Relevant bibliographies by topics / Y type jet atomizer

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
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Academic literature on the topic 'Y type jet atomizer'

Author: Grafiati
Published: 3 June 2025
Last updated: 13 July 2025

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Journal articles on the topic "Y type jet atomizer"

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Malý, Milan, Marcel Sapík, Jan Jedelský, et al. "Internal flow characteristics in scaled pressure-swirl atomizer." EPJ Web of Conferences 180 (2018): 02059. http://dx.doi.org/10.1051/epjconf/201818002059.

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Pressure-swirl atomizers are used in a wide range of industrial applications, e.g.: combustion, cooling, painting, food processing etc. Their spray characteristics are closely linked to the internal flow which predetermines the parameters of the liquid sheet formed at the discharge orifice. To achieve a better understanding of the spray formation process, the internal flow was characterised using Laser Doppler Anemometry (LDA) and high-speed imaging in a transparent model made of cast PMMA (Poly(methyl methacrylate)). The design of the transparent atomizer was derived from a pressure-swirl atomizer as used in a small gas turbine. Due to the small dimensions, it was manufactured in a scale of 10:1. It has modular concept and consists of three parts which were ground, polished and bolted together. The original kerosene-type jet A-1 fuel had to be replaced due to the necessity of a refractive index match. The new working liquid should also be colourless, non-aggressive to the PMMA and have the appropriate viscosity to achieve the same Reynolds number as in the original atomizer. Several liquids were chosen and tested to satisfy these requirements. P-Cymene was chosen as the suitable working liquid. The internal flow characteristics were consequently examined by LDA and high-speed camera using p-Cymene and Kerosene-type jet A-1 in comparative manner.
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Daikoku, Masatoshi, Sh Tanno, and Takao Inamura. "Spray Characteristics of Y-Jet-Type Airblast Atomizer Embedding Fluid Amplifier." International Journal of Fluid Mechanics Research 24, no. 1-3 (1997): 407–15. http://dx.doi.org/10.1615/interjfluidmechres.v24.i1-3.410.

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DAIKOKU, Masatoshi, Hitoshi FURUDATE, and Takao INAMURA. "Characteristics of Y-Jet-Type Airblast Atomizer with Self-Control Function." JSME International Journal Series B 48, no. 1 (2005): 41–47. http://dx.doi.org/10.1299/jsmeb.48.41.

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Arriaga, Ian, Jasuo Sayán, Julio Ronceros, et al. "Study of Internal Flow in a Liquid Nitrogen Flow Decelerator Through Swirl Effect Consisting of a Jet-Type Cryogenic Injection System for Food Freezing." Fluids 9, no. 12 (2024): 302. https://doi.org/10.3390/fluids9120302.

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This article addresses the study of internal flow dynamics within a cryogenic chamber designed for freezing food using liquid nitrogen injection. The chamber features a circular section with strategically placed jet-type atomizers for this purpose. The primary objective is to extend the residence time of the cryogenic fluid within the chamber to ensure uniform and effective freezing of the passing food items. This is achieved by inducing a swirl effect through strategic deceleration of the flow using the atomizers. The meticulous placement of these atomizers at periodic intervals along the internal walls of the cylindrical chamber ensures prolonged recirculation of the internal flow. Internal temperature analysis is crucial to ensure the freezing process. The study is supported by numerical analysis in CFD ANSYS to assess the dynamics of the swirl effect and parameters associated with the nitrogen–air interface, from which we obtain a sophisticated analysis thanks to the design of a hexahedral mesh made in greater detail in ICEM CFD. This approach aims to understand internal flow behavior and its correlation with the complexity of cryogenic system design, utilizing variable nitrogen-injection pressures and strategic atomizer placement as fundamental parameters to optimize system design.
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Xiao, Yao Zong, Wen Jun Zhang, Bin Wang, and Chun Cheng Tai. "Floatation Column Test Research into Ore Way." Advanced Materials Research 347-353 (October 2011): 1718–21. http://dx.doi.org/10.4028/www.scientific.net/amr.347-353.1718.

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Developed a test using column flotation device, this experiment device in the structure designing considerate multifunctional traits, realizing continuous and respectively working. In the testing platform, installing two diameter vertical and inclined floatation column, so the device can complete roughing, selection and sweep the election testing. On researching the inflatable way, designing and testing two kinds of inflatable devices, one is jet, the other is sand core type. And testing three kinds of into ore ways, conical nozzle atomizer, atomizer grid and bar nozzle device. Through a series of contrast testing, making useful testing data, the testing provide the basis for designing the floatation column.
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Sikka, Raghav, Knut Vågsæther, Dag Bjerketvedt, and Joachim Lundberg. "Experimental Study of Primary Atomization Characteristics of Sonic Air-Assist Atomizers." Applied Sciences 11, no. 21 (2021): 10444. http://dx.doi.org/10.3390/app112110444.

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The present study compares two twin-fluid atomizer concepts based on the airflow (shock waves) pattern obtained through shadowgraph imaging for atomization of water with a low air/water pressure supply. The research work was conducted using the backlight imaging technique for converging (sonic) and converging–diverging (supersonic) air-assist atomizers with a 3.0 mm (throat) diameter. An annular sheet of thicknesses 70 µm and 280 µm with a high-speed air-core was employed to study the breakup dynamics for different water mass flow rates (100–350 kg/h) and air mass flow rates (5–35 kg/h). Different sheet breakup patterns were identified as the function of the ALR ratio (air-to-liquid mass flow), liquid Weber number (WeL), and Reynolds number (Reg). Different breakup modes extend from canonical Rayleigh bubble breakup, ligament-type breakup, to the pure pulsating breakup via annular sheet disintegration. The sheet breakup dynamics were studied in terms of spray angle and breakup length. With higher ALR values, breakup length showed a decreasing trend, while spray angle showed an increasing trend in the converging and converging–diverging (CD) air-assist atomizers, respectively, owing to the drastic difference in the jet flow dynamics.
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Wang, Muh Ron, Che Jui Yang, Jian Duen Huang, Tien Chu Lin, and Ming Shen Sheu. "Effects of Substrate Geometry on Performance of Twin-Fluid Atomizer in Metal Powder Production." Materials Science Forum 594 (August 2008): 138–49. http://dx.doi.org/10.4028/www.scientific.net/msf.594.138.

