Bibliografie tematiche / Nozzle-exit conditions

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Letteratura scientifica selezionata sul tema "Nozzle-exit conditions"

Autore: Grafiati

Pubblicato: 7 luglio 2024

Ultima modifica: 19 luglio 2025

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Articoli di riviste sul tema "Nozzle-exit conditions"

Kozlov, Viktor, Genrich Grek, Oleg Korobeinichev, Yuriy Litvinenko, and Andrey Shmakov. "Influence Of Initial Conditions At The Micro Nozzle Exit On Hydrogen Diffusion Combustion." Siberian Journal of Physics 11, no. 3 (2016): 34–45. http://dx.doi.org/10.54362/1818-7919-2016-11-3-34-45.

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The purpose of the given work will consist in an experimental study of influence of initial conditions at the micro nozzle exit on hydrogen diffusion combustion. It is shown, that the mean velocity profile and presence/absence of a heatcapacious material at the nozzle exit play an essential role on a flame structure and process of a round hydrogen microjet combustion. Velocity ranges of existence of a round hydrogen microjet diffusion combustion, flame separation and «bottleneck flame» region for a case of a top – hat mean velocity profile at the nozzle and two cases of a parabolic mean veloci

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Lepicovsky, J. "An Experimental Investigation of Nozzle-Exit Boundary Layers of Highly Heated Free Jets." Journal of Turbomachinery 114, no. 2 (1992): 469–75. http://dx.doi.org/10.1115/1.2929167.

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An experimental investigation of the effects of nozzle operating conditions on the development of nozzle-exit boundary layers of highly heated air free jets is reported in this paper. The total pressure measurements in the nozzle-exit boundary layer were obtained at a range of jet Mach numbers from 0.1 to 0.97 and jet total temperatures up to 900 K. The analysis of results shows that the nozzle-exit laminar boundary-layer development depends only on the nozzle-exit Reynolds number. For the nozzle-exit turbulent boundary layer, however, it appears that the effects of the jet total temperature o

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Chen, Hongjie, Bingxu Chen, Zhizhou Xu, Jing Ge, Honghua Chen, and Zhaoqi Zhong. "A Thermodynamic Model for Performance Prediction of an Ejector with an Adjustable Nozzle Exit Position." Processes 13, no. 3 (2025): 879. https://doi.org/10.3390/pr13030879.

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Improving the efficiency of ejectors during off-design operations can be effectively achieved through the automatic adjustment of the nozzle exit position (NXP). A thermodynamic model for predicting the performance of an ejector with an adjustable nozzle position is proposed and validated. The key factors influencing the optimal nozzle exit position under variable operating conditions are analyzed using the model. The dimensionless optimal nozzle exit position (DONXP) of the ejector is fitted as a function of these key factors, and a nozzle exit position adjustment scheme for variable operatin

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Fontaine, Ryan A., Gregory S. Elliott, Joanna M. Austin, and Jonathan B. Freund. "Very near-nozzle shear-layer turbulence and jet noise." Journal of Fluid Mechanics 770 (March 27, 2015): 27–51. http://dx.doi.org/10.1017/jfm.2015.119.

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One of the principal challenges in the prediction and design of low-noise nozzles is accounting for the near-nozzle turbulent mixing layers at the high Reynolds numbers of engineering conditions. Even large-eddy simulation is a challenge because the locally largest scales are so small relative to the nozzle diameter. Model-scale experiments likewise typically have relatively thick near-nozzle shear layers, which potentially hampers their applicability to high-Reynolds-number design. To quantify the sensitivity of the far-field sound to nozzle turbulent-shear-layer conditions, a family of diame

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Wang, P. C., and J. J. McGuirk. "Validation of a large eddy simulation methodology for accelerated nozzle flows." Aeronautical Journal 124, no. 1277 (2020): 1070–98. http://dx.doi.org/10.1017/aer.2020.12.

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ABSTRACTPrediction of aeroengine exhaust plume near-field development requires knowledge of velocity and turbulence distributions at nozzle exit. The high Reynolds number nozzle inlet boundary layers of engineering practice are fully turbulent, but acceleration can induce re-laminarisation. Thus, to reproduce nozzle exit conditions accurately, large eddy simulation (LES) for plume prediction must be capable of capturing re-laminarisation and any subsequent boundary layer recovery. Validation is essential to establish a credible LES methodology, but previous studies have suffered from lack of n

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Mokni, Amèni, Jamel Kechiche, Hatem Mhiri, Georges Le Palec, and Philippe Bournot. "Numerical Study of the Inlet Conditions Influence on Laminar Plane Wall Jets." Defect and Diffusion Forum 273-276 (February 2008): 406–12. http://dx.doi.org/10.4028/www.scientific.net/ddf.273-276.406.

