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Articles de revues sur le sujet « Space Nozzle »

Auteur : Grafiati
Publié le 4 juin 2021
Mis à jour le 17 février 2022

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1

Lu, Yonghua, Jing Li, Xiang Zhang et Yang Li. « The thrust measurement system research for combined nozzle in small space ». Transactions of the Institute of Measurement and Control 41, no 4 (19 septembre 2018) : 1149–59. http://dx.doi.org/10.1177/0142331218793485.

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For measuring the thrust of combined nozzles in satellite thruster with a small space, the test method that the nozzle directly sprays on the load baffle is employed in this paper. The key problem is how to design the positions of 10 load baffles and how to construct the measurement system. A set of complete and automatic nozzle thrust measurement system is designed and built, and the influence of the load baffle applied on the flow field of nozzles is analyzed using the software FLUENT. Furthermore, the load surface locations of the sensors for the different types of nozzles are analyzed. We draw the conclusion that the load baffle position should range from 4–8 mm for the I-type nozzle and range in 6–12 mm for II-type and III-type nozzle. The correction coefficients of the thrust forces for all channels of the measurement system are determined in the calibration experiment. The uncertainty of measurement system is estimated and the error source of the measurement system is traced. We found that the systematic uncertainty is mainly contributed by the A-type uncertainty which is related with the nozzle dimension and its inner structure. The B-type uncertainty of system is contributed by the force sensor.
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Akib, Yeasir Mohammad, Asif Kabir et Mahdi Hasan. « Characteristics Analysis of Dual Bell Nozzle using Computational Fluid Dynamics ». International Journal of Engineering Materials and Manufacture 4, no 1 (1 mars 2019) : 15–21. http://dx.doi.org/10.26776/ijemm.04.01.2019.02.

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Space exploration and space tourism have now become a raging competition among the developed nations. For this reason, different types of advanced rocket nozzles with prospective privileges are introduced. Altitude adaptive dual bell nozzle will soon replace the conventional nozzles for the first stage rocket launcher. Indeed, this nozzle has auto adaption capability based on altitude. The major feature of a dual bell nozzle is the two bell-shaped contours separated by an inflection point. This nozzle has left rooms for researchers to test different flight conditions and transition characteristics. In this paper, a dual bell nozzle contour has been developed in MATLAB and analysed for different thermodynamic parameters. ANSYS Fluent is used in analysing flow through the nozzle. Shadowgraph imaging technique is used for measuring density gradient and compared it with fluent results. The simulations were performed by using the k-epsilon turbulence model.
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Al-agele, Hadi A., D. M. Mahapatra, Clarence Prestwich et Chad W. Higgins. « Dynamic Adjustment of Center Pivot Nozzle Height : An Evaluation of Center Pivot Water Application Pattern and the Coefficient of Uniformity ». Applied Engineering in Agriculture 36, no 5 (2020) : 647–56. http://dx.doi.org/10.13031/aea.13190.

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Abstract.This study assesses the potential of dynamic nozzle height adjustment for overhead irrigation systems. This system would maintain the nozzle or emitter a constant distance above the crop canopy throughout the growing season and would dynamically respond to variability in canopy height across the field. Within such systems, nozzle height would no longer be fixed in space and time. Nozzle heights would instead vary across space and time. This dynamic system response may therefore have adverse impacts on water application uniformity. The impact of DESA on application uniformity was assessed in three steps. First, changes in individual sprinkler patterns for pressure, nozzle type, flow rate, and nozzle height were measured in controlled experiments. Next, parametrized equations of the individual sprinkler patterns and how they are altered by nozzle height are developed. Next, the Center Pivot Evaluation and Design software was used to simulate theoretical uniformity, and these simulations were tested against field measurements of the coefficient of uniformity. Finally, we use the parameterized equations within the Center Pivot Evaluation and Design software to simulate the coefficient of uniformity for pivots with constant nozzle heights with a random distribution of nozzle heights, which simulate a dynamic elevation system. It was found that the uniformity coefficient decreased by 4-6% as the distribution of heights throughout the pivot become more variable, due to localized dynamic height adjustment. Systems equipped with nozzles with triangular spray patterns were less impacted than systems equipped with nozzles with elliptical spray patterns. Keywords: Keyword. Center pivot, Center Pivot Elevation and Design (CPED), Nozzle height, Sensor, Sprinkler pattern, Uniformity coefficient.
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Khobragade, Nikhil, John Wylie, Jonas Gustavsson et Rajan Kumar. « Control of Flow Separation in a Rocket Nozzle Using Microjets ». New Space 7, no 1 (mars 2019) : 31–42. http://dx.doi.org/10.1089/space.2018.0037.

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Zhang, Feng Hua, Hai Feng Liu, Jun Chao Xu et Chuan Lin Tang. « Experimental Investigation on Cavitation Noise of Water Jet and its Chaotic Behaviour ». Applied Mechanics and Materials 121-126 (octobre 2011) : 3919–24. http://dx.doi.org/10.4028/www.scientific.net/amm.121-126.3919.

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The cavitation noise signals were collected separately for the cavitation nozzle and general nozzle at the target position and the nozzle exit in the condition of different standoff distance. The features of signal’s frequency spectrum and power spectrum were analyzed for different nozzles. Based on chaotic theory, phase space reconstruction was processed and the maximum Lyapunov exponent was calculated separately for each cavitation signal’s time series. Under the condition of this experiment, the difference between the general nozzle and cavitation nozzle was mostly marked at the target position while the standoff distance is 35 mm, which mainly displayed at the high frequency segment. The maximum Lyapunov exponent calculated appeared at standoff distance 35 mm. At the nozzle exit, the noise signal of cavitation nozzle is different from the general nozzle. The difference also displayed at the high frequency segment, and no changing with the standoff distance
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6

Vemula, Rohit Chandra, Jonas Gustavsson et Rajan Kumar. « Rocket Nozzle Thrust and Flow Field Measurements Using Particle Image Velocimetry ». New Space 6, no 1 (mars 2018) : 37–47. http://dx.doi.org/10.1089/space.2017.0045.

