347, pipe diameter of 8 mm, H/D ratio of 2 and in-line nozzle position with the maximum heat transfer coefficient of 189.411 W/m2 K, Nusselt number of 28.8712 and minimum temperature of 56.983°C. Optimum condition-based confirmation experiments result in enhanced Nusselt number and heat transfer coefficient.131145P.ChandramohanMisrimal Navajee Munoth Jain Engineering College, Chennai, Tamilnadu, IndiaMisrimal Navajee Munoth Jain Engineering College, Chennai, Tamilnadu, Indiapaysdrmpchandramohan@gmail.comS. N.MurugesanRajalakshmi Engineering College, Chennai, Tamilnadu, IndiaRajalakshmi Engineering College, Chennai, Tamilnadu, Indiapayssnmurugesan@rediffmail.comS.ArivazhaganSt. Joseph’s College of Engineering, Chennai, Tamilnadu, IndiaSt. Joseph’s College of Engineering, Chennai, Tamilnadu, Indiapaysarivazhagan67@gmail.comJet impingement cooling Heat transfer Response surface methodology Nusselt Number Staggered and inline position Reynolds number.[Bahrampoury, R., A. Behbahaninia, A. Shadaram and E. Taghdiri (2009). Comparison between In-line and Staggered Arrangements in Heat Recovery Steam Generators. Proceedings of the Fourth International Exergy, Energy and Environment Symposium April 19-23, AUS, Sharjah, UAE.##
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]A Simple Passive Device for the Drag Reduction of an Ahmed Body22In this paper, a simple passive device is proposed for drag reduction on the 35° Ahmed body. The device is a simple rectangular flap installed at the slant surface of the model to investigate the effect of slant volume, formed between the device and the slant surface, on the flow behaviour. The slant volume can be varied by changing the flap angle. This investigation is performed using the FLUENT software at a Reynolds number of 7.8 ×〖10〗^5 based on the height of the model. The SST k-omega model is used to solve the Navier-stokes equations. It is found that this passive device influences the separation bubbles created inside the slant volume and provides a maximum drag reduction of approximately 14% at the flap angle of 10°. Moreover, the device delays the main separation point, which changes the flow conditions at the back of the model. The drag reduction was found to mainly dependent on the suppression of the separation bubbles formed inside the slant volume, which leads to faster pressure recovery. The cause of this pressure recovery is found to be the reduction in recirculation length and width. Also, the addition of a flap reduces the turbulent kinetic energy, which lessened the wake entrainment in the recirculation region, leading to a drag reduction. Also, it hinders the formation of horseshoe vortex that provides a pressure recovery and influence the wake width. However, the investigation also reveals that this device does not reduce the induced drag due to longitudinal vortex from the side edges.147164N. A.SiddiquiOntario Tech University, Oshawa, Ontario, L1G0C5, CanadaOntario Tech University, Oshawa, Ontario, L1G0C5, Canadapaysnaseeb.siddiqui@ontariotechu.netM. A.ChaabOntario Tech University, Oshawa, Ontario, L1G0C5, CanadaOntario Tech University, Oshawa, Ontario, L1G0C5, Canadapaysmartin.agelin-chaab@uoit.caAhmed body Passive drag reduction Bluff body Backflow reduction road vehicles Rectangular flap device CFD. [Ahmed, S. R., G. Ramm and G. Faltin (1984). Some Salient Features Of The Time-Averaged Ground Vehicle Wake. SAE Transactions 93(2), 473–503.##
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]A New Modeling Method to Reveal Pumping Mechanism of Turbomolecular Pump22In order to meet the calculating requirements of high speed and miniaturized turbomolecular pump (TMP), a new modeling method is proposed for a rotor-stator row. In the same Cartesian coordinate system, the analytical equations of blade row are derived according to the real three-dimensional geometric model. A self-defining procedure is written to simulate the flow of gas molecules in TMP based on test particle Monte Carlo method. The procedure not only can calculate transmission probability of rotor row, stator row and a rotor-stator row but also evaluate the pumping performance of different blade parameters. The simulation results and known experimental data have a good agreement to confirm the feasibility of presented modeling method. The flow analysis shows that molecules at outlet of rotor row tend to accumulate in large radius and this