Готові списки джерел за темами / Underexpanded flow

Добірка наукової літератури з теми "Underexpanded flow"

Автор: Grafiati
Опубліковано: 14 березня 2023

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Статті в журналах з теми "Underexpanded flow"

1

Lee, K.-H., T. Setoguchi, S. Matsuo, and H.-D. Kim. "An experimental study of underexpanded sonic, coaxial, swirl jets." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 218, no. 1 (January 1, 2004): 93–103. http://dx.doi.org/10.1243/095440604322786974.

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The present study addresses experimental investigations of the near-field flow structures of an underexpanded sonic, dual, coaxial, swirl jet. The swirl stream is discharged from the secondary annular nozzle and the primary inner nozzle provides the underexpanded free jets. The interactions between the secondary swirl and primary underexpanded jets are quantified by a fine pitot impact and static pressure measurements and are visualized using a shadowgraph optical method. The pressure ratios of the secondary swirl and primary underexpanded jets are varied below 7.0. Experiments are conducted to investigate the effects of the secondary swirl stream on the primary underexpanded jets, compared with the secondary stream of no swirl. The results show that the presence of an annular swirl stream causes the Mach disc to move further downstream, with an increased diameter, and remarkably reduces the fluctuations of the impact pressures in the underexpanded sonic dual coaxial jet, compared with the case of the secondary annular stream with no swirl.
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2

Srinivasarao, T., P. Lovaraju, and E. Rathakrishnan. "Characteristics of Underexpanded Co-Flow Jets." Applied Mechanics and Materials 575 (June 2014): 507–11. http://dx.doi.org/10.4028/www.scientific.net/amm.575.507.

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Анотація:
The effect of inner nozzle lip thickness on the co-flow jet characteristics has been studied experimentally. Co-flow nozzles with inner nozzle lip thicknesses of 3 mm and 15 mm have been investigated. The thick-lip nozzle promotes mixing better than the thin-lip nozzle, for all the underexpanded operating conditions. The co-flow nozzle with thin-lip is effective in preserving the shock-cells nature, bringing down the longer shock-cell into shorter one and increasing the number of shock-cells compared to that of the co-flow nozzle with thick-lip.
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3

Cumber, P. S., M. Fairweather, S. A. E. G. Falle, and J. R. Giddings. "Predictions of the Structure of Turbulent, Highly Underexpanded Jets." Journal of Fluids Engineering 117, no. 4 (December 1, 1995): 599–604. http://dx.doi.org/10.1115/1.2817309.

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A mathematical model capable of predicting the shock and flow structure of turbulent, underexpanded jets is described. The model is based on solutions of the fluid flow equations obtained using a second-order accurate, finite-volume integration scheme together with an adaptive grid algorithm. Closure of these equations is achieved using a k-ε turbulence model coupled to the compressible dissipation rate correction proposed by Sarkar et al. (1991a). Extending earlier work which demonstrated the ability of this model to predict the structure of moderately underexpanded jets, the present paper compares model predictions and experimental data, reported in the literature, on a number of highly underexpanded releases. The results obtained demonstrate that the model yields reliable predictions of shock structure in the near field, inviscid region of such jets, while in the far field results derived using the compressibility corrected turbulence model are adequate for predicting mean flow properties, and are superior to those obtained using a standard k-ε approach.
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4

MATSUSHITA, Shinichi, Chungpyo HONG, Yutaka ASAKO, and Ichiro UENO. "G222 Underexpanded flow in a micro-tube." Proceedings of the Thermal Engineering Conference 2011 (2011): 355–56. http://dx.doi.org/10.1299/jsmeted.2011.355.

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5

Zaitsev, E. G. "Underexpanded wall jet in a cocurrent flow." Fluid Dynamics 28, no. 1 (1993): 149–52. http://dx.doi.org/10.1007/bf01055679.

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6

Yaga, Minoru, Yoshio Kinjo, Masumi Tamashiro, and Kenyu Oyakawa. "Flow characteristics of rectangular underexpanded impinging jets." Journal of Thermal Science 15, no. 1 (March 2006): 59–64. http://dx.doi.org/10.1007/s11630-006-0059-x.

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7

Sakakibara, Y., and J. Iwamoto. "Numerical Study of Oscillation Mechanism in Underexpanded Jet Impinging on Plate." Journal of Fluids Engineering 120, no. 3 (September 1, 1998): 477–81. http://dx.doi.org/10.1115/1.2820687.