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Uniform and spherical metal powders have been widely used in many industrial applications. This paper investigates the control of particle size and size distribution by the impingement of the molten spray on the substrate with different geometries. The idea is to combine the atomization process with the classification process. Result shows that a significant reduction of the particle size occurred when the substrate was placed in the spray jet. The mean particle size was lowered to 8.0μm with a low transmission ratio of the spray jet in the existence of the ring type substrate. The particle size increased from 8.78μm to 12.67μm as the transmission ratio was increased from 13.92% to 75.80%. The reduction in particle size was due to the effect of the blockage of the substrate on the spray. The particle size increased from 6.72μm to 6.98μm when the disk-type substrate was placed at Z = 150mm and 200mm, respectively. The particle size of this case was smaller than the case with ring type substrate because the transmission ratio of the disk type substrate was lower. The percentage of small particles (i.e., V15-) were higher than 60% and the percentages of V25-45 were 4.19% and 0.37% when the disk-type substrate was placed at Z=150mm and Z=200mm, respectively, indicating that almost all of the particles were below 25μm under these conditions. Hence this technique is very effective in controlling the particle size in the metal powder production.
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Ridzwan Kamaruddin, Syabillah Sulaiman, Amir Khalid, et al. "Computational Fluid Dynamics: Flow Analysis on The Effect of Different Jet Orifice Angle Multi Circular Jet for Fuel and Air Mixing." CFD Letters 16, no. 1 (2023): 121–37. http://dx.doi.org/10.37934/cfdl.16.1.121137.

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The mixing of fuel and air plays a major role in the spray and flame behavior, hence affecting the combustion performance and emissions of the internal mixing air-assisted atomizers. Air-assisted atomizers are introduced to counter the low-pressure differential of a simplex nozzle, which reduces the atomization quality. The present study aims to determine the effects of Multi Circular Jet (MCJ) plates on the geometrical configurations of internal flows in mixing chamber and the internal flow of plate 3 using different properties of fuel. In this study, the realizable k-ε turbulence model, specifically designed for strongly swirling flows, is validated through numerical simulations. The turbulence model selected is a type of Reynolds averaged Navier-Stokes (RANS) model called the k-ε model. The MCJ plates provide the primary air entrance into the mixing chamber. Additionally, it acts as a turbulence generator and can be adjusted to alter the flow of fuel and air mixtures in a mixing chamber. The study compares several MCJ geometries in terms of pressure, speed, turbulent kinetic energy, and volume fraction and compares the performances of diesel and Crude Palm Oil (CPO) B30 biodiesel fuels. The findings imply that CPO B30 biodiesel has superior atomization and mixing due to its higher density and turbulent kinetic energy. CPO B30 biodiesel was compared to Diesel in terms of maximum pressure, average speed, turbulent kinetic energy per unit mass, and volume fraction. The results indicate that CPO B30 has lower pressure and higher velocity than Diesel, suggesting better fuel atomization and mixing. The higher density of CPO B30 leads to increased turbulent kinetic energy, improving fuel-air mixing inside the combustion chamber. The study demonstrates that the use of MCJ plates can enhance mixing in a mixing chamber. In addition, MCJ plates show the ability to control the spray and atomization. The findings of this study contribute to a better understanding of the relationships between geometry and fuel-air mixing, as well as the characteristics of the internal mixing air-assisted atomizer, which will lead to future burner system improvements.
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Inamura, Takao, and Nobuki Nagai. "CONTROL OF MEAN DROPLET DIAMETER ISSUED FROM Y-JET-TYPE AIRBLAST ATOMIZER BY USING FLUID AMPLIFIER." Atomization and Sprays 5, no. 3 (1995): 243–60. http://dx.doi.org/10.1615/atomizspr.v5.i3.10.

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Zhang, Feichi, Simon Wachter, Thorsten Zirwes, et al. "Effect of nozzle upscaling on coaxial, gas-assisted atomization." Physics of Fluids 35, no. 4 (2023): 043302. http://dx.doi.org/10.1063/5.0141156.