phenomenon is obvious for high rotational speed. The differences were found between a single-stage row and a rotor-stator row. In rotor row, the molecular density at the rear blades is the highest. This is beneficial for pumping speed of TMP because 57% of molecules at the rear blades are likely to reach outlet. This will provide a direction for the structural optimization design of the blades in the future. In stator row, the molecular density reaching outlet does not significantly increase with the increase of blade velocity ratio, which indicates that the stator row is mainly used to increase the pressure ratio of TMP. The analysis of molecular density in each region reveals the pumping mechanism of TMP.165173K.SunSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, ChinaSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, Chinapayssunk08@qq.comS. W.ZhangSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, ChinaSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, Chinapayszhangsw-neu@163.comF.HanSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, ChinaSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, Chinapayshanfeng1993s@163.comF.ZhaoSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, ChinaSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, Chinapays851347819@qq.comZ. J.ZhangSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, ChinaSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, Chinapayszhjzhang@mail.neu.edu.cnJ.HanSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, ChinaSchool of Mechanical Engineering & Automation, Northeastern University, Shenyang, Liaoning, 110819, Chinapaysjhan@mail.neu.edu.cnPumping mechanism Flow analysis Turbomolecular pump Transmission probability Rotor-stator row Monte Carlo method.[Amoli, A. and S. M. Hosseinalipour (2004). A continuum model for pumping performance of turbomolecular pumps in all flow regimes. Vacuum 75(4), 361-366.##
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]Numerical Investigation on Film Cooling Mechanism with Different Coolant Delivery Configurations22Kidney vortex has significant impact on film cooling effectiveness, and different kinds of film cooling hole geometry and configuration are developed to weaken or eliminate kidney vortex. This paper is focus on the mechanism of eliminating kidney vortex by optimizing the coolant delivery configuration, seven coolant delivery configurations are designed to conduct a comparative study with different blowing ratios. At high blowing ratio, the strong kidney-shaped vortex is formed outside the film cooling hole causing the low cooling effectiveness for β≤0˚. For β>0˚, the coolant ejection interacts with mainstream hot gas, and the coolant gas in low momentum region of upstream bypasses the large jet momentum coolant to attach film cooling surface at downstream. It increases the distance between the vortexes to weaken mutually reinforcing effect, resulting in high film cooling effectiveness. When the blowing ratio is 1.5, the average adiabatic film cooling effectiveness of β=+15˚ and β=+30˚ is increased by about 130% and 70% compared to case of β=-60˚, respectively.175185Y. T.JiangCollege of Power and Energy Engineering, Harbin Engineering University, Harbin, 150001, ChinaCollege of Power and Energy Engineering, Harbin Engineering University, Harbin, 150001, Chinapaysjiangyuting07314@126.comH. F.DengCollege of Power and Energy Engineering, Harbin Engineering University, Harbin, 150001, ChinaCollege of Power and Energy Engineering, Harbin Engineering University, Harbin, 150001, Chinapays652286297@qq.comX. L.YouCollege of Power and Energy Engineering, Harbin Engineering University, Harbin, 150001, ChinaCollege of Power and Energy Engineering, Harbin Engineering University, Harbin, 150001, Chinapays252249319@qq.comH. J.ZhaoCollege of Power and Energy Engineering, Harbin Engineering University, Harbin, 150001, ChinaCollege of Power and Energy Engineering, Harbin Engineering University, Harbin, 150001, Chinapays849431065@qq.comG. Q.YueCollege of Power and Energy Engineering, Harbin Engineering University, Harbin, 150001, ChinaCollege of Power and Energy Engineering, Harbin Engineering University, Harbin, 150001, Chinapaysguoqiangyue_heu@126.comFilm cooling Adiabatic cooling effectiveness Kidney vortex Coolant delivery configuration.[Barlow, D. N. and Kim, Y. W (1995). Effect of surface roughness on local heat transfer and film cooling effectiveness. International Gas Turbine and Aeroengine Congress and Exposition, 95-GT-14.##
