Relevant bibliographies by topics / Supersonic diffuser

Academic literature on the topic 'Supersonic diffuser'

Author: Grafiati
Published: 10 December 2022
Last updated: 29 January 2023

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Journal articles on the topic "Supersonic diffuser"

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Wen, Chuang, Xue Wen Cao, Bin Yan, and Jing Zhang. "Optimization Design of Diffusers for Supersonic Separators." Applied Mechanics and Materials 44-47 (December 2010): 1913–17. http://dx.doi.org/10.4028/www.scientific.net/amm.44-47.1913.

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The diffuser is the key part of a supersonic separator, which is a new device for natural gas separation. In this paper, three diffusers are designed for the supersonic separator. The fluid flow in the diffuser is numerical calculated, using the RNG k- turbulence model. The behavior of gas dynamic parameters is analyzed under conditions of shock waves and boundary layers. The numerical results show that the second throat diffuser is a good choice for the supersonic separator, both from the perspective of the pressure recovery and adjustment to the back-pressure changes.
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Li, Qingkuo, Zhigang Sun, Xingen Lu, Yingjie Zhang, and Ge Han. "Investigation of New Design Principles for the Centrifugal Compressor Vaned Diffusers." International Journal of Aerospace Engineering 2022 (February 25, 2022): 1–16. http://dx.doi.org/10.1155/2022/4480676.

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Diffuser’s aerodynamic performance is crucial for the centrifugal compressors, while at present the universal principles for the optimization design of the vaned diffusers are still not available. In this paper, three vaned diffusers with different inlet Mach numbers were numerically studied in order to explore new design principles for the centrifugal compressor vaned diffusers. It proved that there are practical and effective design principles for the vaned diffuser optimizations, the performance of the vaned diffuser can be improved by carefully control of two aerodynamic parameter distributions: Tangential velocity (Vt) and Meridional velocity (Vm). The vaned diffusers with subsonic, transonic and supersonic inlet conditions were optimized with the new design principles, and the peak efficiencies were increased by 4.23%, 2.15% and 2.59%, respectively. The stage pressure ratios were increased by 3.36%, 1.39% and 6.49%, respectively, and their surge margins were also improved substantially. Finally, since the Vt and Vm could affect each other during the optimization process, an interactive optimization design procedure was also presented in this paper in order to accelerate the optimization process.
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Farahat, Said, Seyyed Morteza Javadpour, Hesamodin Ebnodin Hamidi, and Ebrahim Kadivar. "Optimization of a supersonic wind tunnel diffuser using genetic algorithm." Engineering Computations 32, no. 6 (August 3, 2015): 1691–707. http://dx.doi.org/10.1108/ec-04-2014-0077.

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Purpose – The purpose of this paper is to find the optimum design of diffuser of supersonic wind tunnel in order to access the minimum overall pressure drop in wind tunnel, using evolutionary algorithm. Design/methodology/approach – The authors developed a genetic algorithm (GA) code to calculate the shape of a diffuser with flexible walls in order to have the maximum pressure recovery. The two-dimensional turbulent and compressible flow was analyzed numerically using shear-stress transport and Advection Upstream Splitting Method (AUSM)+ turbulence models and its optimization with GA. Findings – The results of this study indicate that elitist GA promises a powerful method for optimization of the wind tunnel diffuser. Separation zone is reduced by 22.2 percent at the convergent part of diffuser and 56 percent at the divergent part of diffuser. The efficiency of new optimized wind tunnel diffuser increased by 83 percent in comparison to the sample of supersonic wind tunnel. Originality/value – It has been observed that AUSM+ method and shape design optimization using GA are robust and efficient technique to optimize wind tunnel diffuser.
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Biedron, R. T., and T. C. Adamson. "Unsteady flow in a supercritical supersonic diffuser." AIAA Journal 26, no. 11 (November 1988): 1336–45. http://dx.doi.org/10.2514/3.10045.