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Mass flow scaling of gas-assisted coaxial atomizers from laboratory to industrial scale is of major interest for a wide field of applications. However, there is only scarce knowledge and research concerning the effect of atomizer scale-up on liquid breakup and spray characteristics. The main objective of this study is therefore to derive basic principles for liquid jet breakup using upscaled nozzles to increase the liquid mass flow rate [Formula: see text]. For that purpose, atomizers with the same geometrical setup but increased sizes have been designed and experimentally investigated for [Formula: see text], 50, 100, and 500 kg/h, while the aerodynamic Weber number Weaero and gas-to-liquid ratio GLR have been kept constant. The primary jet breakup was recorded via high-speed imaging, and the liquid core length LC and the frequency of the Kelvin–Helmholtz instability fK were extracted. Applying these results as reference data, highly resolved numerical simulations have been performed to gain a deeper understanding of the effect of mass flow scaling. In the case of keeping Weaero and GLR constant, it has been shown by both experiments and simulations that the breakup morphology, given by a pulsating liquid jet with the disintegration of fiber-type liquid fragments, remains almost unchanged with the degree of upscaling n. However, the normalized breakup length [Formula: see text] has been found to be considerably increased with increasing n. The reason has been shown to be the decreased gas flow velocity vgas at the nozzle exit with n, which leads to a decreased gas-to-liquid momentum flux ratio j and an attenuated momentum exchange between the phases. Accordingly, the calculated turbulence kinetic energy of the gas flow and the specific kinetic energy in the liquid phase decrease with n. This corresponds to a decreased fKHI with n or [Formula: see text], respectively, which has been confirmed by both experiments and simulations. The same behavior has been shown for two liquids with different viscosities and at different Weaero. The obtained results allow a first-order estimate of the liquid breakup characteristics, where the influence of nozzle upscaling can be incorporated into j and Reliq in terms of n.
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Dissertations / Theses on the topic "Y type jet atomizer"

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Mead, Ryan M. "Analysis of Flow in a Spray Nozzle With Emphasis on Exiting Jet Free Surface." [Tampa, Fla.] : University of South Florida, 2003. http://purl.fcla.edu/fcla/etd/SFE0000138.

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Marzouk, Salwa. "Simulation numérique d'un écoulement de type jet pulsé." Aix-Marseille 2, 2002. http://www.theses.fr/2002AIX22078.

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IBRAHIM, ASHRAF. "COMPREHENSIVE STUDY OF INTERNAL FLOW FIELD AND LINEAR AND NONLINEAR INSTABILITY OF AN ANNULAR LIQUID SHEET EMANATING FROM AN ATOMIZER." University of Cincinnati / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1154536582.

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Hong, Chin Tung. "Analysis of flow in a 3D chamber and a 2D spray nozzle to approximate the exiting jet free surface." [Tampa, Fla.] : University of South Florida, 2004. http://purl.fcla.edu/fcla/etd/SFE0000560.

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Hardy, Pierrick. "Etude et qualification aérothermodynamique et électrique d'un actionneur plasma de type jet." Thesis, Toulouse, ISAE, 2012. http://www.theses.fr/2012ESAE0014/document.

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L’amélioration des performances aérodynamiques et environnementales est un enjeu majeur dans le domaine des transports terrestres et aériens. Pour pouvoir répondre à ses exigences, une des solutions est de contrôler les écoulements. Pour cela, des actionneurs performants sont nécessaires. Une technique innovante, le jet synthétique par plasma (JSP), consiste à appliquer une décharge haute tension dans une micro cavité. Un plasma est ainsi créé dans la chambre augmentant en quelques microsecondes la température et la pression du gaz générant un micro-jet par l’orifice de l’actionneur. Le but de la thèse est de développer cet actionneur, d’en comprendre son fonctionnement et de le mettre en oeuvre pour contrôler le bruit d’un jet subsonique à grand nombre de Mach.La première partie de l’étude s’applique à définir les besoins pour le contrôle d’écoulement et de réaliser un prototype d’actionneur. Il est ensuite caractérisé expérimentalement par des mesures de la décharge électrique et de l’aérodynamique du micro-jet. En s’inspirant du modèle de Braginskii, un modèle simple de la décharge électrique est réalisé et appliqué au JSP. Le rendement de l’actionneur en est déduit. Le modèle de Braginskii modifié est ensuite couplé à une modélisation URANS ce qui permet de simuler le fonctionnement en fréquence de l’actionneur. Ces résultats sont ensuite comparés avec les mesures de l’aérodynamique du micro-jet et montrent un excellent accord.L’actionneur est ensuite mis en application pour contrôler le bruit de jet. En premier lieu, des visualisations par strioscopie de l’interaction des micro-jets avec le jet principal sont effectuées. Des mesures acoustiques sont ensuite réalisées etmettent en évidence que les JSP sont de bons candidats pour contrôler le bruit de jet<br>Improvement of aerodynamics and environmental performances is a major issue for terrestrial and aeronautical industry.For fulfilling increasing demand, one of the answers is flow control. To achieve flow control, high performance actuators are needed. An innovative technique called Plasma Synthetic Jet actuator consists on applying an electrical discharge in asmall cavity. Plasma is created and increases gas temperature and pressure which results on the creation of a micro-jet through cavity opening.The PhD objectives are to develop the PSJ actuator, to describe actuator mechanisms and to apply it for controlling noise of a high subsonic jet. The first part of the study consists on defining flow control needs and on developing a PSJ actuator prototype. Then,actuator performances are characterised using electrical measurements of the discharge and using aerodynamic measurements. These measurements show that an electrical model of the discharge is needed. Based on the Braginskii model, a simple model is carried out and is applied to the actuator. Efficiency of the PSJ is deduced.The modified Braginskii model is then coupled with an URANS model to achieve frequency modelling of the actuator. Results match aerodynamics measurements .PSJ actuators are applied for controlling jet noise in a second part of the study. Schlieren visualisations are used to show micro-jet interaction with the main jet. Acoustic measurements are then performed and show that the PSJ is a goodactuator to control high subsonic jet noise
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Laurendeau, François. "Analyse expérimentale et modélisation numérique d’un actionneur plasma de type jet synthétique." Thesis, Toulouse, ISAE, 2016. http://www.theses.fr/2016ESAE0023/document.

