Готові списки джерел за темами / Dual-bell nozzle

Добірка наукової літератури з теми "Dual-bell nozzle"

Автор: Grafiati

Опубліковано: 14 березня 2023

Оновлено: 7 липня 2024

Оформте джерело за APA, MLA, Chicago, Harvard та іншими стилями

Оберіть тип джерела:

Зміст

Статті в журналах
Дисертації
Книги
Частини книг
Тези доповідей конференцій

Ознайомтеся зі списками актуальних статей, книг, дисертацій, тез та інших наукових джерел на тему "Dual-bell nozzle".

Біля кожної праці в переліку літератури доступна кнопка «Додати до бібліографії». Скористайтеся нею – і ми автоматично оформимо бібліографічне посилання на обрану працю в потрібному вам стилі цитування: APA, MLA, «Гарвард», «Чикаго», «Ванкувер» тощо.

Також ви можете завантажити повний текст наукової публікації у форматі «.pdf» та прочитати онлайн анотацію до роботи, якщо відповідні параметри наявні в метаданих.

Статті в журналах з теми "Dual-bell nozzle"

Akib, Yeasir Mohammad, Asif Kabir, and Mahdi Hasan. "Characteristics Analysis of Dual Bell Nozzle using Computational Fluid Dynamics." International Journal of Engineering Materials and Manufacture 4, no. 1 (March 1, 2019): 15–21. http://dx.doi.org/10.26776/ijemm.04.01.2019.02.

Повний текст джерела

Анотація:

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.

Стилі APA, Harvard, Vancouver, ISO та ін.

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

Повний текст джерела

Анотація:

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

Стилі APA, Harvard, Vancouver, ISO та ін.

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

Повний текст джерела

Анотація:

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.

Стилі APA, Harvard, Vancouver, ISO та ін.

Samantra, Ashis Kumar, K. S. Santhosh, Khalid Rashid, and 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 (September 12, 2020): 042039. http://dx.doi.org/10.1088/1757-899x/912/4/042039.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

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.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

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

Повний текст джерела

Анотація:

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.

Стилі APA, Harvard, Vancouver, ISO та ін.

Cimini, M., E. Martelli, and M. Bernardini. "Numerical Analysis of Side-loads Reduction in a Sub-scale Dual-bell Rocket Nozzle." Flow, Turbulence and Combustion 107, no. 3 (January 28, 2021): 551–74. http://dx.doi.org/10.1007/s10494-021-00243-4.

Повний текст джерела

Анотація:

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.

Стилі APA, Harvard, Vancouver, ISO та ін.

Semenov, Vasiliy, Igor Ivanov, and 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.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

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

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

ISHIHARA, Hidenori, Tomohiro SATO, Masahiro TSUTSUI, Kazuhiko YOKOTA, and 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.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Більше джерел

Дисертації з теми "Dual-bell nozzle"

Legros, Brian. "Flow control in dual-bell nozzles : optimisation of operating mode transition using radial secondary fluidic injection." Electronic Thesis or Diss., Orléans, 2024. http://www.theses.fr/2024ORLE1008.

Повний текст джерела

Анотація:

Le contrôle du changement de régime dans une tuyère à double galbe est étudié par le biais d'une injection fluidique annulaire radiale positionnée en aval du point d'inflexion, dans le profil d'extension de la tuyère. L'objectif de cette étude est d'améliorer les performances de la tuyère et montrer qu'elle peut être une alternative aux tuyères conventionnelles peu efficientes. L'étude s'appuie sur une approche expérimentale et numérique. Elle comprend une étude paramétrique portant sur l'impact de la présence d'une fente d'injection, la position de cette injection dans l'extension de la tuyère, et l'utilisation d'un gaz secondaire aux propriétés différentes de l'air. L'analyse des résultats révèle la sensibilité de la tuyère à l'état de surface du divergent, où la présence d'une discontinuité modifie le taux de détente (NPR) de changement de régime et diminue les charges latérales. L'injection secondaire démontre la capacité à augmenter significativement les NPR de changement de régime tout en réduisant les charges latérales. L'étude de la position de l'injection confirme le potentiel d'optimisation de la tuyère à double galbe pour améliorer ses performances. Les essais avec un gaz secondaire différent montrent des améliorations plus significatives qu'avec de l'air, levant ainsi les verrous scientifiques associés à cette technologie
The control of the operating mode switch in a dual-bell nozzle is studied through radial annular secondary fluidic injection positioned downstream of the inflexion point in the nozzle's extension profile. The objective of this study is to enhance the performance of the nozzle and demonstrate its potential as an alternative to conventional nozzles with sub-optimal efficiency. The study employs experimental and numerical approaches, including a parametric investigation into the impact of the presence of an injection slot, the position of the injection in the nozzle's extension, and the use of a secondary gas with properties different from air. Analysis of the results reveals the nozzle's sensitivity to the surface condition of the divergent, where the presence of a discontinuity alters the nozzle pressure ratio (NPR) at which the switch in operating mode occurs and reduces lateral loads. Secondary injection demonstrates the ability to significantly increase the NPR at which these changes in operating modes occur while reducing lateral loads.The study of the injection position confirms the optimisation potential of the dual-bell nozzle to enhance its performance. Experiments with a different secondary gas show more significant improvements than with air, thereby overcoming scientific challenges associated with this technology