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Matsuo, T., M. Ishikawa, and J. Umoto. "Numerical analysis of bifurcation phenomena in supersonic MHD generator with supersonic diffuser." Energy Conversion and Management 35, no. 6 (June 1994): 507–16. http://dx.doi.org/10.1016/0196-8904(94)90092-2.

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Jo, Seonghwi, Sanghyeon Han, Hong Jip Kim, and Kyung Jin Yim. "Numerical Study on the Flow and Heat Transfer Characteristics of a Second Throat Exhaust Diffuser According to Variations in Operating Pressure and Geometric Shape." Energies 14, no. 3 (January 20, 2021): 532. http://dx.doi.org/10.3390/en14030532.

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A numerical study was conducted to investigate the flow and heat transfer characteristics of a supersonic second throat exhaust diffuser for high-altitude simulations. The numerical results were satisfactorily validated by the experimental results. A subscale diffuser using nitrogen was utilized to investigate starting pressure and pressure variation in the diffuser wall. Based on the validated numerical method, the flow and heat transfer characteristics of the diffuser using burnt gas were evaluated by changing operating pressure and geometric shape. During normal diffuser operation without cooling, high-temperature regions of over 3000 K appeared, particularly near the wall and in the diffuser diverging section. After cooling, the flow and pressure distribution characteristics did not differ significantly from those of the adiabatic condition, but the temperature in the subsonic flow section decreased by more than 1000 K. Furthermore, the tendency of the heat flux from the diffuser internal flow to the wall was similar to that of the pressure variations, and it increased with operating pressure. It was confirmed that the heat fluxes of the supersonic and subsonic flows in the diffuser were proportional to the operating pressure to the 0.8 and −1.7 power, respectively. In addition, in the second throat region after separation, the heat flux could be scaled to the Mach number ratio before and after the largest oblique shock wave because the largest shock train affected the heat flux of the diffuser wall.
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Papamoschou, Dimitri. "Diffuser performance of two-stream supersonic wind tunnels." AIAA Journal 27, no. 8 (August 1989): 1124–27. http://dx.doi.org/10.2514/3.10232.

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8

Saravanan, G., Ravichandra Kumar, and A. Vinoth Kumar. "Performance Analysis of a Two-Dimensional Supersonic Diffuser." Journal of Advances in Mechanical Engineering and Science 2, no. 2 (April 30, 2016): 42–53. http://dx.doi.org/10.18831/james.in/2016021004.

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Singhal, Gaurav, Mainuddin, R. Rajesh, R. K. Tyagi, and A. L. Dawar. "Supersonic diffuser for pressure recovery in SCOIL system." Optics & Laser Technology 42, no. 1 (February 2010): 219–24. http://dx.doi.org/10.1016/j.optlastec.2009.06.009.

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Puzach, S. V. "Effect of supersonic diffuser geometry on operation conditions." Experimental Thermal and Fluid Science 5, no. 1 (January 1992): 124–28. http://dx.doi.org/10.1016/0894-1777(92)90061-9.

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Dissertations / Theses on the topic "Supersonic diffuser"

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Zebiri, Boubakr. "Étude numérique des interactions onde de choc / couche limite dans les tuyères propulsives Shock-induced flow separation in an overexpanded supersonic planar nozzle A parallel high-order compressible flows solver with domain decomposition method in the generalized curvilinear coordinates system Analysis of shock-wave unsteadiness in conical supersonic nozzles." Thesis, Normandie, 2020. http://www.theses.fr/2020NORMIR06.