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De nombreuses recherches sont actuellement menées afin de réduire les émissions polluantesdes aéronefs. Le contrôle actif des écoulements aérodynamiques est une piste envisagéepour répondre à ces enjeux. Parmi les technologies de contrôle en développement, lestechnologies plasma offrent plusieurs avantages, dont la compacité, la simplicité de mise enoeuvre et la réactivité. Ce travail de thèse a été consacré à l’étude d’un actionneur plasmade type jet synthétique. Il se présente sous la forme d’une petite cavité insérée en paroiet reliée à l’extérieur par une tuyère. Un arc électrique est généré dans la cavité, ce quientraîne une augmentation de la pression de l’air dans celle-ci. Par conséquent, un jet estproduit à la sortie de la tuyère, et celui-ci peut interagir avec l’écoulement extérieur. A lasuite de cette phase d’éjection, de l’air extérieur est naturellement aspiré par la cavité, cequi permet au processus d’être répété à des fréquences pouvant atteindre plusieurs kilohertz.L’objectif de ce travail de thèse est de construire un modèle numérique capable dereproduire ces phénomènes physiques. Pour cela, un calcul aérodynamique de type LargeEddy Simulation est mis en oeuvre. L’action du plasma d’arc est prise en compte au traversde termes sources dans l’équation de l’énergie. Ces derniers sont notamment calculés grâceà l’hypothèse d’équilibre thermodynamique local dans le plasma. De plus, l’augmentationde la température dans la partie solide de l’actionneur est simulée lorsque celui-ci est opéréà haute-fréquence. Les résultats du modèle numérique sont comparés à des mesures de vitesseeffectuées lorsque l’actionneur fonctionne dans un environnement extérieur au reposet lorsque celui-ci interagit avec une couche limite<br>Nowadays, many studies are conducted in order to decrease greenhouse gases and noiseemissions from aircrafts. Active aerodynamic flow control is a way considered to meet thesechallenges. Among developed technologies of control, plasma actuators offer several advantages,including compactness, easy implementation and fast response. This thesis is devotedto the study of a plasma synthetic jet actuator which comes in the form of a small cavityinserted in wall and connected to the environment through a nozzle. An electrical arc isgenerated in the cavity, resulting in an increase of the cavity air pressure. Consequently,a jet is produced at the nozzle exhaust that can interact with the external flow. After thisejection phase, an aspiration phase naturally occurs, allowing the process to be repeatedat a frequency that can reach several kilohertz. This thesis aims at building a numericalmodel able to reproduce these physical phenomena. To do so, a Large Eddy Simulationis performed. The action of the plasma arc is taken into account through source terms inthe energy equation. In particular, these source terms are calculated using the assumptionof local thermodynamic equilibrium in the plasma. In addition, the heating of the actuatormaterials is simulated when it is operated at high frequency. The results from the numericalmodel are compared with velocity measurements, carried out when the actuator works ina quiescent environment and when it interacts with a boundary layer
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GALBIATI, Claudio. "Numerical investigation of primary break-up of conical swirled jets." Doctoral thesis, Università degli studi di Bergamo, 2016. http://hdl.handle.net/10446/222090.

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Primary break-up is a hard element to be described into the atomization chain, since experimental works are rare especially for swirl atomizers. In the past, different models had been developed to define the mechanism which leads to break-up of jets and, in this way, the characteristics of the sub-sequent produced spray. These models had been validated against experimental data in simplified conditions, for example using round jets; however they cannot be generalized for all the other categories. Moreover, these models were based on simplified assumptions, for example they neglected turbulence. Thus their application to conical swirled jets is tricky and could produce misleading results. In absence of experimental data, Volume of Fluid Direct Numerical Simulations (VOF DNS) could help to provide more information about the produced primary spray and its characteristics, such as droplets velocity components, location, size and shape in the whole investigated domain. However, in order to simulate conical swirled jets from aeronautical pressure swirl atomizers, realistic velocity profiles of both liquid and gas phases together with the characteristics of the external environment are required as input parameter. Semi-empirical or analytical correlations, indeed, may provide an estimation of these data, but they can be properly applied only to a small group of test cases, if compared with the huge amount of possible configurations with different geometries, liquid properties and operating conditions. VOF RANS and LES are performed to provide the internal nozzle flow characteristics, and the subsequent initial jet characteristics. For this reasons, in this work VOF Reynolds Averaged Navier-Stokes (RANS) and Large Eddy Simulation (LES) have been performed to provide a proper simulation of the internal nozzle flow and the subsequent initial jet characteristics. In addition, a sensitivity analysis has been performed to evaluate the effect of various turbulence model (i.e. RNG k-e, Reynolds Stress Model and LES) on the final numerical results. Then, these informations have been applied to reproduce the following jet development and its subsequent break-up. To reach this goal a DNS code from the University of Stuttgart, Free Surface 3D (FS3D), has been adapted and used. As shown, the achieved results could be useful to define the principal phenomena involved in the atomization process. Moreover, comparison with a well known analytical method are presented in order to underline possible drawback and improvements. For both the internal and the external flow numerical simulations, a grid dependence study, as well as the effect of various operating conditions, has been investigated to exclude any important and unwanted dependences.
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GALBIATI, Claudio. "Numerical investigation of primary break-up of conical swirled jets." Doctoral thesis, Università degli studi di Bergamo, 2016. http://hdl.handle.net/10446/53313.