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In this paper, we present a numerical investigation of a laminar isothermal plane two dimensional wall jets. Special attention has been paid to the effect of the inlet conditions at the nozzle exit on the flow thermal characteristics in forced convection regime. Two velocities profiles at the nozzle exit are used: uniform profile and parabolic profile. The system of equations governing the studied configuration is solved with a finite difference scheme and an implicit scheme, for numerical stability we use a staggered non uniform grid. The obtained results show, first, that the inlet condition

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Huh, Kang Y., Eunju Lee, and Jaye Koo. "DIESEL SPRAY ATOMIZATION MODEL CONSIDERING NOZZLE EXIT TURBULENCE CONDITIONS." Atomization and Sprays 8, no. 4 (1998): 453–69. http://dx.doi.org/10.1615/atomizspr.v8.i4.60.

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Liu, Fuhai, Songchao Lu, Sibao Zeng, Rong Zhu, Guangsheng Wei, and Kai Dong. "Flow Field of Supersonic Oxygen Jet Generated by Various Wear Lengths at the Laval Nozzle Exit." Coatings 14, no. 11 (2024): 1444. http://dx.doi.org/10.3390/coatings14111444.

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As a main apparatus, the oxygen lance is used to deliver the oxygen element and transfer kinetic energy into the molten bath in the steelmaking process. However, the Laval nozzle exit would be gradually worn out during the service life, which suppresses the performance of the oxygen lance. This paper investigated three different wear length (Lw) conditions at the exit of the Laval nozzle through numerical simulations and high-temperature experiments with various oxygen flow rates. The result showed that the entrainment of the ambient gas was the key factor of the wear phenomenon for the Laval

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Liu, Meng, and Yufeng Duan. "Predicting the Liquid Film Thickness and Droplet–Gas Flow in Effervescent Atomization: Influence of Operating Conditions and Fluid Viscosity." International Journal of Chemical Reactor Engineering 11, no. 1 (2013): 393–405. http://dx.doi.org/10.1515/ijcre-2013-0073.

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Abstract The droplet–gas flow in effervescent atomization was simulated using a comprehensive numerical model. Liquid film thicknesses in the nozzle exit orifice and droplet size distribution at the downstream of spray were calculated. The thickness of liquid film in the nozzle exit orifice increased and approached the droplet size in the primary atomization, as the air–liquid ratio increased. The primary breakup model can accurately predict the Sauter mean diameter in the primary atomization when gas–liquid two-phase flow belongs to the annular flow in the nozzle exit orifice. The viscosity o

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Kim1, H.-D., J.-H. Kim, K.-A. Park, T. Setoguchi, and S. Matsuo. "Study of the effects of unsteady downstream conditions on the gas flow through a critical nozzle." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 218, no. 10 (2004): 1163–73. http://dx.doi.org/10.1243/0954406042369053.

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The present study addresses a computational result of unsteady gas flow through a critical nozzle. The axisymmetric unsteady compressible Navier-Stokes equations are solved using a finite volume method that makes use of the second-order upwind scheme for spatial derivatives and the multi-stage Runge-Kutta integral scheme for time derivatives. The steady solutions of the governing equation system are validated with the previous experimental data to ensure that the present computational method is valid to predict the critical nozzle flows. In order to simulate the effects of back-pressure fluctu

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Più fonti

Tesi sul tema "Nozzle-exit conditions"

Trumper, Miles Thomas. "A study of nozzle exit boundary layers in high-speed jet flows." Thesis, Loughborough University, 2006. https://dspace.lboro.ac.uk/2134/31797.

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The requirement for reduced jet noise in order to meet stringent noise legislation (civil aviation), and low infra-red observability and the use of unconventional exhaust nozzle configurations to improve aircraft survivability and performance (military aviation) is driving research to develop a better understanding of jet development and mixing mechanisms. One option open to the engineer is the use of small-scale model testing to investigate jets flows and provide valuable data for the validation of numerical models. Although more economical than large/full scale testing, additional factors th

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Mayo, David Earl Jr. "The Effect of Combustor Exit to Nozzle Guide Vane Platform Misalignment on Heat Transfer over an Axisymmetric Endwall at Transonic Conditions." Thesis, Virginia Tech, 2016. http://hdl.handle.net/10919/78110.