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Анотація:
The mechanism of the oscillatory phenomena of an underexpanded jet impinging on a flat plate is studied numerically. Pressure changes generated in the flow field near the plate propagate radially in the surrounding region of the jet. The configuration of the jet boundary is changed by them and so, the waves forming the underexpanded jet are displaced when they are reflected from the jet boundary. And then, the pressure disturbances return to the region near the plate. Unsteady flow with repetition of growth and decay of the separation bubble on the plate is also found under certain conditions.
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8

Gubanov, Dmitriy, Valeriy Zapryagaev, and Nikolay Kiselev. "Flow Stucture of Supersonic Underexpanded Jet With Microjets Injection." Siberian Journal of Physics 8, no. 1 (March 1, 2013): 44–55. http://dx.doi.org/10.54362/1818-7919-2013-8-1-44-55.

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Experimental and numerical study of transversal microjets injection influence on the supersonic underexpanded jet flow structure has been performed. Data of measurements and calculation have acceptable agreement. Interaction of microjets with main supersonic jet sets to a decrease of an initial gasdynamic region. Microjets lead to a longitudinal streamwise vortices generation and a mushroom-like flow structures create on an external jet mixing layer. Dissipation of longitudinal streamwise vortices was observed at the second jet cell. Complex gasdynamic flow structure of the supersonic underexpanded jet interacting with supersonic microjets has been studied for the first time. This structure contains system of complex chock waves and expansion waves spreading from the position of the impact microjets/main jet localization place. Future of interaction process a chock-wave structure of main jet with additional shock waves has been studied
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9

Sakakibara, Yoko, Masaki Endo, and Junjiro Iwamoto. "On Flow Field of Radially Emitted Underexpanded Jet." International Journal of Aeroacoustics 12, no. 5-6 (October 2013): 423–35. http://dx.doi.org/10.1260/1475-472x.12.5-6.423.

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10

Arun Kumar, R., and G. Rajesh. "Shock transformation and hysteresis in underexpanded confined jets." Journal of Fluid Mechanics 823 (June 21, 2017): 538–61. http://dx.doi.org/10.1017/jfm.2017.231.

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Анотація:
This study investigates the shock transformation in an underexpanded jet in a confined duct when the jet total pressure is increased. Experimental study reveals that the Mach reflection (MR) in the fully underexpanded jet transforms to a regular reflection (RR) at a certain jet total pressure. It is observed that neither the incident shock angle nor the upstream Mach number varies during the MR–RR shock transformation. This is in contradiction to the classical MR–RR transformations in internal flow over wedges and in underexpanded open jets. This transformation is found to be a total pressure variation induced transformation, which is a new kind of shock transformation. The present study also reveals that the critical jet total pressures for MR–RR and RR–MR transformations are not the same when the primary pressure is increasing and decreasing, suggesting a hysteresis in the shock transformations.
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Більше джерел

Дисертації з теми "Underexpanded flow"

1

Garcia, Robert Gordon. "CFD simulation of flow fields associated with high speed jet impingement on deflectors." Thesis, Virginia Tech, 2007. http://hdl.handle.net/10919/31675.

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Computational Fluid Dynamics is used to analyze the formation of under-expanded jets and to investigate the three-dimensional flow field associated with the impingement of free jets onto stationary deflectors. This investigation was performed to develop a verified modeling ability for such problems. Predictions were compared with the experimental results obtained by Donaldson and Snedeker [1]. Computational models for free and impinging jets were created according to the data provided in Ref. 1. Numerical results for each of the experiments performed in this benchmark report are presented.

Three different turbulent free jets produced by a simple convergent nozzle were analyzed. These include a subsonic jet with p1/pâ =1 and M1=0.57, a moderately under-expanded jet with p1/pâ =1.42 and M1=1, and a highly under-expanded jet with p1/pâ =3.57 and M1=1. The reflecting shocks associated with the moderately under-expanded jet as well as the shock disk associated with the highly under-expanded jet were fully resolved. Velocity profile data predicted at locations downstream of the nozzle exit agreed very well with the experimental results.