Bons, J. P., C. D. MacArthur and R. B. Rivir (1996). The effect of high free-stream turbulence on film cooling effectiveness. Journal of Turbomachinery 118(4), 814–825.##
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Burd, S. W. and T. W. Simon (1997). The influence of coolant supply geometry on film coolant exit flow and surface adiabatic effectiveness. International Gas Turbine and Aeroengine Congress and Exhibition, 97-GT-25.##
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]Effect of Temporal Modulation on the Local Kinematic Process of Two-Dimensional Chaotic Flow: A Numerical Analysis22In this work, a numerical analysis based on CFD method is carried out to examine an unsteady laminar flow of Newtonian fluids in a two-dimensional simulation of a mixer, which is composed of two rods inside a moving cylindrical tank. Three stirring protocols are considered: Non-modulated “NM”, Continuously modulated “CM” and non-continuously modulated “ALT” by using the dynamic mesh technique and user defined functions “UDF’s” for the velocity profiles. The chaotic advection is obtained by temporal modulation of the rotational velocity of the cylinder and the rods to enhance the mixing of the fluid for very low Reynolds number. For this purpose, we applied the Poincaré map as a reliable mathematic tool to check mixing quality by tracking particles inside the fluid domain. Additionally, we investigated the evolution of local flow proprieties such as rotation rate, deformation rate and elongation rate at different time periods in order to see the effect of temporal modulation on the fluid kinematics. Among the considered protocols, the results of the mentioned simulation showed that it is possible to obtain a chaotic advection only for non-continuously modulated protocol which enhance mixing fluid efficiency.187199M.TelhaDepartment of Matter Sciences, Laghouat University, Laghouat, 3000, AlgeriaDepartment of Matter Sciences, Laghouat University, Laghouat, 3000, Algeriapaystelhamostefa@gmail.comM.BachiriDepartment of Matter Sciences, Laghouat University, Laghouat, 3000, AlgeriaDepartment of Matter Sciences, Laghouat University, Laghouat, 3000, Algeriapaysmabach73@yahoo.frY.LasbetLDMM Laboratory, Ziane Achour University of Djelfa, 17000 Djelfa, AlgeriaLDMM Laboratory, Ziane Achour University of Djelfa, 17000 Djelfa, Algeriapayspeeryahia@yahoo.frT. T.NaasLDMM Laboratory, Ziane Achour University of Djelfa, 17000 Djelfa, AlgeriaLDMM Laboratory, Ziane Achour University of Djelfa, 17000 Djelfa, Algeriapaystoufiknaas@gmail.comActive mixer Poincaré map Deformation Rotation Elongation Chaotic advection Unsteady flow.[Aref, H. (1984). Stirring by chaotic advection. J FluidMech 143, 1-21.##
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]Impact of a Tapered Design in the Performance of Diffusion Flame Reactors22Several research projects developed processes for precise nanoparticle positioning with high production rates. Among the gas phase manipulation strategies, the study of the inertial properties received special attention for the fabrication of nanostructured systems. In particular, aerodynamic focusing technique has allowed particles concentration onto a single streamline, improving collimated particle beam formation and opening new perspectives for nanoparticles production in the gas phase. In this paper, the influence of the reactor design was investigated, particularly in respect to the gas phase characteristics, aiming to improve the nanoparticles focusing. It was observed that a concentrated beam can be obtained in the new tapered reactor design without significantly affect the production rate and temperature profile. In addition, the coupling of aerodynamic lenses to the tapered reactor was also investigated, showing that the flow can be better focused at the cost of an increase in the average temperature and pressure drop.201214A. C. KlemzChemical Engineering Program, Federal University of Santa Catarina, 88040-970 Florianópolis, SC, BrazilChemical Engineering Program, Federal University of Santa Catarina, 88040-970 Florianópolis, SC, Brazilpaysanacarolinek@gmail.comÉ. FontanaChemical Engineering Program, Federal University of Paraná, 81531-990 Curitiba, PR, BrazilChemical Engineering Program, Federal University of Paraná, 81531-990 Curitiba, PR, Brazilpayseliton.fontana@ufpr.brA. A. U. de SouzaChemical Engineering Program, Federal University of Santa Catarina, 88040-970 Florianópolis, SC, BrazilChemical Engineering Program, Federal University of Santa Catarina, 88040-970 Florianópolis, SC, Brazilpaysantonio.augusto.souz@ufsc.brS. M. A. G. U. de SouzaChemical Engineering Program, Federal University of Santa Catarina, 88040-970 Florianópolis, SC, BrazilChemical Engineering Program, Federal University of Santa Catarina, 88040-970 Florianópolis, SC, Brazilpaysselene.souz@ufsc.brDiffusion flame reactor Computational fluid dynamics Combustion Nanoparticle focusing Aerodynamic lens system.