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Articles de revues sur le sujet « Dual-bell nozzle »

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Auteur : Grafiati
Publié le 14 mars 2023
Mis à jour le 7 juillet 2024

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1

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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2

Dubrovskyi, Ivan. « Результати проектування надзвукового сопла з подвійним розширенням для рідинного ракетного двигуна першого ступеня методами обчислювального аналізу ». Aerospace Technic and Technology, no 6 (6 décembre 2023) : 14–21. http://dx.doi.org/10.32620/aktt.2023.6.02.

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The subject of this study is dual-bell supersonic nozzles of liquid rocket engines. The goal is to design a dual-bell supersonic nozzle that will provide maximum thrust for a liquid rocket engine in the first stage of a launch vehicle by solving an optimization problem using numerical simulation methods. The goal of the study is to choose the exit pressures of each part of the dual-bell nozzle based on the known flight trajectory of the launch vehicle, set and solve the problem of optimizing the dual-bell nozzle contour, and assess the impact of the use of a dual-bell nozzle on the efficiency of a liquid-propellant rocket engine. The methods used are: numerical methods for solving the hyperbolic system of unsteady equations of gas dynamics and multidimensional minimization problems. The following results were obtained. The formulation and solution of the optimization problem of the contour of a dual-bell supersonic nozzle, considering the design limitations in the form of a fixed length of the nozzle, is carried out. By analyzing the flight path of the first stage of the launch vehicle, a first approximation of the nozzle contour was obtained. For further calculations, both sections were approximated by parabolas, the coefficients of which, together with the lengths of the sections, formed a vector of optimized parameters. An expression for the axial component of thrust with the opposite sign was used as the objective function to solve the minimization problem. Because of solving the optimization problem, a dual-bell nozzle contour was designed to provide maximum thrust. An assessment of the effectiveness of his work was also conducted. The calculated value of the average along the trajectory of the specific impulse when using a dual-bell nozzle was higher by 1.6% than when using a standard nozzle. Conclusions. The scientific novelty of the obtained results is as follows: the design of the dual-bell nozzle contour was performed by solving the problem of multidimensional optimization, taking into account the design constraints, and using computational analysis methods
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3

HAIF, Sidali, Hakim KBAB et Amina BENKHEDDA. « Altitude-compensating axisymmetric supersonic nozzle design and flow analysis ». INCAS BULLETIN 15, no 2 (9 juin 2023) : 33–47. http://dx.doi.org/10.13111/2066-8201.2023.15.2.4.

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Altitude-adapted nozzles are designed to facilitate flow adaptation during rocket ascent in the atmosphere, without requiring mechanical activation. As a consequence, the performance of the nozzle is significantly improved. The aim of this study is to develop a new profile of axisymmetric supersonic nozzles adapted at altitude (Dual Bell Nozzle with Central Body), which is characterized by an E-D nozzle as a basic profile. The performances obtained for this nozzle (E-D Nozzle) are then compared to those of a Plug nozzle. The E-D nozzle shows significant performance advantages over the Plug nozzle, including a 13.02% increase in thrust, knowing that the length of the E-D nozzle is half that of the Plug nozzle under the same design conditions. Finally, viscous calculations using the k-ω SST turbulence model were conducted to compare the performance of the dual bell nozzle with central body (DBNCB) and the E-D nozzle with the same cross-sectional ratio, and to assess the impact of nozzle pressure ratio (NPR) variations on the operation mode of the DBNCB. The results obtained show that the DBNCB offers the best performance in most phases of flight.
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4

Samantra, Ashis Kumar, K. S. Santhosh, Khalid Rashid et A. Jayashree. « Study of expansion ratio on dual bell nozzle of LOX-RP1 engine for replacing the existing bell nozzle to dual bell nozzle ». IOP Conference Series : Materials Science and Engineering 912 (12 septembre 2020) : 042039. http://dx.doi.org/10.1088/1757-899x/912/4/042039.