Стилі APA, Harvard, Vancouver, ISO та ін.

CONTE, ANTONIETTA. "Advanced Concepts for Rocket Engine Applications." Doctoral thesis, Politecnico di Torino, 2022. http://hdl.handle.net/11583/2962963.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Génin, Chloé. "Experimental study of flow behaviour and thermal loads in dual bell nozzles." Valenciennes, 2010. http://ged.univ-valenciennes.fr/nuxeo/site/esupversions/315120cf-ee52-488e-94c9-b4901191c383.

Повний текст джерела

Анотація:

Les besoins toujours croissants de l’industrie aérospatiale imposent l’optimisation de tous les sous systèmes du lanceur. Les tuyères sont actuellement le sous-système présentant les possibilités d’optimisation les plus prometteuses. Les tuyères dual bell permettent une adaptation à l’altitude par une simple inflexion du contour. L’écoulement, est forcé à décoller de façon stable et symétrique à l’inflexion, générant ainsi une poussée optimisée à basse altitude. Au cours du vol, lorsque la pression atmosphérique chute sous une certaine valeur, l’écoulement attache soudainement dans toute la tuyère, permettant une détente plus importante pour une poussée plus élevée. Ce nouveau concept de tuyères demande à être compris en détail avant son application éventuelle au moteur principal d’un lanceur. L’étude présentée dans ce document a été réalisée au DLR (centre aérospatial Allemand) de Lampoldshausen dans le cadre d’un travail de thèse. Il s’agit d’une étude fondamentale visant à comprendre le comportement de l’écoulement dans une tuyère dual bell, afin de mettre en évidence les paramètres d’influence. Une série de tests en gaz froid a été réalisée sur différentes géométries de tuyères. Des mesures de pression et une observation de l’écoulement, à l’aide d’une optique de schlieren a permis de conclure sur l’influence de la géométrie sur la transition et sa stabilité face aux variations de pressions et sur le déroulement de la transition d’un mode de fonctionnement à l’autre. Une série de tests en gaz chaud a permis de réaliser des relevés de températures et pression afin d’étudier les charges thermiques dans la paroi au voisinage de l’inflexion
The increasing needs of the aerospatial industry impose the optimisation of every subsystems of the launcher. Nozzles are currently the sub-system presenting the most promising possibilities. The dual bell nozzles allow the altitude adaptation of the flow through a simple contour inflection. The inflexion forces the flow to a stable and symmetrical separation, generating an optimised thrust for sea level operation. During the flight, when the ambient pressure decreases under a certain value, the flow suddenly attaches the nozzles wall down to the nozzles end, generating a higher expansion for higher performance. Before its possible application to a launcher main engine, this new nozzle concept must be fully understood. The study presented in this document was made at the DLR (German Aerospace Center) in Lampoldshaussen as part of a PhD. This fundamental study has for pbjective the understanding of the flow behaviour in a dual bell nozzle, in order to define the various parameters of influence. A cold flow test series has been conducted on various nozzle geometries. Pessure measurements have been made and the flow has been observed with schlieren optics in order to determine the influence of the geometry on the transition point, the transition duration and its stability toward pressure variations and the evolution of the flow from one operating mode to the other. Temperature and pressure measurements were also made during a test series under warm gas conditions to investigate the thermal load in the vicinity of the wall inflection

Стилі APA, Harvard, Vancouver, ISO та ін.