[Araoye, A. A., H. M. Badr and W. H. Ahmed (2017). Investigation of flow through multi-stage restricting orifices. Annals of Nuclear Energy 104, 75–90. ##
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]Numerical Study of Single-Hole and Multi-Holes Orifice Flow Parameters22Importance of accurate fluid flow measurement in industry is crucial especially today with rising energy prices. There is no ideal measuring instrument due to numerous errors occurring during process of physical quantities measurement but also due to specific requirements certain instruments have like fluid type, installation requirements, measuring range etc. Each measuring instrument has its pros and cons represented in accuracy, repeatability, resolution, etc. Conventional single-hole orifice (SHO) flow meter is a very popular differential-pressure-based measuring instrument, but it has certain disadvantages that can be overcame by multi-holes orifice (MHO) flow meter. Having this in mind, the aim of this paper is to help gain more information about MHO flow meters. Both SHO and MHO gas (air) flow meters with same total orifice area and the pipe area ratio β were numerically studied and compared using computational fluid dynamics (CFD). Simulation results of 16 different orifices with four different β (0.5, 0.55, 0.6 and 0.7) were analysed through pressure drop and singular pressure loss coefficient. Standard k-ε turbulence model was used as a turbulence model. Beside singular pressure loss coefficient, pressure recovery as well as axial velocity for both the SHO and MHO were reported. Results showed lower (better) singular pressure loss coefficient and pressure drop as well as quicker pressure recovery in favour of the MHO flow meters. Also, centreline axial velocity results were lower for MHO compared to corresponding SHO. CFD simulation results were verified by experimental results where air was used as a working fluid. The influence of geometrical and flow parameters on singular pressure loss coefficient was also reported and results showed that MHO hole distribution did not have significant influence on singular pressure loss coefficient. 215226M.ĐurđevićDepartment of Energy and Process Engineering, Faculty of Technical Sciences, University of Novi Sad, Trg Dositeja Obradovića 6, 21000 Novi Sad, SerbiaDepartment of Energy and Process Engineering, Faculty of Technical Sciences, University of Novi Sad, Trg Dositeja Obradovića 6, 21000 Novi Sad, Serbiapaysmarkodj@uns.ac.rsM.BukurovDepartment of Energy and Process Engineering, Faculty of Technical Sciences, University of Novi Sad, Trg Dositeja Obradovića 6, 21000 Novi Sad, SerbiaDepartment of Energy and Process Engineering, Faculty of Technical Sciences, University of Novi Sad, Trg Dositeja Obradovića 6, 21000 Novi Sad, Serbiapaysmbukurov@uns.ac.rsS.TašinDepartment of Energy and Process Engineering, Faculty of Technical Sciences, University of Novi Sad, Trg Dositeja Obradovića 6, 21000 Novi Sad, SerbiaDepartment of Energy and Process Engineering, Faculty of Technical Sciences, University of Novi Sad, Trg Dositeja Obradovića 6, 21000 Novi Sad, Serbiapaystasholi@uns.ac.rsS.BikićDepartment of Energy and Process Engineering, Faculty of Technical Sciences, University of Novi Sad, Trg Dositeja Obradovića 6, 21000 Novi Sad, SerbiaDepartment of Energy and Process Engineering, Faculty of Technical Sciences, University of Novi Sad, Trg Dositeja Obradovića 6, 21000 Novi Sad, Serbiapaysbika@uns.ac.rsCFD Orifice flow meter Multi-hole orifice flow meter Pressure loss coefficient.[Arun, N., S. Malavarayan and M. Kaushik (2010). CFD Analysis on Discharge Co- Efficient During Non- Newtonian Flows Through Orifice Meter, International Journal of Engineering Science and Technology 2(7), 3151–3164.