The impingement of a moderately under-expanded jet with p1/pâ =1.42 and M1=1 was also investigated. The interaction of the high speed jet with circular flat plates at angles of 60° and 45° relative to the center axis of the jet are presented. Wall jet velocity profiles on the surface of the flat plate are fully resolved and compare well with experimental results. The CFD solver controls and method used to obtain these results are summarized and justified.
Master of Science

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2

Massman, Jeffrey. "NUMERICAL FLOW FIELD ANALYSIS OF AN AIR AUGMENTED ROCKET USING THE AXISYMMETRIC METHOD OF CHARACTERISTICS." DigitalCommons@CalPoly, 2013. https://digitalcommons.calpoly.edu/theses/1141.

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Анотація:
An Axisymmetric Rocket Ejector Simulation (ARES) was developed to numerically analyze various configurations of an air augmented rocket. Primary and secondary flow field visualizations are presented and performance predictions are tabulated. A parametric study on ejector geometry is obtained following a validation of the flow fields and performance values. The primary flow is calculated using a quasi-2D, irrotational Method of Characteristics and the secondary flow is found using isentropic relations. Primary calculations begin at the throat and extend through the nozzle to the location of the first Mach Disk. Combustion properties are tabulated before analysis to allow for propellant property selection. Secondary flow calculations employ the previously calculated plume boundary and ejector geometry to form an isentropic solution. Primary and secondary flow computations are iterated along the new pressure distributions established by the 1D analysis until a convergence tolerance is met. Thrust augmentation and Specific Impulse values are predicted using a control volume approach. For the validation test cases, the nozzle characteristic net is very similar to that of previous research. Plume characteristics are in good agreement but fluctuate in accuracy due to flow structure formulation. The individual unit processes utilized by the Method of Characteristics are found to vary their outputs by up to 0.025% when compared to existing sources. Rocket thrust and specific impulse are increased by up to 22% for a static system and 15% for an ejector flow at Mach 0.5. Evidence of Fabri conditions were observed in the flow visualization and graphically through the performance predictions. It was determined that the optimum ejector divergence angle for an air augmented rocket greatly depends on the stagnation pressure ratio between the primary and secondary flows.
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3

Goparaju, Kalyan. "Flow and Acoustic Characteristics of Complex Supersonic Jets." The Ohio State University, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=osu1510933315034965.

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4

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

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5

Si-Ameur, Mohamed. "Simulations numériques de mélanges turbulents dans les écoulements cisaillés supersoniques." Université Joseph Fourier (Grenoble ; 1971-2015), 1994. http://www.theses.fr/1994GRE10214.

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Анотація:
L'etude du melange turbulent dans des ecoulements cisailles supersoniques, couche de melange confinee entre parois et jet faiblement sous detendu, est abordee a l'aide de simulations numeriques tridimensionnelles instationnaires. Un code aux volumes finis est utilise dans cette optique. La technique de simulation des grandes echelles a ete utilisee, les effets sous-maille etant pris en compte par les proprietes de l'algorithme numerique ppm qui filtre les concentrations de vorticite a petite echelle. Cette technique nous a permis de considerer certains caracteres des ecoulements reels: prise en compte des parois, simulation explicite du developpement spatial, resolution a des echelles de l'ordre de la taille des dispositifs reels. Les effets de parois sont etudies en approximation bidimensionnelle et en situation reelle tridimensionnelle. Les resultats montrent que les calculs bidimensionnels sont peu realistes pour representer le caractere tridimensionnel de l'ecoulement. Les zones de melange sont analysees qualitativement et quantitativement. La formation de sous-couches au niveau de la zone de melange est evidente pour m#c 0. 6. Une schematisation d'un modele de melange dans une couche de melange compressible est proposee
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6

Menon, Nandkishore. "Analysis of non-axisymmetric underexpanded jet flow fields." Thesis, 2010. http://hdl.handle.net/10539/8629.