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7

Gao, Xiang, Qing Zhen Yang, Hong Zhou et Jian Nan He. « Numerical Simulation on the Infrared Radiation Characteristics of S-Shaped Nozzles ». Applied Mechanics and Materials 482 (décembre 2013) : 282–86. http://dx.doi.org/10.4028/www.scientific.net/amm.482.282.

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Infrared stealth is of great importance to increase the survival ability of the aircraft. The exhaust system is the main radiation source of the aircraft at the rare hemisphere. A program using reverse Monte-Carlo method was developed to calculate the infrared radiation intensity of afterburning turbofan engine under non-afterburning condition, and simulate axisymmetric nozzle and three S-shaped nozzles with different relative eccentric distances. The results demonstrate that: the infrared intensity of S-shaped nozzle is much lower than that of axisymmetric nozzle; S-shaped nozzle can effectively reduce the maximum of IR intensity in the rear hemispheric space; the S-shaped nozzle with the relative eccentric distance of 0.5 can reduce the intensity of infrared radiation in critical detection directions effectively.
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8

Menon, Pranav. « Investigation of Variation in the Performance of an Electro Thermal Thruster with Aerospike Nozzle ». Advanced Engineering Forum 16 (avril 2016) : 91–103. http://dx.doi.org/10.4028/www.scientific.net/aef.16.91.

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One of the most recently developed modes of propulsion is electric propulsion. The commonly used chemical propulsion systems have the advantage of a high Specific Impulse as compared to that of ion propulsion systems. However, owing to the efficacy of ion propulsion systems, it is considered the future of space exploration.Electro thermal thrusters produce thrust by using electrical fields to force hot plasma out of the nozzle with certain exit velocity. The plasma’s exit velocity and the system’s thrust capacity, as of now, are insufficient for space travel to be conducted within a reasonable time. I intend to study the possibility of improving the thruster’s performance by using an aerospike nozzle as an exit nozzle which meets the conditions required for the thruster to function appropriately. I shall be studying the plasma plume exit velocity variation with respect to the nozzles used. Also, a thermal analysis will be conducted in order to find the correct material for the nozzle.
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9

Li, Jue, Zi Rui Lou et Wei Hong. « Research on Effects of Diameter and Arrangement of Nozzles on Combustion and Emissions in Cylinder ». Advanced Materials Research 455-456 (janvier 2012) : 320–26. http://dx.doi.org/10.4028/www.scientific.net/amr.455-456.320.

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Based on the YD4A75-C3 electronically controlled common rail diesel engine, using CFD simulation software, the combustion and emission’s behavior in cylinder was simulated on the numbers, diameter and arrangement of nozzles. The research results showed: in the condition of the certain total nozzle flow area, the proper nozzle numbers could improve fuel’s atomization quality and increase the uniformity degree of gas mixture. The staggered arrangement of nozzles could reduce interference and overlap among the adjacent fuel sprays and increase the air utilization and the space distribution of fuel, finally, the degree of mixing was increased obviously.
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10

Mehta, Yogesh, Vikas N. Bhargav et Rajan Kumar. « Experimental Characterization and Control of an Impinging Jet Issued from a Rocket Nozzle ». New Space 9, no 3 (1 septembre 2021) : 187–201. http://dx.doi.org/10.1089/space.2020.0053.

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11

Zhang, Tian, Deji Jing, Shaocheng Ge, Jiren Wang, Xi Chen et ShuaiShuai Ren. « Dust removal characteristics of a supersonic antigravity siphon atomization nozzle ». Advances in Mechanical Engineering 12, no 12 (décembre 2020) : 168781402097768. http://dx.doi.org/10.1177/1687814020977689.

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To improve the trapping efficiency of respiratory dust by aerodynamic atomization, reduce the energy consumption and the requirements for the working conditions of nozzles and maintain the health and safety of workers, a comparative experiment evaluating aerodynamic atomization dust removal characteristics was conducted with a self-developed supersonic siphon atomization nozzle, which utilizes a Laval nozzle as the core, and an existing ultrasonic atomization nozzle. The experimental results showed that the new type of nozzle, from the perspectives of droplet speed, conservation of water and pressure, range, and attenuation view, completely surpasses the traditional pneumatic atomization nozzle. A supersonic antigravity siphon atomizer produces a cloud fog curtain composed of high-speed droplets and high-speed air. The particle size of the droplets is less than 10 µ. At the same flow rate of water, its dust removal rate is twice as high as that of ultrasonic nozzles. When the dust removal efficiency is the same, the water consumption of the supersonic siphon atomizer nozzle is 1/2, the air flow rate is 1/3, and the power consumption is 1/2 that of the ultrasonic atomizing nozzles. Siphon atomization can siphon at a total air pressure of 0.2 MPa, and the siphon pressure can reach 0.03 MPa at a total air pressure of 0.4 MPa, which increases with the increase in total inlet air pressure. For the first time, the process of siphoning and nozzle internal atomizing in the field of supersonic atomization dust removal is truly realized. The ultrafine sized droplets with high speeds produced by the new nozzle allow them to cover the limited working space in a shorter time, have a more effective trapping effect for a large number of fine dust particles, and quickly suppress the dust with greater kinetic energy. Therefore, the requirements for the working conditions are reduced, which will save more energy compared to the currently used nozzles available on the market.
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12

Fritz, Bradley Keith, Zbigniew Czaczyk et Wesley Clint Hoffmann. « Model based decision support system of operating settings for MMAT nozzles ». Journal of Plant Protection Research 56, no 2 (1 avril 2016) : 178–85. http://dx.doi.org/10.1515/jppr-2016-0030.