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]Numerical Investigation on the Response Characteristics of Hypersonic Boundary Layer under Different Types of Finite Amplitude Pulse Disturbance Waves22The hypersonic transient flow pass a blunt cone under three types of pulse disturbances is calculated using DNS. The response characteristic of hypersonic boundary layer among different types of pulse disturbance is compared. The distribution and evolution characteristics of disturbance modes are investigated by mode analysis. Results indicate that the receptivity characteristics induced by freestream pulse wave have both similarities and differences with that induced by freestream continuous wave. The interactions of different types of pulse waves with boundary layer and bow shock present different characteristics. The boundary layer thermodynamic characteristics under pulse fast acoustic wave are sensitive to mainstream disturbance wave, and that under pulse slow acoustic wave are sensitive to residual reflection wave. The type of pulse disturbance wave has a great influence on the production and mode distribution of boundary layer disturbance wave. In general, the disturbance amplitude in the pulse fast acoustic wave situation is the largest, the case of entropy wave is the second, and the case of slow acoustic wave is the smallest. For regional influence, the type of pulse disturbance has a huge impact on the disturbance modes in both the head and the non-head. For the three cases of pulse wave, the main mode group attenuation phenomenon which narrows the disturbance frequency band exists in the boundary layer. This group attenuation is the fastest for freestream slow acoustic wave, followed by entropy wave, and then fast acoustic wave. Under the action of pulse slow acoustic waves, the disturbance wave evolution of each order mode in the boundary layer along the streamwise is relatively stable, followed by entropy wave, and the case of fast acoustic wave is the most active.227241X.TangCollege of Engineering, Yantai Nanshan University, Yantai, Shandong, 265713, ChinaCollege of Engineering, Yantai Nanshan University, Yantai, Shandong, 265713, Chinapaysxiaojuntang87@sina.comJ.YuChina Center for Information Industry Development, Beijing 100846, ChinaChina Center for Information Industry Development, Beijing 100846, Chinapaysjuanyu88@163.comH.ZhangBeijing Spacecrafts, China Academy of Space Technology, Beijing 100094, ChinaBeijing Spacecrafts, China Academy of Space Technology, Beijing 100094, Chinapayszhgy0317@163.comH.LiBeijing Spacecrafts, China Academy of Space Technology, Beijing 100094, ChinaBeijing Spacecrafts, China Academy of Space Technology, Beijing 100094, Chinapayshaixiali10@sina.comM.ShiCollege of Aerospace and Civil Engineering, Harbin Engineering University, Harbin, 150001, ChinaCollege of Aerospace and Civil Engineering, Harbin Engineering University, Harbin, 150001, Chinapaysmingfangshi@sina.comHypersonic flow Disturbance type Pulse wave Mode analysis Boundary layer.[Chen, Z., Y. Zhao and R. Huang (2018). Reduced-order modeling of unsteady hypersonic aerodynamics in multi-dimensional parametric space. Journal of Applied Fluid Mechanics 11(4), 1033-1045.##
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]Hydrodynamic Simulation of Two-Phase Flow in an Industrial Electrowinning Cell with New Scheme 22Electrowinning is the process of depositing copper of the electrolyte solution inside the cell to the cathode. In the present study, the hydrodynamic simulation of the electrowinning cell of Miduk Copper Complex is studied using computational fluid dynamics. The software used is Ansys CFX. The Navier-Stokes and continuity equations are considered in the form of two phases of fluid and gas, turbulent, incompressible and steady state, and the equation for copper concentration in the electrolyte is solved with consideration of its specific boundary condition. The flow turbulence is modeled using K-ω relationships. Due to large variations in the properties near cathode and anode, and also the large size of the electrowinning cell, to create a good grid, and increase the speed and accuracy of the results, global and local simulations are used together. First, in global simulation, the entire geometry of the cell is modeled by creating an appropriate grid, then, in the local simulation, the