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This paper presents details of an experimental and computational investigation on the effect of misalignment between the combustor exit and nozzle guide vane endwall on the heat transfer distribution across an axisymmetric converging endwall. The axisymmetric converging endwall investigated was representative of that found on the shroud side of a first stage turbine nozzle section. The experiment was conducted at a nominal exit M of 0.85 and exit Re 1.5 x 10⁶ with an inlet turbulence intensity of 16%. The experiment was conducted in a blowdown transonic linear cascade wind tunnel. Two differen

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Vincent, Hugo. "Simulations et analyses de sensibilité du bruit produit des écoulements cisaillés." Electronic Thesis or Diss., Ecully, Ecole centrale de Lyon, 2024. http://www.theses.fr/2024ECDL0007.

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Dans ce travail de thèse, des études de sensibilité portant sur le développement et le bruit des écoulements cisaillés turbulents sont réalisées à l'aide de simulations aéroacoustiques directes et de la méthode de la différentiation complexe.Dans un premier temps, la méthode de la différentiation complexe est appliquée à des couches de mélange bidimensionnelles afin d'étudier sa capacité à mettre en évidence les effets d'un paramètre sur les champs aérodynamiques et acoustiques d'un écoulement.Pour cela, des simulations numériques directes de couches de mélange sont réalisées avec cette méthod

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Capitoli di libri sul tema "Nozzle-exit conditions"

Bolgar, Istvan, Sven Scharnowski, and Christian J. Kähler. "Effects of a Launcher’s External Flow on a Dual-Bell Nozzle Flow." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_7.

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Abstract Previous research on Dual-Bell nozzle flow always neglected the influence of the outer flow on the nozzle flow and its transition from sea level to altitude mode. Therefore, experimental measurements on a Dual-Bell nozzle with trans- and supersonic external flows about a launcher-like forebody were carried out in the Trisonic Wind Tunnel Munich with particle image velocimetry, static pressure measurements and the schlieren technique. A strongly correlated interaction exists between a transonic external flow with the nozzle flow in its sea level mode. At supersonic external flow conditions, a Prandtl–Meyer expansion about the nozzle’s lip decreases the pressure in the vicinity of the nozzle exit by about 55%. Therefore a new definition for the important design criterion of the nozzle pressure ratio was suggested, which considers this drastic pressure drop. Experiments during transitioning of the nozzle from sea level to altitude mode show that an interaction about the nozzle’s lip causes an inherently unstable nozzle state at supersonic free-stream conditions. This instability causes the nozzle to transition and retransition, or flip-flop, between its two modes. This instability can be eliminated by designing a Dual-Bell nozzle to transition during sub-/transonic external flow conditions.

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Xue, Yuqin, Ben Guan, Ge Wang, Hongyi Ren, and Jiatong Cheng. "Experimental Investigation on Porous Media Permeable Nozzle." In Advances in Transdisciplinary Engineering. IOS Press, 2025. https://doi.org/10.3233/atde250098.

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Experimental methods are used in the present work to investigate the thrust characteristics and pressure distribution of porous media permeable nozzles with varying porosities. Comparative analyses are conducted on permeable nozzles with porosities of 15%, 20%, and 30% against a conventional nozzle. The results reveal that the thrust of permeable nozzles can be enhanced by up to 1.9% compared to the conventional nozzle, confirming their capability for thrust compensation. Under the conditions of the present experiments, the influence of porosity on the performance of permeable nozzles is found to be small. Compared to the conventional nozzle, the permeable nozzle flows are characterized by a shift in the flow separation point and a change in exit pressure.

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Mehta, Rakhab. "Analysis of supersonic free jets and impinging supersonic jets on deflector." In Simulation Modeling - Recent Advances, New Perspectives, and Applications [Working Title]. IntechOpen, 2023. http://dx.doi.org/10.5772/intechopen.1002372.

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The computational fluid dynamics analysis is carried out to analyze the shock and flow characteristics of under- and over expanded supersonic free jets emanating from convergent-divergent nozzles. Influence of exit Mach number on shock cell lengths are analyzed with the help of density contours and schlieren images. A parameter based on an exit Mach number is obtained to characterize the pressure variation along the jet axis which shows them independent of the exit to ambient pressure ratio. Impingement flow fields over axisymmetric and wedge deflector are investigated employing numerically and compared with experimental results. Effects of jet expansion ratio and distance between the nozzle to deflector apex has been studied at various expansion ratios and distances. Impingement load is computed at various conditions. Pressure distributions over a surface of wedge and axisymmetric jet deflector are computed and compared between them. Pressure load on a diaphragm of a solid motor during lift-off of a satellite launch vehicle having four liquid engines is numerically simulated.