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Abstract Droplet size, which is affected by nozzle type, nozzle setups and operation, and spray solution, is one of the most critical factors influencing spray performance, environment pollution, food safety, and must be considered as part of any application scenario. Characterizing spray nozzles can be a timely and expensive proposition if the entire operational space (all combinations of spray pressure and orifice size, what influence flow rate) is to be evaluated. This research proposes a structured, experimental design that allows for the development of computational models for droplet size based on any combination of a nozzle’s potential operational settings. The developed droplet size determination model can be used as Decision Support System (DSS) for precise selection of sprayer working parameters to adapt to local field scenarios. Five nozzle types (designs) were evaluated across their complete range of orifice size (flow rate*) and spray pressures using a response surface experimental design. Several of the models showed high level fits of the modeled to the measured data while several did not as a result of the lack of significant effect from either orifice size (flow rate*) or spray pressure. The computational models were integrated into a spreadsheet based user interface for ease of use. The proposed experimental design provides for efficient nozzle evaluations and development of computational models that allow for the determination of droplet size spectrum and spraying classification for any combination of a given nozzle’s operating settings. The proposed DSS will allow for the ready assessment and modification of a sprayers performance based on the operational settings, to ensure the application is made following recommendations in plant protection products (PPP) labels.
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13

Athota Rathan Babu et.al.,, Athota Rathan Babu et al ,. « Nozzle Contour Design for Space Propulsion Module ». International Journal of Mechanical and Production Engineering Research and Development 7, no 4 (2017) : 351–60. http://dx.doi.org/10.24247/ijmperdaug201735.

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14

Bueno, Mariana Rodrigues, João Paulo Arantes Rodrigues da Cunha et Denise Garcia de Santana. « Drift curves from spray applications on commom bean crop ». Ciência e Agrotecnologia 40, no 6 (décembre 2016) : 621–32. http://dx.doi.org/10.1590/1413-70542016406016716.

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ABSTRACT In order to avoid the occurrence of drift in pesticide applications, it is fundamental to know the behavior of sprayed droplets. This study aimed to determine drift curves in pesticide applications on common bean crop under brazilian weather conditions, using different nozzle types and compared them with the "German" and "Dutch" drift prediction models. The experiment was conducted in Uberlândia, Minas Gerais/Brazil, in completely randomized design with ten replications and 4 x 20 split-plot arrangement in space. Drift deposited on collectors located over ground level was resulted by 150 L ha-1 carrier volume applications through four nozzle types (XR 11002 (fine droplets); AIXR 11002 (coarse droplets); TT 11002 (medium droplets); TTI 11002 (extremely coarse droplets)), collected in 20 downwind distances, parallel to the crop line outside the target area, spaced by 2.5 m. The tracer rhodamine B was added to the spray to be quantified by fluorimetry. Drift prediction models adjusted by exponential functions were obtained considering the 90th percentile for XR, TT, AIXR and TTI nozzles. It is suggested to use the estimated drift models from this study for each nozzle type in drift prediction evaluations on bean crops under brazilian weather conditions.
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15

Hardalupas, Y., et J. H. Whitelaw. « Interaction Between Sprays From Multiple Coaxial Airblast Atomizers ». Journal of Fluids Engineering 118, no 4 (1 décembre 1996) : 762–71. http://dx.doi.org/10.1115/1.2835507.

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Phase Doppler measurements of size, velocity, liquid flux, and average mass fractions were obtained in sprays produced by three identical coaxial airblast atomizers, with their axes placed in a triangular arrangement at distances of two air jet diameters from each other; the arrangement simulates the spray interaction in the preburner of the space shuttle main engine with water and air respectively replacing the liquid oxygen and hydrogen of the preburner sprays. Each nozzle comprised a liquid jet with exit diameter of 2.3 mm centred in a 8.95 mm diameter air stream. Two liquid flowrates were examined, while the air flowrate was kept constant, resulting in Weber number at the exit of the nozzle around 1100, air-to-liquid momentum ratio 8.6 and 38, velocity ratio 24 and 51, mass flowrate ratio 0.35 and 0.75, liquid jet Reynolds number 10,000 and 21,000 and air jet Reynolds number around 108,000. The air flow characteristics were compared to the flow without liquid injection. Up to 10 air jet diameters from the nozzle exit, individual spray characteristics dominated and maximum Sauter mean diameters, typically around 150 μm, and liquid flux were observed on the geometrical axes of the nozzles. Spray merging was strong in the region between the nozzle axes, where the Sauter mean diameter reduced and the liquid flux and the mean and rms of the fluctuations of the axial velocity of the droplets and the air flow increased relative to the single spray. Downstream of 25 air jet diameters from the nozzle exit, the multiple sprays merged to a single spray-like flow produced by a nozzle located at the centre of the triangular region between the nozzle axes. Reduction of the liquid flowrate by 50 percent, improved atomization by 25 percent, shortened the axial distance from the nozzles where the individual spray characteristics disappeared by 30 percent and increased the air flow turbulence by 20 percent. Droplet coalescence was negligible for high liquid flowrates, but for reduced liquid flowrates coalescence became important and the Sauter mean diameter increased with the axial distance from the exit by around 15 percent. Spray merging increased the air flow turbulence and the local mass fraction distribution of the air in the region between the nozzle axes by around 50 and 40 percent respectively relative to the single sprays, resulting in a fuel rich region with increased gas flow turbulence which may influence the ignition process in the preburner of the space shuttle main engine.
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Martin, Daniel E., Mohamed A. Latheef, Juan D. Lopez et Sara E. Duke. « Aerial Application Methods for Control of Weed Species in Fallow Farmlands in Texas ». Agronomy 10, no 11 (12 novembre 2020) : 1764. http://dx.doi.org/10.3390/agronomy10111764.