Bolgar, Istvan [Verfasser], Christian J. [Akademischer Betreuer] Kähler, Christian J. Gutachter] Kähler, and Rolf [Gutachter] [Radespiel. "On the performance increase of future space launchers: Investigations of buffeting, its reduction via passive flow control, and the Dual-Bell nozzle concept at trans- and supersonic flight conditions / Istvan Bolgar ; Gutachter: Christian J. Kähler, Rolf Radespiel ; Akademischer Betreuer: Christian J. Kähler ; Universität der Bundeswehr München, Fakultät für Luft- und Raumfahrttechnik." Neubiberg : Universitätsbibliothek der Universität der Bundeswehr München, 2019. http://nbn-resolving.de/urn:nbn:de:bvb:706-6871.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Bolgar, Istvan [Verfasser], Christian J. [Akademischer Betreuer] Kähler, Christian J. [Gutachter] Kähler, and Rolf [Gutachter] Radespiel. "On the performance increase of future space launchers: Investigations of buffeting, its reduction via passive flow control, and the Dual-Bell nozzle concept at trans- and supersonic flight conditions / Istvan Bolgar ; Gutachter: Christian J. Kähler, Rolf Radespiel ; Akademischer Betreuer: Christian J. Kähler ; Universität der Bundeswehr München, Fakultät für Luft- und Raumfahrttechnik." Neubiberg : Universitätsbibliothek der Universität der Bundeswehr München, 2019. http://d-nb.info/1222682982/34.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Génin, Chloé [Verfasser]. "Experimental Study of Flow Behaviour and Thermal Loads in Dual Bell Nozzles / Chloé Génin." Aachen : Shaker, 2010. http://d-nb.info/1101184302/34.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Francis, Abel Christena. "Numerical Simulation of Dual Bell Nozzle for Rocket Engines." Thesis, 2017. http://ethesis.nitrkl.ac.in/9055/1/2017_MT_ACFrancis.pdf.

Повний текст джерела

Анотація:

Owing to the improved performance, several nozzle concepts have been introduced, that promises a gain in performance when compared with the conventional nozzles. As nozzle plays an important role in the improvement of the rocket engine, many have developed technologies for better operational and reliable nozzles. Altitude adapting nozzles are the most advanced technology in this field. And among them Dual Bell Nozzles have gained reasonable popularity in these days. It is shown that they gain a significant performance gain which is the result of their adaptation to the ambient pressure. Current research results presented for dual bell nozzles are mainly for understanding the flow behavior and optimizing the geometrical parameters for maximum flight performance for a range of altitude by its adaptive characteristics. In general, these altitude adapting nozzles induces less shock waves and expansion waves. Flow phenomena observed in present day experiments and numerical simulations work during different nozzle operational conditions are very much highlighted, and gained attention. Many researchers have presented the occurrence of lateral side loads but failed to explain their detailed flow mechanisms. Also, the key parameters governing fluctuations remain unknown. By its peculiar geometry with a inflection between the two nozzle, this nozzle can control flow separation corresponding to a range of Pressure Ratio. As the capturing of the flow and transition from one bell to another during startup and shutdown in Dual Bell Nozzle is not studied much, motivation for the present work is to get an understanding of the flow behaviour in Dual Bell Nozzle with highlight given to its separation phenomenon at different Pressure Ratio and holding of flow at the transition point. Being an altitude adaptive nozzle, flow separation and side loads being a major concern of such nozzle, in this way, the study can contribute to its better understanding. The comparison with the existing High Altitude nozzles will help to get the improvements obtained. Also another area which is less studied is cooling of dual bell nozzle. Cooling of Dual Bell Nozzle like any other nozzle is important for its improved performance and specific impulse. Hence all these study of flow analysis, holding at transition and cooling in Dual Bell Nozzle will cumulatively help to implement such new concepts in future launching vehicles especially for SSTO (single stage to orbit) launchers and maximizing payloads in the future launch vehicles.

Стилі APA, Harvard, Vancouver, ISO та ін.

Книги з теми "Dual-bell nozzle"

National Aeronautics and Space Administration (NASA) Staff. Proposed Flight Research of a Dual-Bell Rocket Nozzle Using the NASA F-15 Airplane. Independently Published, 2019.

Знайти повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

National Aeronautics and Space Administration NASA. Conceptual Design for a Dual-Bell Rocket Nozzle System Using a NASA F-15 Airplane as the Flight Testbed. Independently published, 2019.

Знайти повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Частини книг з теми "Dual-bell nozzle"

Génin, Chloé, Dirk Schneider, and Ralf Stark. "Dual-Bell Nozzle Design." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 395–406. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_25.

Повний текст джерела

Анотація:

Abstract The dual-bell nozzle is an altitude adaptive nozzle concept that offers two operation modes. In the framework of the German Research Foundation Special Research Field SFB TRR40, the last twelve years have been dedicated to study the dual-bell nozzle characteristics, both experimentally and numerically. The obtained understanding on nozzle contour and inflection design, transition behavior and transition prediction enabled various follow-ups like a wind tunnel study on the dual-bell wake flow, a shock generator study on a film cooled wall inflection or, in higher scale, the hot firing test of a thrust chamber featuring a film cooled dual-bell nozzle. A parametrical system study revealed the influence of the nozzle geometry on the flow behavior and the resulting launcher performance increase.