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5

YONEZAWA, Koichi. « 0143 Jet Oscillation in Dual-Bell Nozzle ». Proceedings of the Fluids engineering conference 2012 (2012) : 91–92. http://dx.doi.org/10.1299/jsmefed.2012.91.

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6

Ternova, K. V. « Effect of the length of truncated nozzle with a tip on its thrust characteristics ». Technical mechanics 2022, no 4 (15 décembre 2022) : 26–34. http://dx.doi.org/10.15407/itm2022.04.026.

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Nowadays, for solving new problems, rocket engine nozzle developers are increasingly turning to non- traditional nozzle configurations that differ from the classic Laval one. A relatively new line in the design of supersonic nozzles is the development of the so-called bell-shaped nozzle, which, unlike the classical Laval nozzle, has a larger angle of entry into the supersonic part of the nozzle. In this case, dual bell nozzles, which have two flow expansion sections in their supersonic part, are considered. However, the effect of the length ratio of the two flow expansion sections of a truncated nozzle on its characteristics has not yet been studied. The goal of this work is to determine the effect of the length of the upstream conical supersonic section on the static pressure distribution in the nozzle and its thrust characteristics with the shape of the bell-shaped tip kept unchanged. The nozzle characteristics were studied using the ANSYS Fluent computing package. It was shown that the flow patterns in the nozzle (velocity fields) change with the length of the conical part upstream of the tip and the underexpansion degree. Under terrestrial conditions (Pн = 1 bar), all variants show a developed separation zone that starts from the corner point where the tip is connected to the conical part. In this case, the pressure on the nozzle wall is nearly equal to the ambient pressure. At a large flow underexpansion degree (P0 = 300 bar) and in low-pressure conditions conditions (Pн =0.1 bar), the flow in the tip is adjacent to the wall. At a large flow underexpansion degree, the pressure in the nozzle increases from the corner point to the tip exit, and the pressure at the tip exit increases with decreasing tip length. The nozzle thrust coefficient decreases with increasing flow underexpansion degree, and it reaches a constant value after the flow becomes adjacent to the tip wall downstream of the corner point where the tip is connected to the nozzle. At high flow underexpansion degrees, the nozzle thrust coefficient is higher for a nozzle with a longer conical part. The calculated results are in good agreement with experimental data on nozzles of this type.
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7

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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8

Semenov, Vasiliy, Igor Ivanov et Igor Kryukov. « Dual bell slot nozzle of a rocket engine ». Perm National Research Polytechnic University Aerospace Engineering Bulletin, no 46 (2016) : 56–72. http://dx.doi.org/10.15593/2224-9982/2016.46.03.

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9

Martelli, Emanuele, Francesco Nasuti et Marcello Onofri. « Numerical Parametric Analysis of Dual-Bell Nozzle Flows ». AIAA Journal 45, no 3 (mars 2007) : 640–50. http://dx.doi.org/10.2514/1.26690.

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10

ISHIHARA, Hidenori, Tomohiro SATO, Masahiro TSUTSUI, Kazuhiko YOKOTA et Motoyuki ITOH. « Transient Flow Characteristics in a Dual Bell Nozzle ». Proceedings of Conference of Tokai Branch 2003.52 (2003) : 17–18. http://dx.doi.org/10.1299/jsmetokai.2003.52.17.

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11

Stark, Ralf, Chloé Génin, Christian Mader, Dietmar Maier, Dirk Schneider et Michael Wohlhüter. « Design of a film cooled dual-bell nozzle ». Acta Astronautica 158 (mai 2019) : 342–50. http://dx.doi.org/10.1016/j.actaastro.2018.05.056.

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12

KBAB, Hakim, Sidali HAIF et Omar ABADA. « Design Process and Flow Field Analysis of a Double Divergent Supersonic Nozzle : Enhancing Efficiency and Performance ». International Conference on Pioneer and Innovative Studies 1 (13 juin 2023) : 328–33. http://dx.doi.org/10.59287/icpis.851.