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La nécessité d’une meilleure compréhension du mécanisme d’entrainement pour l’instabilité à basse fréquence observée dans un écoulement dans une tuyère sur-détendue a été discutée. Le caractère instable de l’onde de choc/couche limite reste un défi pratique important pour les problèmes des écoulements dans les tuyères. De plus, pour une couche limite turbulente incidente donnée, ce type d’écoulement présente généralement des mouvements de choc à basse fréquence plus élevées qui sont moins couplés aux échelles de temps de la turbulence en amont. Cela peut être bon du point de vue d’un expérimentateur, en raison de difficultés à mesurer des fréquences plus élevées, mais c’est plus difficile d’un point de vue calcul numérique en raison de la nécessité d’obtenir des séries temporelles plus longues pour résoudre les mouvements à basse fréquence. En excellent accord avec les résultats expérimentaux, une série de calcul LES de très longue durée a été réalisée, il a été clairement démontré l’existence de mouvements énergétiques à basse fréquence et à large bande près du point de séparation. Des efforts particuliers ont été faits pour éviter tout forçage à basse fréquence en amont, et il a été explicitement démontré que les oscillations de choc à basse fréquence observées n’étaient pas liées à la génération de turbulence d’entrée, excluant la possibilité d’un artefact numérique. Différentes méthodes d’analyse spectrales, et en décomposition en mode dynamique ont été utilisées pour montrer que les échelles de temps impliquées dans un tel mécanisme sont environ deux ordres de grandeur plus grandes que les échelles de temps impliquées dans la turbulence de la couche limite, ce qui est cohérent avec les mouvements de basse fréquence observés. En outre, ces échelles de temps se sont avérées être fortement modulées par la quantité de flux inversé à l’intérieur de la bulle de séparation. Ce scénario peut, en principe, expliquer à la fois l’instabilité des basses fréquences et sa nature à large bande
The need for a better understanding of the driving mechanism for the observed low-frequency unsteadiness in an over-expanded nozzle flows was discussed. The unsteady character of the shock wave/boundary layer remains an important practical challenge for the nozzle flow problems. Additionally, for a given incoming turbulent boundary layer, this kind of flow usually exhibits higher low-frequency shock motions which are less coupled from the timescales of the incoming turbulence. This may be good from an experimenter’s point of view, because of the difficulties in measuring higher frequencies, but it is more challenging from a computational point of view due to the need to obtain long time series to resolve low-frequency movements. In excellent agreement with the experimental findings, a very-long LES simulation run was carried out to demonstrate the existence of energetic broadband low-frequency motions near the separation point. Particular efforts were done in order to avoid any upstream low-frequency forcing, and it was explicitly demonstrated that the observed low-frequency shock oscillations were not connected with the inflow turbulence generation, ruling out the possibility of a numerical artefact. Different methods of spectral analysis and dynamic mode decomposition have been used to show that the timescales involved in such a mechanism are about two orders of magnitude larger than the time scales involved in the turbulence of the boundary layer, which is consistent with the observed low-frequency motions. Furthermore, those timescales were shown to be strongly modulated by the amount of reversed flow inside the separation bubble. This scenario can, in principle, explain both the low-frequency unsteadiness and its broadband nature
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2

Ghosh, Somnath [Verfasser]. "Direct and large eddy simulation of supersonic turbulent flow in pipes, nozzles and diffusers / Somnath Ghosh." 2008. http://d-nb.info/98843394X/34.

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Books on the topic "Supersonic diffuser"

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L, Burley Richard, Johns Albert L, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Analytical and experimental studies of a short compact subsonic diffuser for a two-dimensional supersonic inlet. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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2

A full Navier-Stokes analysis of subsonic diffuser of a a bifurcated 70/30 supersonic inlet for high speed civil transport application. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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A full Navier-Stokes analysis of subsonic diffuser of a a bifurcated 70/30 supersonic inlet for high speed civil transport application. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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4

H, Anderson Bernhard, Shaw Robert J. 1946-, and United States. National Aeronautics and Space Administration., eds. A full Navier-Stokes analysis of subsonic diffuser of a a bifurcated 70/30 supersonic inlet for high speed civil transport application. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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H, Anderson Bernhard, Shaw Robert J. 1946-, and United States. National Aeronautics and Space Administration., eds. A full Navier-Stokes analysis of subsonic diffuser of a a bifurcated 70/30 supersonic inlet for high speed civil transport application. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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6

Andreja, Brankovic, and NASA Glenn Research Center, eds. Measurement and computation of supersonic flow in a lobed diffuser-mixer for trapped vortex combustors. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2002.