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Primary break-up is a hard element to be described into the atomization chain, since experimental works are rare especially for swirl atomizers. In the past, different models had been developed to define the mechanism which leads to break-up of jets and, in this way, the characteristics of the sub-sequent produced spray. These models had been validated against experimental data in simplified conditions, for example using round jets; however they cannot be generalized for all the other categories. Moreover, these models were based on simplified assumptions, for example they neglected turbulence. Thus their application to conical swirled jets is tricky and could produce misleading results. In absence of experimental data, Volume of Fluid Direct Numerical Simulations (VOF DNS) could help to provide more information about the produced primary spray and its characteristics, such as droplets velocity components, location, size and shape in the whole investigated domain. However, in order to simulate conical swirled jets from aeronautical pressure swirl atomizers, realistic velocity profiles of both liquid and gas phases together with the characteristics of the external environment are required as input parameter. Semi-empirical or analytical correlations, indeed, may provide an estimation of these data, but they can be properly applied only to a small group of test cases, if compared with the huge amount of possible configurations with different geometries, liquid properties and operating conditions. VOF RANS and LES are performed to provide the internal nozzle flow characteristics, and the subsequent initial jet characteristics. For this reasons, in this work VOF Reynolds Averaged Navier-Stokes (RANS) and Large Eddy Simulation (LES) have been performed to provide a proper simulation of the internal nozzle flow and the subsequent initial jet characteristics. In addition, a sensitivity analysis has been performed to evaluate the effect of various turbulence model (i.e. RNG k-e, Reynolds Stress Model and LES) on the final numerical results. Then, these informations have been applied to reproduce the following jet development and its subsequent break-up. To reach this goal a DNS code from the University of Stuttgart, Free Surface 3D (FS3D), has been adapted and used. As shown, the achieved results could be useful to define the principal phenomena involved in the atomization process. Moreover, comparison with a well known analytical method are presented in order to underline possible drawback and improvements. For both the internal and the external flow numerical simulations, a grid dependence study, as well as the effect of various operating conditions, has been investigated to exclude any important and unwanted dependences.
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Stewart, Gregory D. "Numerical simulation of titania deposition in a cold-walled impinging jet type APCVD reactor." Ohio : Ohio University, 1995. http://www.ohiolink.edu/etd/view.cgi?ohiou1178908165.

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Singy, Dominique. "Production à basse température d'un jet intense d'atomes d'hydrogène polarisés /." Zurich, 1987. http://e-collection.ethbib.ethz.ch/show?type=diss&nr=8196.

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Books on the topic "Y type jet atomizer"

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Janes, Muriel. Jet nurse. Chivers, 1986.

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Copper, Basil. Jet-lag. Thorndike Press, 2004.

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Gupta, Santosh K. Glove box adaptation, installation and commissioning of an assembled modular type atomic absorption unit with GF atomizer. Scientific Information Resource Division, Bhabha Atomic Research Centre, 2013.

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J, Capone Francis, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Effect of port corner geometry on the internal performance of a rotating-vane-type thrust reverser. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Robotti, Aurelio C. Experimental research on electric propulsion.: Experimental research on a plasma jet with vortex type stabilization for propulsion. National Aeronautics and Space Administration, 1985.

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Jet Nurse. Chivers Press, 1986.

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The jet-set seduction. Mills & Boon, 2006.

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Precipitation Noise Measurements on Jet Type Aircraft. Creative Media Partners, LLC, 2021.

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Parker, Philip M. The 2007-2012 World Outlook for Naphtha-Type Jet Fuel. ICON Group International, Inc., 2006.

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The 2006-2011 World Outlook for Naphtha-Type Jet Fuel. Icon Group International, Inc., 2005.

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Book chapters on the topic "Y type jet atomizer"

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Marudhappan, Raja, U. Chandrasekhar, and K. Hemachandra Reddy. "Investigation of 3D Printed Jet Fuel Atomizer." In Lecture Notes on Multidisciplinary Industrial Engineering. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-8468-4_25.

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Zeiss, Wilke, and Roland Behr. "Vortical type flow with respect to jet-external airflow interaction." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-540-39604-8_24.

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Hiroyasu, Hiroyuki, Masataka Arai, Kaoru Nakamori, and Shinji Nakaso. "Blue Flame Combustion in a Jet-Mixing-Type Spray Combustor." In Aerothermodynamics in Combustors. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_13.

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Akimoto, M., H. Matsumori, and M. Kimura. "Jet Control Using the Coaxial Type DBD-PA by Burst Modulation." In Fluid-Structure-Sound Interactions and Control. Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-10-7542-1_11.

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Xue, Xianbo, Zejun Hua, Haijun Liu, et al. "Optimization of Structural Parameters of Vortex Type Coiled Tubing Drag Reduction Tool Based on Coanda Effect." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-97-7887-4_58.

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Abstract The vortex drag reduction tool based on wall attachment effect has a simple structure and high reliability, but lacks systematic research on tool structural parameters. In the application of coiled tubing drilling, there are problems such as poor parameter matching and weak power output. Therefore, based on the theory of wall attached jet, this article establishes a numerical model of vortex drag reduction tools, and investigates the effects of wedge distance, sidewall angle, wedge angle, and flow channel width on the oscillation performance of the tools. The research results indicate that the wedge distance and the angle between the sidewalls affect the oscillation frequency generated by the tool by affecting the jet deflection angle, the wedge angle affects the fluid flow velocity and vortex strength in the vortex chamber, and the flow passage affects the switching of the attached wall jet by affecting the pressure on both sides of the jet port. When the splitting distance is greater than 40 mm, the angle between the sidewalls is 30°, the width of the flow passage is 4–5 mm, and the angle between the splitting tips is 15°, the oscillation performance generated by the tool is better. The research results have certain guiding significance for the reasonable matching and optimization design of the structural parameters of eddy current drag reduction tools.
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Schüler, Manuel, Ralph Lindken, and Brendan Görres. "Influence of Phase Composition in an Injection-Type Abrasive Slurry Jet (iASJ)." In Lecture Notes in Mechanical Engineering. Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-72778-8_16.