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The dual bell nozzle concept's primary goal is to increase performance through the idea of selfadaptation for two operating regimes without mechanical activation. The dual bell nozzle type known asthe planar double divergent nozzle (DDN) has a rectangular cross section. In this study we propose anumerical method for the design of the nozzle profile with double planar divergent. The design of the doubledivergent nozzle is carried out in two parts. The first divergent is a contour of a two-dimensional supersonicnozzle with a sharp-edged throat that gives uniform parallel flow at the exit. The method of characteristicapplied to the two-dimensional isentropic flow of an ideal gas was used for the design of a supersonic planarnozzle. The contour of the second divergent (nozzle extension) is a polynomial. This is achieved using thedirect method of characteristics. A numerical analysis of a double divergent nozzle, and a planar nozzlewith the same area ratio and the same length using ANSYS-Fluent software. The analysis's findingsindicated that the double divergent nozzle had a weight decrease of 0.61%. The thrust increase is estimatedat 3.88% in the low-altitude operating mode for the double divergent nozzle.
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13

Kim, Jeong Hoon, et Hwanil Huh. « Transition Characteristics with Design Parameters of Dual Bell Nozzle ». Transactions of the Korean Society of Mechanical Engineers - B 42, no 7 (31 juillet 2018) : 503–11. http://dx.doi.org/10.3795/ksme-b.2018.42.7.503.

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14

Stark, Ralf, Chloé Génin, Dirk Schneider et Christian Fromm. « Ariane 5 Performance Optimization Using Dual-Bell Nozzle Extension ». Journal of Spacecraft and Rockets 53, no 4 (juillet 2016) : 743–50. http://dx.doi.org/10.2514/1.a33363.

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15

Kbab, H., M. Sellam, T. Hamitouche, S. Bergheul et L. Lagab. « Design and performance evaluation of a dual bell nozzle ». Acta Astronautica 130 (janvier 2017) : 52–59. http://dx.doi.org/10.1016/j.actaastro.2016.10.015.

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16

Hasegawa, Keiichi, Akinaga Kumakawa, Kazuo Kusaka, Masahiro Sato, Makoto Tadano, Akira Konno, Hiroshi Aoki, Eijiro Namura et Masahiro Atsumi. « Fundamental Study of Extendible Nozzle and Dual-Bell Nozzle for Reusable Rocket Engine ». SPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 2 (2003) : 25–34. http://dx.doi.org/10.2322/stj.2.25.

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17

PROSHCHANKA, Dzianis, Koichi YONEZAWA, Hiroaki TSUKUDA, Kasumi ARAKI, Tatsuya KIMURA, Kazuhiko YOKOTA et Yoshinobu TSUJIMOTO. « Flow Oscillation in Dual-Bell Nozzle at Low-Altitude Operation ». JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 60, no 1 (2012) : 24–30. http://dx.doi.org/10.2322/jjsass.60.24.

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18

., Balaji Krushna P. « ANALYSIS OF DUAL BELL ROCKET NOZZLE USING COMPUTATIONAL FLUID DYNAMICS ». International Journal of Research in Engineering and Technology 02, no 11 (25 novembre 2013) : 412–17. http://dx.doi.org/10.15623/ijret.2013.0211060.

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19

ISHIHARA, Hedenori, Tomohiro SATO, Masahiro TSUTSUI, Kazuhiko YOKOTA et Motoyuki ITOH. « Transient Flow Characteristics in Two-Dimensional Dual Bell Nozzle Models ». Transactions of the Japan Society of Mechanical Engineers Series B 70, no 692 (2004) : 968–75. http://dx.doi.org/10.1299/kikaib.70.968.