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Prolific growth of weeds, especially when followed by abundant rainfall, is common in Texas farmlands during early winter and progresses into spring when farmers begin chiseling and disking operations for spring-seeded cropping. This research sought to develop aerial application technologies designed to control unwanted vegetation in croplands left fallow until spring. The aerial nozzles used in the study were conventional hydraulic (CP), rotary atomizer, and electrostatically (ES) charged nozzles. Glyphosate at 0.4145 kg ae·ha−1 was applied on weeds using a fixed-wing aircraft equipped with various aerial nozzles used as treatments. The spray application rate for the conventional and rotary atomizer nozzles was 28.1 L·ha−1, while that for the ES charged nozzle was 9.4 L·ha−1. Aerial and ground-based remote sensing and visual estimates quantified weed vigor and canopy health. Both the CP and rotary atomizer nozzles were efficacious in suppressing weeds. ES charged on nozzles at one-third of the spray application rate of the CP and the rotary atomizer nozzles were equally effective in reducing weed vigor. More aerially applied replicated field research trials conducted over time and space are needed to unravel the differences between aerial spray nozzle technologies for controlling weed populations in Texas farmlands.
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De Chant, L. J. « Subsonic Elector Nozzle Limiting Flow Conditions ». Journal of Engineering for Gas Turbines and Power 125, no 3 (1 juillet 2003) : 851–54. http://dx.doi.org/10.1115/1.1581890.

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This paper describes an analytical method used to provide information concerning limiting flows for subsonic ejector nozzles. Three potential limiting flows have been identified and modeled using reduced control volume based analysis: (1) incipient reverse flow into the secondary inlet, (2) choked flow in the secondary inlet, and (3) choked flow in the exit mixing stream. Comparison of the methods developed here with the classical control volume portion of an ejector nozzle code have been performed and show good agreement. As such, it is concluded, that within the scope of one-dimensional control-volume based computations, that the methods developed here provide an efficient tool to help delimit the design space acceptable for ejector operation.
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Flock, Andreas K., et Ali Gülhan. « Design of converging-diverging nozzles with constant-radius centerbody ». CEAS Space Journal 12, no 2 (15 novembre 2019) : 191–201. http://dx.doi.org/10.1007/s12567-019-00286-4.

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AbstractSeveral flow phenomena, such as recirculating wake flows or noise generation, occur in aerodynamic configurations with backward facing steps. In this context, subsonic nozzles with constant-radius centerbodies exist, which enable fundamental research of these phenomena for $$M < 1$$M<1. For the supersonic regime, however, the existing database and knowledge are limited. Therefore, this work presents a design approach for a converging-diverging nozzle with constant-radius centerbody. For the nozzle throat, Sauer’s method is modified to include a centerbody. The method of characteristics is used for the subsequent supersonic portion. Comparing the analytical calculations to numerical simulations results in very good agreement and therefore underlines the feasibility of the chosen approach. Viscosity reduced the Mach number on the exit plane by 1.0–1.2% and therefore had little influence.
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Sharapov, A. I., A. A. Chernykh et A. V. Peshkova. « Supersonic flow of two-phase gas- droplet flows in nozzles ». Power engineering : research, equipment, technology 21, no 3 (29 novembre 2019) : 86–98. http://dx.doi.org/10.30724/1998-9903-2019-21-3-86-96.

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For practical applications, the description of processes occurring during the flow of two-phase gas-liquid mixtures requires a simple physical and mathematical model that describes the behavior of a two-phase medium in the entire range of phase concentrations changes and in a wide range of pressure changes. Problems of this kind arise in various branches of industry and technology. In the space industry, one often has to deal with the movement of various gases in rocket nozzles, consider the combustion, condensation of various vapors on the nozzle walls and their further impact on the velocity sublayer at the nozzle wall. The large acoustic effect arising from the engines affects the gas-liquid mixture in the nozzles of rocket engines. In the metal industry, metal cooling occurs with the help of nozzles in which the emulsion mixture is supplied under high overpressure. But this is only a short list of applied issues in which one has to deal with a problem of this type. The paper presents the results and directions of study of the problems of two-phase dispersed gas-droplet flows in the nozzles. The main methods of investigation of two- phase heterogeneous flows are described. The main characteristics of heterogeneous two-phase flows in the nozzles, which were confirmed by experimental results, are presented. The calculation of the air-droplet flow in the Laval nozzle is given. The technique, which is based on integral energy equations for two-phase dispersed flows, is described. The main problems and questions concerning the further description and studying of two-component flows are stated.
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Papon, Easir Arafat, Anwarul Haque et Muhammad Ali Rob Sharif. « Numerical study for the improvement of bead spreading architecture with modified nozzle geometries in additive manufacturing of polymers ». Rapid Prototyping Journal 27, no 3 (4 février 2021) : 518–29. http://dx.doi.org/10.1108/rpj-05-2019-0142.