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Meng, Qi, Gui-tao Du, Shao-gong Zhu, et al. "Simulation Analysis of a New Type of Combined Double Jet Nozzle Flow Field." In Springer Series in Geomechanics and Geoengineering. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-0761-5_27.

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Kezuka, Hiroshi. "Properties of Fine Superconducting YBCO Particles Prepared by Dry- and Wet-Type Jet-Mill." In Advances in Superconductivity VIII. Springer Japan, 1996. http://dx.doi.org/10.1007/978-4-431-66871-8_153.

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Maekawa, Yasunori, and Tatsu-Hiko Miura. "Rate of the Enhanced Dissipation for the Two-jet Kolmogorov Type Flow on the Unit Sphere." In Collected Papers in Honor of Yoshihiro Shibata. Springer Nature Switzerland, 2022. http://dx.doi.org/10.1007/978-3-031-19252-4_10.

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Fan, Jing Ming, Cheng Yong Wang, Jun Wang, and Guo Sheng Luo. "Effect of Nozzle Type and Abrasive on Machinablity in Micro Abrasive Air Jet Machining of Glass." In Advances in Grinding and Abrasive Technology XIV. Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-459-6.404.

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Conference papers on the topic "Y type jet atomizer"

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Deng, Shaozheng, Fan Zhang, Jianhui Zhang, et al. "A Study of the Contour Morphology of Dynamic Mesh-Type Ultrasonic Atomizer Sprays." In 2024 18th Symposium on Piezoelectricity, Acoustic Waves, and Device Applications (SPAWDA). IEEE, 2024. https://doi.org/10.1109/spawda63926.2024.10878833.

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Qi-Shou, Zhao, and Yu Yun-Fang. "Investigation of Jet-Filming Airblast Atomizer." In ASME 1985 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-gt-185.

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The jet-filming airblast atomizer is another kind of airblast atomizer differing from a prefilming airblast atomizer. Its atomizing mechanism and performance were investigated experimentally and theoretically. The effects of design parameters on the mean droplet size SMD and the thickness of the liquid film were obtained. The inherent mechanism consisting of three atomizing processes was proved. From this, the performance curves of atomization and thickness of liquid film can be explained and the principles of design of this kind atomizer were derived. The results obtained show that the performance of the jet-filming airblast atomizer is better than that of the prefilming type, and it is simple in design. So it is advantageous to apply this kind of atomizer to an advanced aircraft engine.
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Daikoku, Masatoshi, Sh Tanno, and Takao Inamura. "Spray Characteristics of Y-Jet-Type Airblast Atomizer Embedding Fluid Amplifier." In ICLASS 97. Begellhouse, 2023. http://dx.doi.org/10.1615/iclass-97.390.

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Lall, Pradeep, Kartik Goyal, Nakul Kothari, Ben Leever, and Scott Miller. "Effect of Process Parameters on Aerosol Jet Printing of Multi-Layer Circuitry." In ASME 2019 International Technical Conference and Exhibition on Packaging and Integration of Electronic and Photonic Microsystems. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/ipack2019-6574.

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Abstract Printing technologies such as Aerosol Jet provides the freedom of miniaturizing interconnects and producing fine pitch components. Aerosol Jet, a direct printing technique replaces the traditional steps of manufacturing a printed circuit board such as lithography or etching, which are quite expensive, and further allowing the circuits to be fabricated onto all kinds of substrates. Wide impact areas range from healthcare to wearables to future automotive applications. The aerosol jet printer from Optomec utilized in this study, consists of two types of atomizers depending on ink viscosity. One is Ultrasonic Atomizer which supports ink with viscosity range of 1–5cP, and another is Pneumatic Atomizer with large range of suitable viscosity 1–1000cP. This paper focuses on utilizing the aerosol jet printing using both the atomizers to develop process parameters to be able to successfully print bi-material, multi-layer circuitry. The insulating material between two conductive lines used in the paper is of very high viscosity of 350cP, suitable for Pneumatic atomizer and Silver Nano-particle ink with the viscosity suitable for Ultrasonic atomizer as a conductive ink. A statistical modeling approach is presented to predict the attributes such as micro-via diameter before starting the print process, enabling us to pre-adjust the dimensions in CAD for the desired output. Process parameters to obtain a fine print with good electrical properties and better dimensional accuracy are developed. Importance of pre-cleaning the substrate is discussed, in addition to the printing process efficiency gauged as a function of process capability index and process capability ratio.
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Chin, Ju Shan, and Li Xing Wang. "Experimental Study on Internal Mixing Sonic Flow Air Assist Atomizer for Heavy Oils." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-006.

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Based on the experiences previously obtained from the experimental study of plain jet atomization under cross flowing air stream and under supersonic air flow, the authors designed and studied a serious of internal mixing sonic flow air assist atomizers for heavy oil application. The contradiction between the requirements for fine spray (for high combustion completeness) and for long flame (for flame rigidity) often existing in industrial furnace has been solved. Good data were obtained which can be used for the design of such kind atomizers. By properly choosing the configuration and geometrical dimensions of the atomizer, also by choosing suitable values for mixing chamber pressure, air–liquid ratio, it is possible to have very fine spray and desirable flame length. The results showed that the ratio of mixing chamber pressure to air supply pressure should be in the range of 0.6 to 0.7. For atmospheric pressure combustion furnace, such air assist atomizer needs 0.4 MPa compressed air to have sonic flow at nozzle exit. This type of air assist atomizer has already been put into industrial operation.
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Maly, Milan, Lada Janáčková, Jan Jedelský, Jaroslav Sláma, Marcel Sapík, and Graham Wigley. "Internal flow and air core dynamics in simplex and spill-return pressure-swirl atomizers." In ILASS2017 - 28th European Conference on Liquid Atomization and Spray Systems. Universitat Politècnica València, 2017. http://dx.doi.org/10.4995/ilass2017.2017.4995.