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20

Proschanka, Dzianis, Yonezawa Koichi, Hiroaki Tsukuda, Kasumi Araki, Yoshinobu Tsujimoto, Tatsuya Kimura et Kazuhiko Yokota. « Jet Oscillation at Low-Altitude Operation Mode in Dual-Bell Nozzle ». Journal of Propulsion and Power 28, no 5 (septembre 2012) : 1071–80. http://dx.doi.org/10.2514/1.b34466.

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21

Ferrero, Andrea, Antonietta Conte, Emanuele Martelli, Francesco Nasuti et Dario Pastrone. « Dual-bell nozzle with fluidic control of transition for space launchers ». Acta Astronautica 193 (avril 2022) : 130–37. http://dx.doi.org/10.1016/j.actaastro.2021.12.048.

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22

Wang, Yong, Yuzhen Lin, Qitai Eri et Bo Kong. « Flow and thrust characteristics of an expansion–deflection dual-bell nozzle ». Aerospace Science and Technology 123 (avril 2022) : 107464. http://dx.doi.org/10.1016/j.ast.2022.107464.

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23

Loosen, Simon, Matthias Meinke et Wolfgang Schröder. « Numerical Investigation of Jet-Wake Interaction for a Dual-Bell Nozzle ». Flow, Turbulence and Combustion 104, no 2-3 (3 septembre 2019) : 553–78. http://dx.doi.org/10.1007/s10494-019-00056-6.

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24

Moon, Taeseok, et Hwanil Huh. « Specific Impulse Gain for KSLV-II with Combination of Dual Bell Nozzle and Expansion-Deflection Nozzle ». Journal of the Korean Society of Propulsion Engineers 22, no 1 (1 février 2018) : 16–27. http://dx.doi.org/10.6108/kspe.2018.22.1.016.

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25

Choi, Junsub, et Hwanil Huh. « Technology Review and Development Trends of Dual-Bell Nozzle for Altitude Compensation ». Journal of the Korean Society for Aeronautical & ; Space Sciences 43, no 5 (1 mai 2015) : 456–65. http://dx.doi.org/10.5139/jksas.2015.43.5.456.

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26

Zebbiche, Toufik. « Supersonic Dual Bell Axisymmetric Minimum Length Nozzle Conception for High Propulsion Thrust ». International Journal of Aeronautical and Space Sciences 20, no 3 (29 mars 2019) : 673–87. http://dx.doi.org/10.1007/s42405-019-00164-7.

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27

Kim, Jeonghoon, Junsub Choi et Hwanil Huh. « Preliminary CFD Results of a Dual Bell Nozzle based on the KSLV-II ». Journal of the Korean Society of Propulsion Engineers 20, no 6 (1 décembre 2016) : 18–28. http://dx.doi.org/10.6108/kspe.2016.20.6.018.

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28

Choi, Junsub, et Hwanil Huh. « Numerical Study on Transition Characteristics of Dual Bell Nozzle with Expansion Ratio Fixed ». Journal of the Korean Society of Propulsion Engineers 21, no 3 (1 juin 2017) : 68–75. http://dx.doi.org/10.6108/kspe.2017.21.3.068.

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29

Verma, Mayank, Nitish Arya et Ashoke De. « Investigation of flow characteristics inside a dual bell nozzle with and without film cooling ». Aerospace Science and Technology 99 (avril 2020) : 105741. http://dx.doi.org/10.1016/j.ast.2020.105741.

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30

SATO, Tomohiro, Shinji SHIMIZU, Kazuhiko YOKOTA et Motoyuki ITOH. « Study on Side Loads and Supersonic Jet Characteristics Using Two-Dimensional Dual Bell Nozzle Model ». Proceedings of the Fluids engineering conference 2004 (2004) : 310. http://dx.doi.org/10.1299/jsmefed.2004.310.

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31

Zmijanovic, Vladeta, Luc Leger, Mohamed Sellam et Amer Chpoun. « Assessment of transition regimes in a dual-bell nozzle and possibility of active fluidic control ». Aerospace Science and Technology 82-83 (novembre 2018) : 1–8. http://dx.doi.org/10.1016/j.ast.2018.02.003.