volume between two cathodes of the cell only is considered and modeled with a much smaller mesh. Data on boundary conditions of the common border plates in the local simulation are obtained from global simulation data, which increases the accuracy of modeling. The results of this simulation are the velocity vectors, the concentrations of acid and copper, turbulence Intensity, the amount of pressure, and the volume ratio of the oxygen phase in the entire electrowinning cell domain. Finally, for model validation, the model is compared with experiments conducted on actual cells in the industry. Results show high accuracy with less than 2.5% deviation of this modeling technique. Then, the mass transfer coefficient values for the different electrode intervals are obtained by this modeling and the results are validated using the results of the experimental relations, indicating a deviation of only 0.5%. In the next step, the electrolyte mixture containing different mass fractions of oxygen is sprayed into the electrowinning cell from the inlet of the simulated cell. The results demonstrate that spraying 16 liters per second of oxygen at the inlet can increase the overall mass transfer coefficient of the electrode plates up to 7%. The effect of changing inlet temperature and flow rate of the electrolyte on the mass transfer coefficient is also investigated by the obtained model. 243257S. A. A.Pourahmadi Department of Mechanical Engineering, Yazd University, Yazd, Yazd, 89195-741, Iran Department of Mechanical Engineering, Yazd University, Yazd, Yazd, 89195-741, Iran paysaliakbar211@gmail.comS.TalebiDepartment of Mechanical Engineering, Yazd University, Yazd, Yazd, 89195-741, Iran Department of Mechanical Engineering, Yazd University, Yazd, Yazd, 89195-741, Iran paystalebi_s@yazd.ac.ir Computational fluid dynamics (CFD) Global and Local Simulations Mass transfer coefficient Two phase flow. [Alshakarji, R. (2012). Mechanisms of acid mist formation in electrowinning, James Cook University.##
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]Stability of Oblique Water Entry of Cylindrical Projectiles 22Water entry is an interesting subject but many of its physical aspects have remained unknown so far. Using computational fluid dynamics (CFD), this study investigates the dynamic stability of cylindrical projectiles in the oblique water entry at shallow angles in the presence of three phases of air, water and water vapor. The three-dimensional and transient numerical model has been verified using the former experimental results in the literature. In this study, the effects of projectile length-to-diameter ratio (L/D) and water entry angle on the projectile stability within cavity were investigated. Accordingly, the water entry of six projectiles was simulated with aspect ratios of 2 to 6 at three water entry angles of 6, 9 and 12 degrees with respect to the free surface with an initial velocity of 280 m/s. At each of the aforementioned angles, the critical L/D, where the projectile avoids tumbling inside the cavity at a larger value, was determined. This study showed that in the oblique water entry of a cylindrical projectile at the angles of 6, 9 and 12 degrees, the projectile tumbled within the cavity with a L/D of less than 5, 4 and 3.5, respectively. The simulation results showed that increasing the L/D as well as the water entry angle relative to the free surface resulted in the improvement of the cylindrical projectile motion stability, which is in agreement with the experimental results. By analyzing the details of each simulation, it was found that the projectile stability within the cavity is correlated with the magnitude of the angular momentum which is generated in the projectile by the impact of the cavitator on the free surface and it was shown that the projectile with a specific L/D can withstand destabilizing angular momentum to a certain extent. Considering the fact that the atmospheric ballistics of gyroscopically stabilized projectiles lead to a limit for increasing L/D, this study showed that, for aluminum cylindrical projectiles in which air stability is achieved via the gyroscopic effect, the minimum water entry angle is 6° to attain the gyroscopic stability of the projectile in the air and stable motion inside the cavity. This fact is very important from a practical point of view.