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It is well known that the spray characteristics of pressure-swirl atomizers are strongly linked to the internal flow andthat an unstable air core may cause instabilities in the spray. In this paper, a 10:1 scale transparent Plexiglas (PMMA) model of a pressure-swirl atomizer as used in a small gas turbine is introduced. The internal flow is examined using high-speed imaging, laser-Doppler anemometry and computational fluid dynamics tools. The experimental and numerical results were analysed and compared in terms of the air core morphology and its temporal stability. Two different liquids were used, Kerosene-type Jet A-1 represented a commonly used fuel while p-Cymene (4-Isopropyltoluene) matched the refractive index of the Plexiglas atomizer body. The internal flow characteristics were set using dimensionless numbers i.e. the Reynolds number and Froude number. The flow test conditions were limited to inlet Reynolds numbers from 750 to 1750. Two atomizers were examined to represent a simplex and spill-return (SR) geometry. In a comparative manner, the SR atomizer features a central passage in the rear wall of the swirl chamber. The main advantage of this concept is that the fuel is always supplied to the swirl chamber at a high pressure therefore providing good atomization over a wide range of the injection flow rate. However, the presence of the spill orifice strongly affects the internal flow even if the spill-line is closed. The air core in the simplex atomizer was found fully developed and stable. The SR atomizer behaved differently, the air core didnot form at all, and the spray was therefore unstable.DOI: http://dx.doi.org/10.4995/ILASS2017.2017.4995
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Gong, Jing, Yuzhen Lin, Quanhong Xu, and Gaoen Liu. "Investigation of Combustion Performance of a Hybrid Airblast Atomizer Under Simulated Low Power Conditions." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68219.

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An aero gas turbine combustor has to meet requirements for both high and low power condition operation. Within the requirements for low power conditions, lean-blow-out (LBO) and combustion efficiency are the basic ones. A pure prefilming air blast atomizer may have difficulty meeting combustion requirements under low power conditions, such as, idle LBO, idle combustion efficiency, etc. Use of a hybrid airblast atomizer may offer a solution for such problems. A hybrid airblast atomizer is a single fuel injection unit that has both pilot and main fuel circuits. A simplex nozzle is often used for pilot fuel circuit and an airblast atomizer of the swirl cup type may be used for the main fuel circuit. For the main fuel circuit, fuel is injected from a number of plain jet holes. The fuel jets are injected towards a venturi, with the help of swirling air from another air swirler, and the main fuel is airblasted and well mixed with both swirler airflows. For low power conditions, the pilot fuel nozzle (simplex nozzle) works alone. Not all of the swirler air will mix with pilot nozzle fuel spray. With appropriate pilot nozzle pressure drop and with some airblast function, the pilot fuel is well atomized and does not fully mix with the swirler air nor with primary hole air. Thus, the low power condition combustion efficiency is improved. The investigation reported in the present paper has concentrated on hybrid atomizer combustion performance under simulated low power conditions, when only the pilot nozzle is operating. The study consists of the following parts: • Pilot nozzle drop size measurement; • Numerical simulation of combustor flow field; • Atmospheric ignition test; • Simulated idle condition LBO test; • Low power condition combustion efficiency test. Results are reported, and future work is defined.
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Dikshit, Saurabh, Salim Channiwala, Digvijay Kulshreshtha, and Kamlesh Chaudhari. "Experimental Investigations of Performance Parameters of Pressure Swirl Atomizer for Kerosene Type Fuel." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59084.

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The process of atomization is one in which a liquid jet or sheet is disintegrated by the kinetic energy of the liquid itself, or by exposure to high velocity air or gas, or as a result of mechanical energy applied externally. Combustion of liquid fuels in engines and industrial furnaces is dependent on effective atomization to increase the specific surface area of the fuel and thereby achieve high rate of mixing and evaporation. The pressure swirl atomizer is most common type atomizer used for combustion in gas turbine engines and industrial furnaces. The spray penetration is of prime importance for combustion designs. Over penetration of the spray leads to impingement of the fuel on walls of furnaces and combustors. On the other hand, if spray penetration is inadequate, fuel–air mixing is unsatisfactory. Optimum engine performance is obtained when the spray penetration is matched to the size and geometry of combustors. Methods for calculating penetration are therefore essential to sound engine design. Equally important are the spray cone angles and the drop size distribution in the sprays. An attempt is being made to experimentally investigate pressure swirl atomizer performance parameters such as spray cone angle, penetration length and drop size at different injection pressures ranging from 6 bar to 18 bar.
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Rizk, N. K., and H. C. Mongia. "Calculation Approach Validation for Airblast Atomizers." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-305.

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In order to formulate a common approach that could provide the spray parameters of airblast atomizers, various processes of liquid preparation, breakup and secondary atomization have been included in a semi-analytical calculation procedure. The air velocity components in the atomizer flow field are provided by mathematical expressions, and the spray droplets are considered to form at ligament breakup through a disturbance wave growth concept. The validation of the developed approach included the application to six atomizers that significantly varied in concept, design, and size. They represented both prefilming and plain-jet types, and their data utilized in the present effort were obtained with six different liquids. Satisfactory agreement between the measurements and the predictions has been achieved under wide ranges of air/fuel ratio and air pressure drop for various test liquids. The results of this investigation indicate the potential of using such an approach in the early phases of airblast atomizer design, and may be followed by more detailed calculations using analytical tools.
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Levy, Yeshayahou, Semion Lipkin, Valery Nadvany, and Valery Sherbaum. "Fuel Atomization in Small Jet Engines." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30586.