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Purpose This paper aims to develop a numerical model of bead spreading architecture of a viscous polymer in fused filament fabrication (FFF) process with different nozzle geometry. This paper also focuses on the manufacturing feasibility of the nozzles and 3D printing of the molten beads using the developed nozzles. Design/methodology/approach The flow of a highly viscous polymer from a nozzle, the melt expansion in free space and the deposition of the melt on a moving platform are captured using the FLUENT volume of fluid (VOF) method based computational fluid dynamics code. The free surface motion of the material is captured in VOF, which is governed by the hydrodynamics of the two-phase flow. The phases involved in the numerical model are liquid polymer and air. A laminar, non-Newtonian and non-isothermal flow is assumed. Under such assumptions, the spreading characteristic of the polymer is simulated with different nozzle-exit geometries. The governing equations are solved on a regular stationary grid following a transient algorithm, where the boundary between the polymer and the air is tracked by piecewise linear interface construction (PLIC) to reconstruct the free surface. The prototype nozzles were also manufactured, and the deposition of the molten beads on a flatbed was performed using a commercial 3D printer. The deposited bead cross-sections were examined through optical microscopic examination, and the cross-sectional profiles were compared with those obtained in the numerical simulations. Findings The numerical model successfully predicted the spreading characteristics and the cross-sectional shape of the extruded bead. The cross-sectional shape of the bead varied from elliptical (with circular nozzle) to trapezoidal (with square and star nozzles) where the top and bottom surfaces are significantly flattened (which is desirable to reduce the void spaces in the cross-section). The numerical model yielded a good approximation of the bead cross-section, capturing most of the geometric features of the bead with a reasonable qualitative agreement compared to the experiment. The quantitative comparison of the cross-sectional profiles against experimental observation also indicated a favorable agreement. The significant improvement observed in the bead cross-section with the square and star nozzles is the flattening of the surfaces. Originality/value The developed numerical algorithm attempts to address the fundamental challenge of voids and bonding in the FFF process. It presents a new approach to increase the inter-bead bonding and reduce the inter-bead voids in 3D printing of polymers by modifying the bead cross-sectional shape through the modification of nozzle exit-geometry. The change in bead cross-sectional shape from elliptical (circular) to trapezoidal (square and star) cross-section is supposed to increase the contact surface area and inter-bead bonding while in contact with adjacent beads.
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Cimini, M., E. Martelli et M. Bernardini. « Numerical Analysis of Side-loads Reduction in a Sub-scale Dual-bell Rocket Nozzle ». Flow, Turbulence and Combustion 107, no 3 (28 janvier 2021) : 551–74. http://dx.doi.org/10.1007/s10494-021-00243-4.

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AbstractA calibrated delayed detached eddy simulation of a sub-scale cold-gas dual-bell nozzle flow at high Reynolds number and in sea-level mode is carried out at nozzle pressure ratio NPR = 45.7. In this regime the over-expanded flow exhibits a symmetric and controlled flow separation at the inflection point, that is the junction between the two bells, leading to the generation of a low content of aerodynamic side loads with respect to conventional bell nozzles. The nozzle wall-pressure signature is analyzed in the frequency domain and compared with the experimental data available in the literature for the same geometry and flow conditions. The Fourier spectra in time and space (azimuthal wavenumber) show the presence of a persistent tone associated to the symmetric shock movement. Asymmetric modes are only slightly excited by the shock and the turbulent structures. The low mean value of the side-loads magnitude is in good agreement with the experiments and confirms that the inflection point dampens the aero-acoustic interaction between the separation-shock and the detached shear layer.
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Sun, Dechuan, Tianyou Luo et Qiang Feng. « New Contour Design Method for Rocket Nozzle of Large Area Ratio ». International Journal of Aerospace Engineering 2019 (20 décembre 2019) : 1–8. http://dx.doi.org/10.1155/2019/4926413.

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A rocket engine for space propulsion usually has a nozzle of a large exit area ratio. The nozzle efficiency is greatly affected by the nozzle contour. This paper analysed the effect of the constant capacity ratio in Rao’s method through the design process of an apogee engine. The calculation results show that increasing the heat capacity ratio can produce an expansion contour of smaller expansion angle and exit area ratio. A simple modification of Rao’s method based on thermally perfect gas assumption was made and verified to be more effective. The expansion contour designed by this method has much thinner expansion section and higher performance. For the space engine, a new extension contour type for the end section of the nozzle is proposed. The extension curve bent outward with increasing expansion angle increases the vacuum specific impulse obviously.
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Hiraiwa, Tetsuo, Sadatake Tomioka, Shuuichi Ueda, Tohru Mitani, Masahiko Yamamoto et Masashi Matsumoto. « Performance variation of scramjet nozzle at various nozzle pressure ratios ». Journal of Propulsion and Power 11, no 3 (mai 1995) : 403–8. http://dx.doi.org/10.2514/3.23858.

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Mandrovskiy, K. P., et Ya S. Sadovnikova. « NUMERICAL RESEARCH OF QUALITY CHARACTERISTICS OF REAGENT DISTRIBUTION BY COMBINED ROAD MACHINE ». Spravochnik. Inzhenernyi zhurnal, no 279 (juin 2020) : 18–23. http://dx.doi.org/10.14489/hb.2020.06.pp.018-023.

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From the theory of aerohydrodynamics it is known that the design of hydraulic nozzles and the modes of their operation determine the nature of the distribution of droplets in space and the efficiency of the process. The subject of the research is the characteristics of the distribution quality of the liquid reagent, namely, the speed of dropping of droplets from the disk and the radius of the treatment zone formed by flying droplets on the coating. The question of the dispersion of the spray torch of a low-viscosity liquid, its role in the formation of the basic kinematic characteristics of moving drops, is considered. The article provides a numerical calculation and analysis of the effect of the dispersion of droplets of a distributed liquid (reagent) on the rate of dropping of droplets from a rotating disk and on the radius of the coating treatment zone. For research, two values of nozzle nozzle openings and a wide range of variation in the diameters of reagent droplets were selected. Based on the mathematical models previously developed by the authors of the process of dropping droplets from the nozzle and the movement of droplets in the air, implemented as part of a software product, the velocity of dropping of droplets from the nozzle nozzle and the rate of dropping of droplets from the disk at a given pressure were calculated. A cycle of calculations of the radius of the coating treatment zone was carried out with varying work and geometric characteristics of hydraulic equipment, providing high-quality and cost-effective implementation of the anti-icing reagent distribution process.
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Mandrovskiy, K. P., et Ya S. Sadovnikova. « NUMERICAL RESEARCH OF QUALITY CHARACTERISTICS OF REAGENT DISTRIBUTION BY COMBINED ROAD MACHINE ». Spravochnik. Inzhenernyi zhurnal, no 279 (juin 2020) : 18–23. http://dx.doi.org/10.14489/hb.2020.06.pp.018-023.