Стилі APA, Harvard, Vancouver, ISO та ін.

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, 115–27. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_7.

Повний текст джерела

Анотація:

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.

Стилі APA, Harvard, Vancouver, ISO та ін.

Barklage, Alexander, and Rolf Radespiel. "Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 129–43. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_8.

Повний текст джерела

Анотація:

Abstract This work investigates the interaction of the afterbody flow with the propulsive jet flow on a generic space launcher equipped with two alternative nozzle concepts and different afterbody geometries. The flow phenomena are characterized by experimental measurements and numerical URANS and LES simulations. Investigations concern a configuration with a conventional truncated ideal contour nozzle and a configuration with an unconventional dual-bell nozzle. In order to attenuate the dynamic loads on the nozzle fairing, passive flow control devices at the base of the launcher main body are investigated on the configuration with TIC nozzle. The nozzle Reynolds number and the afterbody geometry are varied for the configuration with dual-bell nozzle. The results for integrated nozzles show a shift of the nozzle pressure ratio for transition from sea-level to altitude mode to significant lower levels. The afterbody geometry is varied including a reattaching and non-reattaching outer flow on the nozzle fairing. Investigations are performed at supersonic outer flow conditions with a Mach number of $$Ma_\infty =3$$. It turns out, that a reattachment of the outer flow on the nozzle fairing leads to an unstable nozzle operation.

Стилі APA, Harvard, Vancouver, ISO та ін.

Ludescher, Sandra, and Herbert Olivier. "Film Cooling in Rocket Nozzles." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 65–78. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_4.

Повний текст джерела

Анотація:

Abstract In this project supersonic, tangential film cooling in the expansion part of a nozzle with rocket-engine like hot gas conditions was investigated. Therefore, a parametric study in a conical nozzle was conducted revealing the most important influencing parameter on film cooling for the presented setup. Additionally, a new axisymmetric film cooling model and a method for calculating the cooling efficiency from experimental data was developed. These models lead to a satisfying correlation of the data. Furthermore, film cooling in a dual-bell nozzle performing in altitude mode was investigated. The aim of these experiments was to show the influence of different contour inflection geometries on the film cooling efficiency in the bell extension.

Стилі APA, Harvard, Vancouver, ISO та ін.

Verma, Mayank, and Ashoke De. "Film Cooling Aspects of a Dual Bell Nozzle." In Lecture Notes in Mechanical Engineering, 99–107. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-5183-3_11.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Loosen, Simon, Matthias Meinke, and Wolfgang Schröder. "Numerical Analysis of the Turbulent Wake for a Generic Space Launcher with a Dual-Bell Nozzle." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 163–77. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_10.

Повний текст джерела

Анотація:

Abstract The turbulent wake of an axisymmetric generic space launcher equipped with a dual-bell nozzle is simulated at transonic ($$Ma_\infty = 0.8$$ and $$Re_D = 4.3\cdot 10^5$$) and supersonic ($$Ma_\infty = 3$$ and $$Re_D = 1.2\cdot 10^6$$) freestream conditions, to investigate the influence of the dual-bell nozzle jet onto the wake flow and vice versa. In addition, flow control by means of four in circumferential direction equally distributed jets injecting air encountering the backflow in the recirculation region is utilized to determine if the coherence of the wake and consequently, the buffet loads can be reduced by flow control. The simulations are performed using a zonal RANS/LES approach. The time-resolved flow field data are analyzed by classical spectral analysis, two-point correlation analysis, and dynamic mode decomposition (DMD). At supersonic freestream conditions, the nozzle counter pressure is reduced by the expansion of the outer flow around the nozzle lip leading to a decreased transition nozzle pressure ratio. In the transonic configuration a spatio-temporal mode with an eigenvalue matching the characteristic buffet frequency of $$Sr_D=0.2$$ is extracted by the spectral and DMD analysis. The spatial shape of the detected mode describes an antisymmetric wave-like undulating motion of the shear layer inducing the low frequency dynamic buffet loads. By flow control this antisymmetric coherent motion is weakened leading to a reduction of the buffet loads on the nozzle fairing.

Стилі APA, Harvard, Vancouver, ISO та ін.

Haidn, Oskar J., Nikolaus A. Adams, Rolf Radespiel, Thomas Sattelmayer, Wolfgang Schröder, Christian Stemmer, and Bernhard Weigand. "Collaborative Research for Future Space Transportation Systems." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 1–30. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_1.