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A study has been performed that involved the experimental testing and numerical analysis of the underexpanded free jet °ows issuing from rectangular, elliptical and slot nozzles. Aspect ratios of 1, 1.5, 2, 3 and 4 were tested at pressure ratios (exit plane pressure to ambient pressure) of 2 and 3 for rectangular nozzles. In the case of the slot and the elliptical nozzles the aspect ratios of 1.5, 2, 3 and 4 were tested at the same pressure ratios. There is reasonable qualitative agreement between the experimental observations and the numerical predictions. In the case of rectangular jets, a complex system of shock waves forming the incident shock system was discovered. This shock wave system originated at the corners of the nozzle exits, and proceeded to propagate downstream. Mach re°ections have been discovered on the incident shock wave surface of the underexpanded jet from rectangular nozzles. The incident shock system has also been observed to undergo a Mach re°ection in the direction of the jet °ow. The resulting Mach disk has had a cross-sectional shape of a square, a hexagon and octagon in some of the °ow ¯elds from the nozzles that were tested. For slot and elliptical jets the formation of the incident shock wave was not observed along the minor axis plane of the nozzle for aspect ratios > 2. The incident shock wave was observed to originate downstream of the nozzle exit in the major axis plane. In cross-sectional slices it has been established that the incident shock wave undergoes a transition to Mach re°ection as it propagates downstream of the nozzle exit. In all cases tested, the shape of the jet boundary has been signi¯cantly distorted. In rectangular jets the narrowing of the jet boundary along the diagonal axis of the nozzle exit has been observed, and in the case of the elliptical and slot jets axis switching has been observed on the cross-sectional shape of the jet boundary.
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7

Roshanzamir, Alireza. "Experimental studies on flow and noise generated from single and twin supersonic underexpanded jets." Thesis, 1994. http://spectrum.library.concordia.ca/3221/1/MM97632.pdf.

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Optical and acoustical data were obtained for a wide range of jet pressure ratios. Small rectangular tabs placed at the exit plane of a single, and three twin chocked tube models reduced screech tone amplitude to below sonic fatigue level.
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8

Wang, Chang-Nan, and 王昌楠. "Experimental Study on the Shock Oscillating in an Underexpanded Jet to Cavity Interaction Flow." Thesis, 1997. http://ndltd.ncl.edu.tw/handle/94226655554655524878.

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Анотація:
碩士
國立成功大學
航空太空工程學系
85
Underexpansion jet to cavity flow induced pressure oscillation inside the cavity tube and the induced temperature increasing on the bottom of the tube has been investigated based on three parameters of nozzle pressure ratio, nozzle exit to cavity distance and the cavity tube length. Two major flow modes named as regurgitant mode and screeching mode were observed. The measured major frequency on the pressure oscillation inside cavity tube is very closed to the theoretical fundamental frequency of the flow system or its multiplier. Instead of a solid cavity tube end, as replacing it with a sponge-end or a open-end, it has been observed that the amplitude of the pressure oscillating reduced to a negligible level, however, the major frequency remains on the same characteristics. It is concluded that the major mechanism for the pressure oscillating inside cavity tube is owing to the pressure wave reflection between the solid end surface and the inlet surface of the cavity tube. On some regurgitant modes the amplitude of the pressure oscillation can be as high as 70 psia, with a frequency closed to the fundamental frequency. Due to the accumulation of the entropy on the cavity tube end on the pressure oscillation processes in regurgitant mode, an obviously temperature rising has been measured on the end of the cavity tube.
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9

Wang, Chi-Yu, and 王啟宇. "Flow-field Simulation of Multiple Underexpanded Supersonic Jets Using The Parallel Direct Simulation Monte Carlo Method." Thesis, 2002. http://ndltd.ncl.edu.tw/handle/81569250202704300356.

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Анотація:
碩士
國立交通大學
機械工程系
90
Flow fields of multiple underexpanded supersonic jets are simulated using the three-dimensional, parallel direct simulation Monte Carlo (DSMC) method employing an unstructured mesh incorporating static domain decomposition. One, two, three and four jets of argon gas issuing from the orifice(s) into a lower-pressure environment are considered, respectively. Inflow conditions at the orifice outlet (throat) required for the DSMC computation are calculated using the continuum approach. Ratio of upstream stagnation pressure to downstream chamber pressure remains fixed at 50 in the current study. Rarefaction parameter characterized by Knudsen numbers (based on throat conditions) is varied in the range of 0.001~0.1, which corresponds to the flow from near-continuum to transitional regimes. Results show that a distinct barrel shock and Mach disk structure is clearly captured for a single jet flow at Knudsen number of 0.001, while it is diminished to a purely compressible, expanding flow with increasing Knudsen number. Interaction between multiple jets is discussed in detail. Strong thermal non-equilibrium in translational degree of freedoms appears for both high and low Knudsen-number flows due to different reasons.
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Частини книг з теми "Underexpanded flow"

1

Panov, B. F. "Tangential Stress on a Cylinder Surface Impinged by a Underexpanded Low Density Jet." In Separated Flows and Jets, 855–58. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-84447-8_106.