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32

Fu, Jun, Yuan Tang, Wen Hua Yuan, Yi Ma, Wei Chen et Guang Ming Li. « Research on the Angle of Swirl Chamber Diesel Engine with Dual Channel ». Applied Mechanics and Materials 635-637 (septembre 2014) : 598–602. http://dx.doi.org/10.4028/www.scientific.net/amm.635-637.598.

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Swirl chamber diesel engine’s insert piece of channel performance has a great influence on the swirl chamber indoor airflow movement condition. So based on the 175F series bell flat bottom type swirl chamber’s single connection channel improvement, the influence law of swirl chamber indoor air movement during the injection time by the double connection channel angle at the engine rated speed 2600r/min was studied. Simplified boundary conditions to establish its mathematical solution model for the swirl chamber, then the fluid simulation software was used to research the original scheme and double channel with angle of 50 ° and 30 °, 40 °, 60 ° schemes’ swirl chamber indoor air movement. Results show that the angle of 40 ° dual channel form, the loss of the throttle was reduced, and the swirl chamber air velocity increases obviously, the swirl chamber air velocity in injection time up to 125 m/s,which not only increased indoor vortexes energy but also contribute to oil and gas preferably blended, and near the nozzle the temperature lower 20 °C than the original machine, effectively reducing the nozzle heat load.
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Schneider, Dirk, Ralf Stark, Chloé Génin, Michael Oschwald et Konstantin Kostyrkin. « Active Control of Dual-Bell Nozzle Operation Mode Transition by Film Cooling and Mixture Ratio Variation ». Journal of Propulsion and Power 36, no 1 (janvier 2020) : 47–58. http://dx.doi.org/10.2514/1.b37299.

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34

Léger, L., V. Zmijanovic, M. Sellam et A. Chpoun. « Experimental investigation of forced flow regime transition in a dual bell nozzle by secondary fluidic injection ». International Journal of Heat and Fluid Flow 89 (juin 2021) : 108818. http://dx.doi.org/10.1016/j.ijheatfluidflow.2021.108818.

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35

Emelyanov, Vladislav N., Konstantin N. Volkov et Mikhail S. Yakovchuk. « Unsteady flow in dual-bell nozzle with movement of extendible section from initial to working position ». Physical-Chemical Kinetics in Gas Dynamics 19, no 1 (6 mars 2018) : 1–13. http://dx.doi.org/10.33257/phchgd.19.1.729.

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36

YAMASHITA, Yukinori, Koichi YONEZEWA et Yoshinobu TUJIMOTO. « 1310 A Numerical Study of the effects of Dual-Bell Nozzle contour on and Specific Impulse ». Proceedings of Conference of Kansai Branch 2004.79 (2004) : _13–19_—_13–20_. http://dx.doi.org/10.1299/jsmekansai.2004.79._13-19_.

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37

Choudhury, Siba Prasad, Abhilash Suryan, J. C. Pisharady, A. Jayashree et Khalid Rashid. « Parametric study of supersonic film cooling in dual bell nozzle for an experimental air–kerosene engine ». Aerospace Science and Technology 78 (juillet 2018) : 364–76. http://dx.doi.org/10.1016/j.ast.2018.04.038.

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38

SHIMIZU, Shinji, Kazuhiko YOKOTA, Motoyuki ITOH et Shinji TAMANO. « 2508 Flow Characteristics of Two-Dimensional Compressed Dual Bell Nozzle Models during the Startup and Shutdown Transients ». Proceedings of the JSME annual meeting 2006.2 (2006) : 223–24. http://dx.doi.org/10.1299/jsmemecjo.2006.2.0_223.