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From the theory of aerohydrodynamics it is known that the design of hydraulic nozzles and the modes of their operation determine the nature of the distribution of droplets in space and the efficiency of the process. The subject of the research is the characteristics of the distribution quality of the liquid reagent, namely, the speed of dropping of droplets from the disk and the radius of the treatment zone formed by flying droplets on the coating. The question of the dispersion of the spray torch of a low-viscosity liquid, its role in the formation of the basic kinematic characteristics of moving drops, is considered. The article provides a numerical calculation and analysis of the effect of the dispersion of droplets of a distributed liquid (reagent) on the rate of dropping of droplets from a rotating disk and on the radius of the coating treatment zone. For research, two values of nozzle nozzle openings and a wide range of variation in the diameters of reagent droplets were selected. Based on the mathematical models previously developed by the authors of the process of dropping droplets from the nozzle and the movement of droplets in the air, implemented as part of a software product, the velocity of dropping of droplets from the nozzle nozzle and the rate of dropping of droplets from the disk at a given pressure were calculated. A cycle of calculations of the radius of the coating treatment zone was carried out with varying work and geometric characteristics of hydraulic equipment, providing high-quality and cost-effective implementation of the anti-icing reagent distribution process.
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26

Riedelbauch, Stefan, et Claus Weiland. « Inviscid Laval-nozzle flowfield calculation ». Journal of Spacecraft and Rockets 25, no 1 (janvier 1988) : 88–90. http://dx.doi.org/10.2514/3.25993.

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Thompson, Brian E., Olivier Bouchery et K. D. Lowney. « Flow through a submerged nozzle ». Journal of Spacecraft and Rockets 32, no 6 (novembre 1995) : 986–92. http://dx.doi.org/10.2514/3.26719.

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Yoo, Jae-Seok. « First Korea Space Launch Vehicle Kick Motor Movable Nozzle Motion ». Journal of Spacecraft and Rockets 47, no 1 (janvier 2010) : 153–68. http://dx.doi.org/10.2514/1.44921.

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Fortov, V. E., Yu S. Solomonov, V. V. Golub, T. V. Bazhenova, T. A. Bormotova, V. V. Volodin, V. P. Efremov, A. A. Makeich et S. B. Shcherbak. « Shock-wave egress from a nozzle into a bounded space ». Doklady Physics 47, no 12 (décembre 2002) : 856–58. http://dx.doi.org/10.1134/1.1536215.

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Chen, Huan, Sheng Li Wei et Dong Tang. « Numerical Simulation on the Effects of Angle of Nozzle on Combustion and Emission for Diesel Engine ». Advanced Materials Research 614-615 (décembre 2012) : 404–8. http://dx.doi.org/10.4028/www.scientific.net/amr.614-615.404.

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A double ω-combustion chamber matched with a double-row nozzle combustion system was proposed to improve the spray space distribution and the mixture formation quality for diesel engines. The cylinder spray, mixture formation and combustion process of a double ω-combustion chamber were simulated by using AVL FIRE software. With different nozzle angles, the effect of which on air velocity, concentration and temperature fields as well as combustion and emission characteristics in the combustion chamber was analyzed. The results show that the spray angle of the nozzle has a great influence on combustion and emission performance. Using the double-row nozzle injector can effectively improve the quality of the mixture, moreover, compared with single-row nozzle injector, the max soot emission was reduced by 57.8% and the ultimate formation was also lower.
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Rommel, T., G. Hagemann, C. A. Schley, G. Krulle et D. Manski. « Plug Nozzle Flowfield Analysis ». Journal of Propulsion and Power 13, no 5 (septembre 1997) : 629–34. http://dx.doi.org/10.2514/2.5227.

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Tillman, T. G., R. W. Paterson et W. M. Presz. « Supersonic nozzle mixer ejector ». Journal of Propulsion and Power 8, no 2 (mars 1992) : 513–19. http://dx.doi.org/10.2514/3.23506.

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Dutton, J. C. « Swirling supersonic nozzle flow ». Journal of Propulsion and Power 3, no 4 (juillet 1987) : 342–49. http://dx.doi.org/10.2514/3.22996.

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Pirker, K., et U. Knott. « Technology Demonstration Nozzle for Mach 7 Turboramjets ». Journal of Engineering for Gas Turbines and Power 117, no 3 (1 juillet 1995) : 401–5. http://dx.doi.org/10.1115/1.2814109.

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Under the German Hypersonic Technology Program, future-oriented designs and technologies for reusable space vehicles, such as SA¨NGER, are being developed. Pioneering the way in a new field of technology, MTU constructed and tested, with success from the very beginning, an actively cooled, asymmetric rectangular nozzle (SERN—single expansion ramp nozzle) of advanced design, characterized by the following innovative features: • rectangular, flap-controlled variable flow cross section; • liquid-hydrogen-cooled structures; • high-temperature-resistant sealing system for variable nozzle flaps; and • uncooled expansion ramp in carbon/carbon composite with anti-oxidation coating. Development of the nozzle called for the mastery of new manufacturing techniques; proof of concept was provided in the successful performance of initial tests of 300 second duration.
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Chutkey, Kiran, B. Vasudevan et N. Balakrishnan. « Analysis of Annular Plug Nozzle Flowfield ». Journal of Spacecraft and Rockets 51, no 2 (mars 2014) : 478–90. http://dx.doi.org/10.2514/1.a32617.