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Atti di convegni sul tema "Nozzle-exit conditions"

Zaman, Khairul. "Effect of nozzle exit conditions on subsonic jet noise." In 17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference). American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2704.

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Panda, J., K. Zaman, and R. Seasholtz. "Measurements of initial conditions at nozzle exit of high-speed jets." In 7th AIAA/CEAS Aeroacoustics Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-2143.

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Barre, Sebastien, Christophe Bogey, and Christophe Bailly. "Computation of the Noise Radiated by Jets with Laminar/Turbulent Nozzle-Exit Conditions." In 12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference). American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-2443.

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LEPICOVSKY, J., and W. BROWN. "Effects of nozzle-exit boundary-layer conditions on excitability of heated free jets." In 11th Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2723.

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Bolot, R., D. Klein, and C. Coddet. "Design of a Nozzle Extension for Thermal Spray Under Very Low Pressure Conditions." In ITSC2004, edited by Basil R. Marple and Christian Moreau. ASM International, 2004. http://dx.doi.org/10.31399/asm.cp.itsc2004p0574.

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Abstract Conventional equipments used for low pressure plasma spraying are designed for a chamber pressure of a few tens of mbar. During the past three years, an increasing interest for thermal spray under very low pressure conditions (as low as 1 mbar) was encountered but no significant advances concerning the spray gun design was proposed. However, it is clear that actual tools do not allow providing uniform plasma jets and that the produced jets present successive expansions and constrictions due to a poor adaptation of the nozzle exit pressure regarding to the chamber one. In the present p

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Zhang, Kun, Bo Zhang, Xu Xiang, and Yong Yang. "Numerical Comparison of Operating Conditions and Nozzle Geometry on Injector Performance." In ASME 2013 Heat Transfer Summer Conference collocated with the ASME 2013 7th International Conference on Energy Sustainability and the ASME 2013 11th International Conference on Fuel Cell Science, Engineering and Technology. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/ht2013-17207.

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A model was established to discuss the effect of operating parameters and nozzle shapes on the performance of injectors. The comparison pointed out that heat load has worst effect on injector geometries, while little effect on area ratio. On the other hand, the area ratio is very sensitive to suction temperature, which is critical to injector performance. The least energy loss is achieved when nozzle converges gently at the same nozzle entrance and exit diameter.

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Bishop, Kristen, and William Allan. "Effects of Fuel Nozzle Condition on Gas Turbine Combustion Chamber Exit Temperature Distributions." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23441.

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The effects of fuel nozzle condition on the temperature distributions experienced by the nozzle guide vanes have been investigated using an optical patternator. Average spray cone angle, symmetry, and fuel streaks were quantified. An ambient pressure and temperature combustion chamber test rig was used to capture exit temperature distributions and to determine the pattern factor. The rig tests matched representative engine operating conditions by matching Mach number, equivalence ratio, and fuel droplet size. It was observed that very small deviations (± 10° in spray cone angle) from a nominal

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Lepicovsky, J. "An Experimental Investigation of Nozzle-Exit Boundary Layers of Highly Heated Free Jets." 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-255.

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Kavka, T., R. Henne, and J. Arnold. "Improvement of Plasma Spraying Conditions for SOFC Applications: Effect of Nozzle Geometry and Gas Shrouds." In ITSC2006, edited by B. R. Marple, M. M. Hyland, Y. C. Lau, R. S. Lima, and J. Voyer. ASM International, 2006. http://dx.doi.org/10.31399/asm.cp.itsc2006p0841.

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Abstract Thermal plasma jets interact intensively with the surrounding atmosphere. This interaction leads to strong changes of the plasma jet properties affecting the resulting products. Modification of the nozzle parameters and conditions at the exit of the torch helps to vary and better control the process of plasma jet and ambient air interaction. In the present study, the DC arc plasma torch was equipped with a modified anode nozzle (M2.5) and a surrounding shroud at the jet exit. The process of air entrainment was investigated when shroud gas was supplied producing a protecting envelope t

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Litvinenko, Yu A., G. R. Grek, G. V. Kozlov, A. M. Sorokin, and M. V. Litvinenko. "Development of a free round jet at different conditions at the nozzle exit under an acoustic action." In Progress in Flight Physics. EDP Sciences, 2012. http://dx.doi.org/10.1051/eucass/201203429.

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