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39

JITHENDRA, SAI RAJA CHADA, DEEPAK AKELLA SRI RAM, SRINIVAS BASWANTH PAPPULA SASHENDRA et NATHIPAM GANESH. « CONCEPTUAL DESIGN AND STUDY OF FLOW THROUGH A DUAL BELL NOZZLE AT DIFFERENT ALTITUDES USING COMPUTATIONAL FLUID DYNAMICS ». i-manager's Journal on Mechanical Engineering 11, no 3 (2021) : 38. http://dx.doi.org/10.26634/jme.11.3.18057.

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40

Verma, S. B., R. Stark, C. Nuerenberger-Genin et O. Haidn. « Cold-gas experiments to study the flow separation characteristics of a dual-bell nozzle during its transition modes ». Shock Waves 20, no 3 (22 mai 2010) : 191–203. http://dx.doi.org/10.1007/s00193-010-0259-x.

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41

Emelyanov, V. N., K. N. Volkov et M. S. Yakovchuk. « Unsteady Flow in a Dual-Bell Nozzle with Displacement of an Extendible Section from the Initial to Working Position ». Fluid Dynamics 57, S1 (décembre 2022) : S35—S45. http://dx.doi.org/10.1134/s0015462822601267.

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42

Emelyanov, Vladislav, Konstantin Volkov et Mikhail Yakovchuk. « Unsteady flow simulation of compressible turbulent flow in dual-bell nozzle with movement of extendible section from its initial to working position ». Acta Astronautica 194 (mai 2022) : 514–23. http://dx.doi.org/10.1016/j.actaastro.2021.10.007.

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43

Frey, Manuel, et Gerald Hagemann. « Critical Assessment of Dual-Bell Nozzles ». Journal of Propulsion and Power 15, no 1 (janvier 1999) : 137–43. http://dx.doi.org/10.2514/2.5402.

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44

Nürnberger-Genin, Chloe, et Ralf Stark. « Flow transition in dual bell nozzles ». Shock Waves 19, no 3 (20 novembre 2008) : 265–70. http://dx.doi.org/10.1007/s00193-008-0176-4.

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45

Stark, Ralf, et Chloé Génin. « Sea-level transitioning dual bell nozzles ». CEAS Space Journal 9, no 3 (24 mai 2017) : 279–87. http://dx.doi.org/10.1007/s12567-017-0154-8.

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46

Genin, Chloe, et Ralf H. Stark. « Side Loads in Subscale Dual Bell Nozzles ». Journal of Propulsion and Power 27, no 4 (juillet 2011) : 828–37. http://dx.doi.org/10.2514/1.b34170.

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47

Nürnberger-Génin, Chloé, et Ralf Stark. « Experimental Study on Flow Transition in Dual Bell Nozzles ». Journal of Propulsion and Power 26, no 3 (mai 2010) : 497–502. http://dx.doi.org/10.2514/1.47282.

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48

ARAKI, Kasumi, Hiroaki TSUKUDA, Koichi YONEZAWA, Yoshinobu TSUZIMOTO et Tatsuya KIMURA. « 1306 Numerical Investigation of Flow Oscillation in Dual-Bell Nozzles ». Proceedings of Conference of Kansai Branch 2011.86 (2011) : _13–6_. http://dx.doi.org/10.1299/jsmekansai.2011.86._13-6_.

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Génin, Chloé, Andreas Gernoth et Ralf Stark. « Experimental and Numerical Study of Heat Flux in Dual Bell Nozzles ». Journal of Propulsion and Power 29, no 1 (janvier 2013) : 21–26. http://dx.doi.org/10.2514/1.b34479.

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YOKOTA, Kazuhiko, Shinji SHIMIZU, Tomohiro SATO, Shinji TAMANO et Motoyuki ITOH. « Flow Fields and Side Load in Compressed 2D Dual Bell Nozzles ». Transactions of the Japan Society of Mechanical Engineers Series B 73, no 735 (2007) : 2204–12. http://dx.doi.org/10.1299/kikaib.73.2204.

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