301314M. A.AkbariFaculty of Mechanics, Malek Ashtar University of Technology, Iran Faculty of Mechanics, Malek Ashtar University of Technology, Iran paysmoak89@gmail.comJ.MohammadiFaculty of Aerospace, Malek Ashtar University of Technology, IranFaculty of Aerospace, Malek Ashtar University of Technology, Iranpaysmohammadijalal@mut.ac.irJ.FereidooniFaculty of Mechanics, Malek Ashtar University of Technology, IranFaculty of Mechanics, Malek Ashtar University of Technology, Iranpaysj.fereidooni@gmail.comWater entry Cylindrical projectiles Stability Supercavitation. [Aus der Wiesche, S. (2005). Numerical simulation of cavitation effects behind obstacles and in an automotive fuel jet pump. Heat and mass transfer 41(7), 615-624.
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Chen, T., W. Huang, W. Zhang, Y. Qi and Z. Guo (2019b). Experimental investigation on trajectory stability of high-speed water entry projectiles. Ocean Engineering 175, 16-24.##
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]Cavitation Status Recognition Method of Centrifugal Pump Based on Multi-Pointand Multi-Resolution Analysis 22Cavitation monitoring is particularly important for pump efficiency and stability. It is easy to misjudge cavitation by using a given threshold of a single eigenvalue. In this work, based on the vibration signal, a method for multi-resolution cavitation status recognition of centrifugal pump is proposed to improve the accuracy and universality of cavitation status recognition., wavelet packet decomposition (WPD) is used to extract the statistical eigenvalues of multi-scale time-varying moment of cavitation signal after reducing the clutter, such as root mean square value, energy entropy value and so on. The characteristic matrix is constructed. Principal component analysis method (PCA) is employed to reduce the dimension of the characteristic matrix and remove the redundancy, which constructs the radial basis function (RBF) neural network as the input. The results show that the overall recognition rate of non-cavitation, inception cavitation and serious cavitation by using the vibration signal of one measuring point is more than 97.7%. The recognition rate of inception cavitation is more than 80%. Based on the vibration signal information fusion method of two measuring points, the recognition rate of centrifugal pump inception cavitation status reaches more than 99%, and the recognition rate of vibration signal information fusion method of three measuring points reaches 100% for all three cavitation statuses. Due to the influence of factors such as change of external excitation and abrupt change of working conditions, sensor data acquisition is often subjected to unpredictable disturbance. To study the ability of single-point cavitation status recognition method to resist unknown disturbances, by constantly adjusting the value of the interference coefficient of the interference term. It is found that the recognition rate of cavitation status using single measuring point decreases almost linearly with the increase of the interference coefficient. When five measuring points are used for information fusion cavitation status recognition, the cavitation status recognition rate still reaches over 90% even if the interference factor of one measuring point reaches 50%. 315329L.DongResearch Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China Research Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China paysdongliang@ujs.edu.cnJ. C.ZhuResearch Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China Research Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China pays2658570555@qq.comK.WuResearch Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China Research Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China paysmvswupu@163.comC.DaiSchool of Energy and Power Engineering, Jiangsu University, Zhenjiang, Jiangsu Province, 212013, China School of Energy and Power Engineering, Jiangsu University, Zhenjiang, Jiangsu Province, 212013, China paysdaicui@ujs.edu.cnH. L.LiuResearch Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China