Повний текст джерела

Анотація:

Abstract This chapter book summarizes the major achievements of the five topical focus areas, Structural Cooling, Aft-Body Flows, Combustion Chamber, Thrust Nozzle, and Thrust-Chamber Assembly of the Collaborative Research Center (Sonderforschungsbereich) Transregio 40. Obviously, only sample highlights of each of the more than twenty individual projects can be given here and thus the interested reader is invited to read their reports which again are only a summary of the entire achievements and much more information can be found in the referenced publications. The structural cooling focus area included results from experimental as well as numerical research on transpiration cooling of thrust chamber structures as well as film cooling supersonic nozzles. The topics of the aft-body flow group reached from studies of classical flow separation to interaction of rocket plumes with nozzle structures for sub-, trans-, and supersonic conditions both experimentally and numerically. Combustion instabilities, boundary layer heat transfer, injection, mixing and combustion under real gas conditions and in particular the investigation of the impact of trans-critical conditions on propellant jet disintegration and the behavior under trans-critical conditions were the subjects dealt with in the combustion chamber focus area. The thrust nozzle group worked on thermal barrier coatings and life prediction methods, investigated cooling channel flows and paid special attention to the clarification and description of fluid-structure-interaction phenomena I nozzle flows. The main emphasis of the focal area thrust-chamber assembly was combustion and heat transfer investigated in various model combustors, on dual-bell nozzle phenomena and on the definition and design of three demonstrations for which the individual projects have contributed according to their research field.

Стилі APA, Harvard, Vancouver, ISO та ін.

Raju, Martin, V. V. Ijas Muhammed, Abhilash Suryan, and Heuy Dong Kim. "Computational Study on the Flow Characteristics in a Film Cooled Dual-Bell Nozzle." In Lecture Notes in Mechanical Engineering, 225–32. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-5183-3_24.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Bolgar, Istvan, Sven Scharnowski, and Christian J. Kähler. "Experimental Analysis of the Interaction Between a Dual-Bell Nozzle with an External Flow Field Aft of a Backward-Facing Step." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 405–15. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-25253-3_39.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Тези доповідей конференцій з теми "Dual-bell nozzle"

Otsu, Hirotaka, Masafumi Miyazawa, and Yasunori Nagata. "Design Criterion of the Dual-Bell Nozzle Contour." In 56th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.iac-05-c4.2.08.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Genin, Chloe, Ralf Stark, Sebastian Karl, and Dirk Schneider. "Numerical Investigation of Dual Bell Nozzle Flow Field." In 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4164.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Toufik, Hamitouche, Sellam Mohamed, Kbab Hakim, Bergheul Said, and Lagab Lynda. "Design and performances of the dual-bell nozzle." In 2016 IEEE Aerospace Conference. IEEE, 2016. http://dx.doi.org/10.1109/aero.2016.7500518.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Davis, Kate, Elizabeth Fortner, Michael Heard, Hannah McCallum, and Hunter Putzke. "Experimental and Computational Investigation of a Dual-Bell Nozzle." In 53rd AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-0377.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Ferrero, Andrea, Emanuele Martelli, Francesco Nasuti, and Dario Pastrone. "Fluidic Control of Transition in a Dual-bell Nozzle." In AIAA Propulsion and Energy 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3788.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Génin, C., R. Stark, O. Haidn, K. Quering, and M. Frey. "Experimental and numerical study of dual bell nozzle flow." In Progress in Flight Physics, edited by P. Reijasse, D. Knight, M. Ivanov, and I. Lipatov. Les Ulis, France: EDP Sciences, 2013. http://dx.doi.org/10.1051/eucass/201305363.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Martelli, Emanuele, Francesco Nasuti, and Marcello Onofri. "Film Cooling Effect on Dual-Bell Nozzle Flow Transition." In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-4953.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Stark, Ralf, and Chloé Génin. "Hot Flow Testing of a Film Cooled Dual Bell Nozzle." In 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-5614.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Ferrero, Andrea, Antonietta Conte, Emanuele Martelli, Francesco Nasuti, and Dario Pastrone. "Dual-bell nozzle for space launchers with fluidic control of transition." In AIAA Propulsion and Energy 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-3586.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Barklage, Alexander, Rolf Radespiel, and Chloe Genin. "Afterbody jet interaction of a dual-bell nozzle in supersonic flow." In 2018 Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4468.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Ми пропонуємо знижки на всі преміум-плани для авторів, чиї праці увійшли до тематичних добірок літератури. Зв'яжіться з нами, щоб отримати унікальний промокод!