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Ruffin, Stephen M., Ethiraj Venkatapathy, Earl R. Keener et Frank W. Spaid. « Hypersonic single expansion ramp nozzle simulations ». Journal of Spacecraft and Rockets 29, no 6 (novembre 1992) : 749–55. http://dx.doi.org/10.2514/3.25527.

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Boraas, S. « Spacecraft contamination from scarfed nozzle exhausts ». Journal of Spacecraft and Rockets 24, no 6 (novembre 1987) : 539–45. http://dx.doi.org/10.2514/3.25950.

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Spaid, Frank W., et Earl R. Keener. « Hypersonic Nozzle-Afterbody Experiment - Flowfield surveys ». Journal of Spacecraft and Rockets 33, no 3 (mai 1996) : 333–38. http://dx.doi.org/10.2514/3.26764.

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Stelmach, Tomasz. « Numerical investigation of flow distribution in tubular space of fin-and-tube heat exchanger ». MATEC Web of Conferences 240 (2018) : 02011. http://dx.doi.org/10.1051/matecconf/201824002011.

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This paper presents the experimental and numerical investigation of flow distribution in the tubular space of cross-flow fin-and-tube heat exchanger. The tube bundle with two rows arranged in staggered formation is considered. A standard heat exchanged manifold, with inlet nozzle pipe located asymmetrically is considered. The outlet nozzle pipe is located in the middle of the outlet manifold. A developed experimental setup allows one to measure volumetric flow rate in heat exchanger tubes using the ultrasonic flowmeters. The measurement results are then compared with CFD simulation in ANSYS CFX code using the SSG Reynolds Stress turbulence model, and a good agreement is found for tube Re numbers varied from 1800 to 3100.
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Chandika, S., R. Asokan et K. C. K. Vijayakumar. « Flow characteristics of the diffuser/nozzle micropump—A state space approach ». Flow Measurement and Instrumentation 28 (décembre 2012) : 28–34. http://dx.doi.org/10.1016/j.flowmeasinst.2012.06.003.

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41

Beneda, Károly, Rudolf Andoga et Ladislav Főző. « Linear Mathematical Model for State-Space Representation of Small Scale Turbojet Engine with Variable Exhaust Nozzle ». Periodica Polytechnica Transportation Engineering 46, no 1 (16 mars 2017) : 1. http://dx.doi.org/10.3311/pptr.10605.

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The goal of this article is to develop a linear mathematical model for a small scale turbojet engine with variable convergent nozzle, and validate it on existing laboratory hardware owned by the authors’ Departments.Control of gas turbine engines plays an essential role in the safety of aviation. Although its role is constantly expanding, ranging from pilot workload reduction to detailed diagnostics, the basic competence is to regulate the thrust output of the power plant with maximum available accuracy, rapidity, stability, and robustness. The linear quadratic control is one possible solution for the above mentioned criteria.Although civil aircraft engines include fixed exhaust nozzle geometry, in military applications the exhaust nozzle geometry is also adjustable to reach optimum efficiency due to better matching of individual engine components, etc.In the present article the authors deduce the members of state space governing equations to acquire the basis of the LQ control.The established model is based on the physical laws describing the operational behavior of the engine as well as its complexity should be reduced to an acceptable level where still enough details remain to reflect the nature of the controlled object.
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Boccaletto, Luca, et Jean-Paul Dussauge. « High-Performance Rocket Nozzle Concept ». Journal of Propulsion and Power 26, no 5 (septembre 2010) : 969–79. http://dx.doi.org/10.2514/1.48904.

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Wilson, Erich A., Dan Adler et Pinhas Bar-Yoseph. « Thrust-Vectoring Nozzle Performance Modeling ». Journal of Propulsion and Power 19, no 1 (janvier 2003) : 39–47. http://dx.doi.org/10.2514/2.6100.

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Statnikov, Vladimir, Matthias Meinke et Wolfgang Schröder. « Reduced-order analysis of buffet flow of space launchers ». Journal of Fluid Mechanics 815 (14 février 2017) : 1–25. http://dx.doi.org/10.1017/jfm.2017.46.

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A reduced-order analysis based on optimized dynamic mode decomposition (DMD) is performed on the turbulent wake of a generic axisymmetric space launcher configuration computed via a zonal large-eddy simulation at the free stream Mach number $Ma_{\infty }=0.8$ and the Reynolds number based on the main body diameter $Re_{D}=6\times 10^{5}$ to investigate the buffet phenomenon. The transonic wake is characterized by an unsteady recirculation region occurring around the nozzle due to the separation of the turbulent boundary layer at the main body shoulder and subsequent dynamic interaction of the unstable free-shear layer with the nozzle surface. This results in strongly periodic and antisymmetric wall pressure fluctuations, for which three distinct frequency ranges are identified using conventional spectral analysis, i.e. $Sr_{D}\approx 0.1$, $Sr_{D}\approx 0.2$ and $Sr_{D}\approx 0.35$. For the spatially integrated side (buffet) loads on the nozzle, the second range is found to be energetically most dominant. To clarify the origin of the detected wake dynamics, the underlying spatio-temporal coherent modes are extracted using DMD. Subsequent analysis of the reduced-order modelled flow field based on the identified DMD modes reveals that at $Sr_{D}\approx 0.1$ a longitudinal cross-pumping motion of the separation bubble takes place, caused by a harmonic antisymmetric oscillation of the main recirculation vortex in the streamwise direction. At $Sr_{D}\approx 0.2$, a cross-flapping motion of the shear layer is determined, triggered by antisymmetric vortex shedding which is in phase with the cross-pumping motion such that it occurs at twice the frequency value. The last range of $Sr_{D}\approx 0.35$ is attributed to a swinging motion of the shear layer caused by a higher harmonic of the vortex shedding mode. Conclusively, the controversial aspect of the true three-dimensional shape of the antisymmetric mode at $Sr_{D}\approx 0.2$ that dominates the buffet phenomenon is scrutinized. Inclined elongated closed-loop vortices are identified that are shed in alternating sequence from azimuthally opposite positions in a longitudinal plane of symmetry that changes its momentary orientation irregularly, maintaining an axisymmetric time-averaged field and spatially isotropic buffet loads.
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Chen, Fang-Jenq, Stephen P. Wilkinson et Ivan E. Beckwith. « Goertler instability and hypersonic quiet nozzle design ». Journal of Spacecraft and Rockets 30, no 2 (mars 1993) : 170–75. http://dx.doi.org/10.2514/3.11525.