Research Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China paysliuhoulin@ujs.edu.cnL. X.ZhangResearch Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China Research Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China pays1280225062@qq.comJ. N.GuoResearch Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China Research Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang ,Jiangsu Province, 212013, China pays827387562@qq.comH. B.LinSichuan Provincial Key Lab of Process Equipment and Control, Sichuan University of Science & Engineering, Zigong, Sichuan Province, 643000,China Sichuan Provincial Key Lab of Process Equipment and Control, Sichuan University of Science & Engineering, Zigong, Sichuan Province, 643000,China payszhujianceng@163.comCentrifugal pump Cavitation recognition Vibration Wavelet packet decomposition Principal component analysis RBF neural network. [Alfayez, L. Mba, D. Dyson, G (2005). The application of acoustic emission for detecting incipient cavitation and the best efficiency point of a 60kW centrifugal pump: case study [J]. NDT&E International 38(5), 354-358.##
Azizi, R., B. Attaran, A. Hajnayeb, A. Ghanbarzadeh and M. Changizian (2017). Improving accuracy of cavitation severity detection in centrifugal pumps using a hybrid feature selection technique． Measurement 108, 9-17．##
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]Innovations in Non-Linear Oscillations of a Pendent Drop From a Capillary Tip During Formation and Detachment - An LBM Simulation 22Individual drops are suitable tools to study the liquid-fluid interfacial properties. In this work, forcedisplacement equation and non-linear oscillations of a pendent drop are numerically investigated. The presented novel force-displacement function allows following the dynamics of a pendent drop and realizing its elastic behavior. The growth and detachment of drop, which is pending due to gravity from a capillary tip, is considered (assuming high density and high viscosity ratios and immiscible two-phase flows). Twodimensional multi-relaxation time lattice Boltzmann method (MRT-LBM) was used to simulate growth, detachment, and oscillations of the drop using a conservative model for high-density ratio. The forcedisplacement function of a pendent drop (FDFPD), which is non-linear, was introduced. Using FDFPD, the non-linear elastic specifications of the pendent drop were determined. It was realized that the drop shows three different elastic behaviors simultaneously (hardening, linear, and softening). The drop superharmonic and subharmonic frequencies were calculated, using the natural frequency of the linear portion of FDFPD. Besides, the drop would grow as long as its displacement is between the extrema of FDFPD. In addition, a dynamic criterion for the onset of detachment was established. Also, increasing the Bond number from 0.11 to 1.96, while keeping Reynolds number equal to 0.023, accelerates the drop detachment and increases the linear portion of FDFPD. It was shown that increasing Capillary number from 1.8E-5 to 7.3E-4, while keeping Reynolds number equal to 0.023, accelerates the drop detachment and increases the non-linear portions of FDFPD. 331344S.GhorbanifarIslamic Azad University Science and Research Branch, Tehran.Islamic Azad University Science and Research Branch, Tehran.payssh.ghorbanifar@iau-astara.ac.irM.Taeibi-RahniAerospace Department, Sharif University of Technology, Tehran, Iran Aerospace Department, Sharif University of Technology, Tehran, Iran paystaeibi@sharif.eduM.ZarehIslamic Azad University Science and Research Branch, Tehran, Iran Islamic Azad University Science and Research Branch, Tehran, Iran paysm.zareh@srbiau.ac.irTwo-phase flow Growing drop Drop non-linear oscillations Lattice Boltzmann method Drop dynamics [Allen, S. M. and J. W. Cahn(1979). A microscopic theory for antiphase boundary motion and its application to antiphase domain coarsening. Acta Metallurgica 27(6), 1085–1095. ##
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]