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2

Riabov, V. V., and A. I. Fedoseyev. "The Analysis of Underexpanded Jet Flows for Hypersonic Aerodynamic Experiments in Vacuum Chambers." In 29th International Symposium on Shock Waves 2, 1561–66. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-16838-8_124.

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Тези доповідей конференцій з теми "Underexpanded flow"

1

CORNELIUS, KENNETH, and GERALD LUCIUS. "Thrust vectoring control from underexpanded asymmetric nozzles." In 3rd Shear Flow Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3261.

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2

Feng, Tong, and James McGuirk. "LDA Measurements of Underexpanded Jet Flows from Axisymmetric Nozzle with Solid Tabs." In 3rd AIAA Flow Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-3702.

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3

Al-Rashdan, Hussein. "Supersonic Underexpanded Flow Visualization in Sub-Atmospheric Facility." In AIAA AVIATION 2021 FORUM. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-2859.

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4

Bannink, W., E. Houtman, and P. Bakker. "Base flow/underexpanded exhaust plume interaction in a supersonic external flow." In 8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-1598.

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5

Callender, B., and E. Gutmark. "Reduction of underexpanded jet noise by flow/filament interaction." In 38th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-82.

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6

Quesada, Jose Hermida, Jose A. Morinigo, and Francisco Caballero Requena. "Underexpanded Micro-nozzle Flow Simulation with Coupled Thermal-Fluid Modeling." In 2007 International Conference on Thermal, Mechanical and Multi-Physics Simulation Experiments in Microelectronics and Micro-Systems. EuroSime 2007. IEEE, 2007. http://dx.doi.org/10.1109/esime.2007.360025.

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7

Zapryagaev, V. I., I. N. Kavun, and N. P. Kiselev. "GASDYNAMIC FLOW STRUCTURE AT INITIAL REGION OF SUPERSONIC UNDEREXPANDED JET." In INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH. Novosibirsk: Издательство Сибирского отделения РАН, 2022. http://dx.doi.org/10.53954/9785604788974_179.

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8

Uchida, Mitsunori, Satoshi Someya, Koji Okamoto, and Hiroyuki Ohshima. "Preliminary Experiments With an Underexpanded Gas Jet Into Water." In ASME 2009 Heat Transfer Summer Conference collocated with the InterPACK09 and 3rd Energy Sustainability Conferences. ASMEDC, 2009. http://dx.doi.org/10.1115/ht2009-88417.

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Анотація:
When a heat exchanger in a Fast Breeder Reactor cracks, highly pressurized water or steam escapes into the surrounding liquid sodium. A sodium-water reaction then occurs, forming disodium oxide (and hydrogen gas). It can cause secondary damages to the heat exchangers by the reaction heat and erosion corrosion. The released flow of steam from the cracks of the heat exchanger is an underexpanded jet because the ambient pressure outside the tubes is lower than the critical pressure. When the pressure of a jet released at high pressure cannot be reduced to the low pressure of the ambient fluid, the flow is said to be underexpanded. Because this expansion causes a reduction of pressure and the pressure is lower than the critical pressure, the velocity of the flow can reach supersonic speed. Several studies have examined the underexpansion of the gas-gas phase. However, there have been few studies on the underexpansion of gas-liquid two-phase flows. The flow characteristics of the gas-liquid two-phase flow differ from the gas-gas flow because breakups of the bubbles appear in the gas-liquid two-phase flow. Therefore, in this study qualitative measurement was carried out for the purpose of revealing the flow with the underexpanded gas jet injected into water. The gas jet distance L and the expansion angle θ were then obtained from averaged image of a high-speed camera. L and θ increased approximately linearly with increasing pressure. The entrainment velocity and the velocity of entrained water droplets into the gas jet were obtained by PIV. Images of unstable expansion near the jet nozzle were captured for the first time.
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9

Liu, Junhui, Andrew T. Corrigan, Kailas Kailasanath, Nicholas S. Heeb, and Ephraim J. Gutmark. "Numerical Study of Noise Sources Characteristics in An Underexpanded Jet Flow." In 20th AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2604.

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10

Andre, Benoit, Thomas Castelain, and Christophe Bailly. "INVESTIGATION OF THE MIXING LAYER IN A SLIGHTLY UNDEREXPANDED SUPERSONIC JET BY PARTICLE IMAGE VELOCIMETRY." In Eighth International Symposium on Turbulence and Shear Flow Phenomena. Connecticut: Begellhouse, 2013. http://dx.doi.org/10.1615/tsfp8.280.

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