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Lacey, John, Yasutoshi Inoue, Akio Higashida, Manabu Inoue, Kouichi Ishizaka et John J. Korte. « Mach 10 Hypersonic Nozzle : Improved Flow Quality ». Journal of Spacecraft and Rockets 40, no 1 (janvier 2003) : 126–31. http://dx.doi.org/10.2514/2.3925.

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Adavbiele, A. S., et L. A. Salami. « Performance Optimization of a Thrust-Vectoring Nozzle ». Advanced Materials Research 18-19 (juin 2007) : 407–13. http://dx.doi.org/10.4028/www.scientific.net/amr.18-19.407.

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This study employed Computational Fluid Dynamics, CFD solution to configure the entire shape of the nozzle. The problems arising from the initial geometrical shape obtained using one-dimensional approach were highlighted. Then with a two-dimensional approach and coded FORTRAN programs, the convergent portion was handled with time matching CFD while the divergent portion was handled with space matching CFD. A post-processing results analysis shows that the results are in agreement with that obtained with the analytical approach. This research has demonstrated significant and tangible benefits of the use of CFD numerical experimentation to optimize the shape of the nozzle. These benefits are not solely limited to performance enhancements, but solution reliability and algorithm development.
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48

Weclas, M., et J. Cypris. « Characterization of the distribution-nozzle operation for mixture homogenization by a late-diesel-injection strategy ». Proceedings of the Institution of Mechanical Engineers, Part D : Journal of Automobile Engineering 226, no 4 (3 octobre 2011) : 529–46. http://dx.doi.org/10.1177/0954407011420499.

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In order to realize a homogeneous combustion process it is necessary to decouple this combustion process from fuel injection. This homogeneous combustion process requires the charge to be homogeneous prior to simultaneous volumetric ignition. This kind of ignition is a self-ignition process requiring control of the ignition timing. A late-injection strategy as used in a conventional diesel engine permits control of the ignition timing; however, the time available for mixture formation and the homogenization process is very limited. The present paper deals with a distribution-nozzle concept which combines both strategies: a late-injection strategy for controlling the ignition timing with significantly accelerated fuel distribution in space and corresponding mixture homogenization. The distribution-nozzle concept combines a conventional diesel nozzle with a porous element (ring) positioned in proximity to the nozzle outlet. Because of multi-jet splitting as a result of the diesel-jet interaction with a porous structure, the fuel leaving the porous ring spreads widely in space. Additionally, a very effective fuel vaporization process occurs within the porous structure, supporting quick mixture formation. The paper describes both the fuel distribution in space and its vaporization for different configurations of the distribution elements, the injection pressure, and the porous ring temperature. In comparison with a free diesel injection, the distribution nozzle results in a significantly increased fuel surface area, a reduced jet penetration length, a reduced jet velocity, and very quick fuel vaporization. This process is three dimensional in nature. Depending on the distribution-element structure, the geometry, and its temperature, as well as the injection pressure, the contributions of multi-jet splitting, and fuel vaporization, are different with respect to the surface area, penetration length, and exit velocity, as well as intensity distribution. Generally, at higher injection pressures these parameters are less temperature dependent, except for the fact that the intensity distribution is a function of the fuel vapour’s concentration.
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Kochergin, Anatoly, et Valeeva Ksenia. « CALCULATION OF THE INTEGRAL NOISE LEVEL AT A FIELD POINT OF A FREE SUPERSONIC JET OF A ROCKET ENGINE ». Akustika 36, no 36 (2020) : 22–24. http://dx.doi.org/10.36336/akustika20203622.

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The paper considers an acoustic field created by a supersonic jet (CES) of a rocket engine freely flowing into flooded space. The acoustic field was presented in the form of a diagram of noise isobars, from which it can be seen that the acoustic field is formed by two effective noise sources: the nearest one, lying at a distance of 5-10 calibers from the nozzle cut and the far one, lying at a distance of 15-30 calibers from the nozzle cut.
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Vinod, G., S. Renjith et V. Thaddeus Basker. « Thermo Structural Analysis of Carbon-Carbon Nozzle Exit Cone for Rocket Cryo Engines ». Applied Mechanics and Materials 877 (février 2018) : 320–26. http://dx.doi.org/10.4028/www.scientific.net/amm.877.320.

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Launch and space vehicle structures are required to be extremely weight efficient. The need to achieve the performance required for the engine in the upper stage of a launch vehicle, increase the payload capacity drives rocket engine manufacturers to seek higher thrust level, specific impulse and thrust to weight ratio. The use of high temperature C-C composite materials is an efficient way to reach these objectives by allowing use of high expansion ratio. Nozzle extensions benefiting of the outstanding thermal, mechanical and fatigue resistance of these materials to decrease mass and featuring high temperature margins. A three-directionally reinforced (3D) carbon-carbon (c-c) material nozzle exit cone is selected for the current study. C-C composite exit nozzle must possess excellent stability and strength under extreme conditions for a specified amount of time. Carbon-carbon composites are appropriate materials for applications that require high specific strength at elevated temperatures. The paper describes the thermo structural analysis of a typical c/c nozzle exit cone.
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