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Small and inexpensive jet engines are usually equipped with vaporizing fuel supply systems. This is in order to deliver low fuel flow-rates from relatively low-pressure fuel supply systems and the need for simple configuration. The difficulties associated with small engines are mainly during ignition or at high altitude re-lights, when the combustor is cold, air supply is poor, and fuel demand and pressure are low. Such conditions lead to poor atomization within the vaporizer resulting in very large droplets at its exit tip or even to a pool of liquid fuel within the combustor. Thus, there is no fuel vapor for ignition. Ignition is very difficult or even impossible under such conditions. Therefore, small engines are commonly equipped with dual fuel supply systems, either in the form of gaseous fuel for the ignition stage or with an additional higher-pressure supply line to the dedicated fuel nozzles for the purpose of ignition. Additional solutions involve the use of a large glow plug or high-energy pyrotechnic cartridges in the kilo-Joule range, to heat the combustor casing prior to ignition. The present work is concerned with the development of alternative and novel atomization systems, which would improve atomization at low pressures and consequently facilitate the ignition process, thus minimizing the need for supporting systems. The work refers to an alternative design for an existing vaporizer system of a small jet engine with 400 Nt of thrust. It focuses on an alternative design for the fuel injection within the vaporizer housing while maintaining all external dimensions and operating conditions unchanged. Three types of fuel nozzles were investigated: • a special impact atomizer, • a miniature pressure swirl atomizer, • a doublet atomizer involving two swirling nozzles (preliminary study only). Droplet size distribution under various nozzle pressure drops and air velocities were measured with Phase Doppler Particle Anemometry (PDPA) and global spray characteristics were obtained by photography. All modified atomization systems demonstrated improved performance and better atomization than the existing system. Initially, water was used as a liquid. At a later stage, the modified impact atomizer was tested and successful spark ignition was demonstrated.
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Reports on the topic "Y type jet atomizer"

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Kalantari, Alireza, Elliot Sullivan-Lewis, and Vincent McDonell. Development of Criteria for Flashback Propensity in Jet Flames for High Hydrogen Content and Natural Gas Type Fuels. Office of Scientific and Technical Information (OSTI), 2016. http://dx.doi.org/10.2172/1357931.

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Cooper, Leonard Y. Fire-plume-generated ceiling jet characteristics and convective heat transfer to ceiling and wall surfaces in a two-layer zone-type fire environment:. National Institute of Standards and Technology, 1991. http://dx.doi.org/10.6028/nist.ir.4705.

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Kirkpatrick, Mitchell, and Willson. L51953 CFD Modeling of Gas Flow and Mixing in a Two-Stroke Natural Gas Engine. Pipeline Research Council International, Inc. (PRCI), 2002. http://dx.doi.org/10.55274/r0010912.

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The objective of this project is to examine the effect of the injection pressure on the subsequent mixing in the cylinder. We examine the injection of natural gas from two types of poppet valves, shrouded and unshrouded valves and assess the ability of a commercial CFD code to compute the velocity and pressure profiles in high pressure gas flow from simple sonic nozzles. A sonic nozzle is a convergent or straight nozzle with an exit Mach number equal to one. The main parameters determining the type of the flow exiting from a sonic nozzle are the ratio of the injection pressure to the cylinder pressure and the nozzle geometry. As the injection pressure increases, a point is reached for convergent nozzles where the exit velocity reaches the speed of sound. This pressureratio is the critical pressure ratio for the nozzle. For an ideal gas with a specific heat ratio of 1.35, the critical pressure ratio is 1.86. At higher pressure ratios, the exit velocity remains sonic, but the exit pressure is greater than ambient, thus substantial gas expansion from the exit pressure to the cylinder pressure is required downstream of the nozzle. This type of nozzle outflow is defined as an underexpanded jet.
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BARKHATOV, NIKOLAY, and SERGEY REVUNOV. A software-computational neural network tool for predicting the electromagnetic state of the polar magnetosphere, taking into account the process that simulates its slow loading by the kinetic energy of the solar wind. SIB-Expertise, 2021. http://dx.doi.org/10.12731/er0519.07122021.

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The auroral activity indices AU, AL, AE, introduced into geophysics at the beginning of the space era, although they have certain drawbacks, are still widely used to monitor geomagnetic activity at high latitudes. The AU index reflects the intensity of the eastern electric jet, while the AL index is determined by the intensity of the western electric jet. There are many regression relationships linking the indices of magnetic activity with a wide range of phenomena observed in the Earth's magnetosphere and atmosphere. These relationships determine the importance of monitoring and predicting geomagnetic activity for research in various areas of solar-terrestrial physics. The most dramatic phenomena in the magnetosphere and high-latitude ionosphere occur during periods of magnetospheric substorms, a sensitive indicator of which is the time variation and value of the AL index. Currently, AL index forecasting is carried out by various methods using both dynamic systems and artificial intelligence. Forecasting is based on the close relationship between the state of the magnetosphere and the parameters of the solar wind and the interplanetary magnetic field (IMF). This application proposes an algorithm for describing the process of substorm formation using an instrument in the form of an Elman-type ANN by reconstructing the AL index using the dynamics of the new integral parameter we introduced. The use of an integral parameter at the input of the ANN makes it possible to simulate the structure and intellectual properties of the biological nervous system, since in this way an additional realization of the memory of the prehistory of the modeled process is provided.
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