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7

National Aeronautics and Space Administration (NASA) Staff. Analytical and Experimental Studies of a Short Compact Subsonic Diffuser for a Two-Dimensional Supersonic Inlet. Independently Published, 2018.

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8

D, Saunders J., and United States. National Aeronautics and Space Administration., eds. Parametrics on 2D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

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Parametrics on 2D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

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D, Saunders J., and United States. National Aeronautics and Space Administration., eds. Parametrics on 2D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

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Book chapters on the topic "Supersonic diffuser"

1

James, Jintu K., and T. M. Muruganandam. "Shock Oscillations in a Supersonic Diffuser Flow with Varying Stagnation Pressure." In 31st International Symposium on Shock Waves 2, 829–35. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91017-8_103.

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2

Ghosh, Somnath, and Rainer Friedrich. "On the Turbulence Structure in a Supersonic Diffuser with Circular Cross-Section." In High Performance Computing in Science and Engineering, Garching/Munich 2009, 89–97. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-13872-0_8.

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Manoj Prabakar, S., and T. M. Muruganandam. "Experimental Investigations of a Diffuser Start/Unstart Characteristics for Two Stream Supersonic Wind Tunnel." In 31st International Symposium on Shock Waves 2, 1119–26. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91017-8_139.

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4

Castañeda, Héctor O. "Supersonic Turbulence in Giant Extragalactic HII Regions." In Kinematics and Dynamics of Diffuse Astrophysical Media, 285–89. Dordrecht: Springer Netherlands, 1994. http://dx.doi.org/10.1007/978-94-011-0926-0_46.

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Malone, M. T., J. E. Dyson, and T. W. Hartquist. "Highly Supersonic Molecular Flows in Wind-Clump Boundary Layers." In Kinematics and Dynamics of Diffuse Astrophysical Media, 143–50. Dordrecht: Springer Netherlands, 1994. http://dx.doi.org/10.1007/978-94-011-0926-0_24.

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Prabakar, S. Manoj, Chimakurthy Srikanth, and T. M. Muruganandam. "Effect of Mach Number on Shock Oscillations in Supersonic Diffusers." In 30th International Symposium on Shock Waves 1, 257–61. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-46213-4_42.

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Ashokkumar, R., Sathiyavageeswaran Sankaran, and T. Sundararajan. "Investigation of Second Throat Supersonic Exhaust Diffusers for the Altitude Testing of Rocket Motors." In Lecture Notes in Mechanical Engineering, 647–55. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-0698-4_71.

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Ghosh, Somnath, and Rainer Friedrich. "Green's Function Analysis of Pressure-Strain Correlations in a Supersonic Pipe, Nozzle and Diffuser." In Advances in Computation, Modeling and Control of Transitional and Turbulent Flows, 311–20. WORLD SCIENTIFIC, 2015. http://dx.doi.org/10.1142/9789814635165_0030.

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"Supersonic Diffusers." In Analytical Fluid Dynamics, Third Edition, 343–69. CRC Press, 2015. http://dx.doi.org/10.1201/b19392-21.

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"18: Supersonic Diffusers." In Analytical Fluid Dynamics, 343–70. 6000 Broken Sound Parkway NW, Suite 300 Boca Raton, FL 33487-2742: CRC Press, 2015. http://dx.doi.org/10.1201/9781315148076-21.

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Conference papers on the topic "Supersonic diffuser"

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Gillen, Tyler, Michael Rybalko, and Eric Loth. "Vortex Generators for Diffuser of Axisymmetric Supersonic Inlets." In 5th Flow Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-4253.

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"Combustion-driven M3 supersonic wind tunnel with diffuser-ejector." In 25th Plasmadynamics and Lasers Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-2573.

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Sugimoto, Takao, Tsukinami Kawanishi, Hiroshige Kumamaru, and Yasumasa Tohbe. "Performance Investigation Into Supersonic Diffuser for a High Pressure Centrifugal Compressor." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25104.

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In high pressure centrifugal compressors, the overall stage performance is greatly influenced by its diffuser performance. Extremely complicated non-uniform and unsteady flow exists in the region between the impeller exit and the diffuser inlet. Furthermore, in the case of supersonic diffuser, shock waves can be observed near the diffuser inlet. These can cause aerodynamic losses. Therefore, it is essential to recognize such complicated flow to realize an appropriate diffuser design. An investigation into the performance of supersonic diffuser was carried out using a high pressure compressor test rig for a small industrial gas turbine with a high back swept impeller and a quasi pipe-shaped channel diffuser. In addition, 3D quasi-unsteady flow analyses of the entire compressor by a RANS code with Non Linear Harmonic method at several operating conditions between surge and choke were conducted to investigate the details of unsteady flow between the impeller exit and the diffuser exit. The results of the performance test and that of the 3D unsteady flow analyses have shown good agreement in the pressure rise and the isentropic efficiency at several operating conditions. These support high accuracy of the flow analyses and the performance measurements.
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Li, Xiangru, and Feng He. "Periodic Oscillations of Flow Structures in a Supersonic Diffuser Pipe." In 21st AIAA International Space Planes and Hypersonics Technologies Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-2313.

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Sung, Hong-Gye, Sangkyu Yoon, Hyowon Yeom, Jinkon Kim, Yongwook Kim, Yongsung Ko, Yongwook Kim, and Seunghyup Oh. "Study on Design- and Operation- Parameters of Supersonic Exhaust Diffuser." In 46th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-855.

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Lee, Sunghun, Myeongwon Lee, Jin Park, and Hongjip Kim. "A Numerical Study on Flow Characteristics of Super Sonic Diffuser for the Position and Nose Cone Angles of Center Body." In ASME-JSME-KSME 2019 8th Joint Fluids Engineering Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/ajkfluids2019-5430.

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Abstract The center body diffuser is one of supersonic diffuser that can simulate high-altitude environment. There is center-body structure inside the diffuser, and a complex fluid flow is occurred inside the diffuser because of the interaction of the CB structure with gas exhausted from the nozzle outlet. In this study, starting point and flow characteristics of diffuser were investigated according to changing the CB nose cone angle and the length of distance between nozzle and CB structure. The differences of the supersonic flow were compared through each parameter of CB distance and CB nose angle. First changed parameter was length between nozzle and CB. According to the length of distance between nozzle and CB, axial momentum was developed and oblique shock wave moved front of CB from end of CB nose cone. Also, when CB position was located on a certain length, starting point of CBD decreased. Next change parameter was angle of CB nose cone. According to the angle raised, angle of oblique shock wave was raised and radial momentum of supersonic diffuser developed. But, according to radial momentum of supersonic flow over certain angle, the starting pressure of CBD increased. Because axial momentum which isolated vacuum chamber from atmospheric pressure. Through these CFD analysis results, it was shown that angle and length of distance between nozzle and CB influent performance of CBD.
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Dudek, J., D. Davis, and J. Slater. "Validation and verification of the wind code for supersonic diffuser flow." In 39th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-224.

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Burrows, Travis J., Bojan Vukasinovic, and Ari Glezer. "Fluidic Control of an Aggressive Offset Diffuser for a Supersonic Inlet." In 47th AIAA Fluid Dynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-4304.

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BENSON, RUSTY, and D. MCRAE. "Numerical simulations of the unstart phenomenon in a supersonic inlet/diffuser." In 29th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-2239.

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OH, JONG, and VIGOR YANG. "Interactions Between Shock and Acoustic Waves in a Supersonic Inlet Diffuser." In 30th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-2706.

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