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Статті в журналах з теми "Supersonic diffuser"

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Автор: Grafiati

Опубліковано: 10 грудня 2022

Оновлено: 29 січня 2023

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1

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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Анотація:

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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2

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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3

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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Анотація:

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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4

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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5

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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6

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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Анотація:

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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7

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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9

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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10

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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11

Puzach, S. V., N. N. Zakharov, S. V. Sovin, and R. A. Yanson. "Startup and steady operating conditions of supersonic diffuser." Journal of Engineering Physics 61, no. 1 (July 1991): 856–62. http://dx.doi.org/10.1007/bf00871563.

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12

Farahani, M., N. Fouladi, and AR Mirbabaei. "Design and analysis of a cooling system for a supersonic exhaust diffuser." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 14 (April 2019): 5253–63. http://dx.doi.org/10.1177/0954410019840970.

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Анотація:

High-altitude test facilities are usually used to evaluate the performance of space mission engines. The supersonic exhaust diffuser, a main part of high-altitude test facility, provides the required test cell vacuum conditions by self-pumping the nozzle exhaust gases to the atmosphere. However, the plume temperature is often much higher than the temperature the diffuser structure is able to withstand, usually above 2500 K. In this study, an efficient cooling system is designed and analyzed to resolve the thermal problem. A water spray cooling technique is preferred among various existing techniques. Here, a new algorithm is developed for a spray cooling system for a supersonic exhaust diffuser. This algorithm uses a series of experimental and geometrical relationships to resize the governing parameters and remove the required heat flux from the diffuser surface. The efficiency of the newly designed cooling system is evaluated via numerical simulations. The utilized numerical technique is based on the discrete-phase method. Various computational studies are accomplished to enhance the accuracy of numerical prediction and validation. The present numerical study is validated using experimental results. The results show that the realizable k-ɛ method is superior compared to other Reynolds-averaged Navier–Stokes models.

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13

Li, Zeng Cai, Heng Sun, Bao Ling Guo, and Feng Liu. "A Design Method of Supersonic Separator Used in Natural Gas Liquefaction Process." Advanced Materials Research 608-609 (December 2012): 1309–13. http://dx.doi.org/10.4028/www.scientific.net/amr.608-609.1309.

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Анотація:

It is feasible to obtain low temperature that can liquefy the natural gas using supersonic separator in a liquefaction process. This paper represented a design method of the supersonic separator used in natural gas liquefaction plant, including the design of the Laval nozzle, the design of the rectifier straight segment and the design of the diffuser segment. The size of each part and the appropriate shape can be gotten by the theoretical calculation. The design results of an experiment liquefaction device using supersonic separator is given. The work is helpful for the natural gas transportation in remote and low production gas field.

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14

Rao, M. Srinivasa, Afroz Javed, and Debasis Chakraborty. "Numerical Characterisation of Supersonic Exhaust Diffusers." Defence Science Journal 67, no. 2 (March 14, 2017): 219. http://dx.doi.org/10.14429/dsj.67.9544.

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Анотація:

<p>Rocket motors that are designed to operate at high altitudes need a nozzle with a large expansion ratio to maximize the thrust at much lower atmospheric pressure than that of the sea level pressure. Accurate performance of these nozzles cannot be obtained when static tested on ground. Computational fluid dynamics (CFD) analyses have been performed to characterise the supersonic exhaust diffuser (SED). The results obtained from the CFD analyses have been found to be in good agreement with experimental and numerical values reported in the published literature. Started and un-started regions of the SED have been identified with the CFD results.</p>

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15

Huang Zhilong, 黄知龙, 张国彪 Zhang Guobiao, 耿子海 Geng Zihai, and 陈吉明 Chen Jiming. "Performance of line-divergence subsection supersonic diffuser for COIL." High Power Laser and Particle Beams 23, no. 5 (2011): 1211–14. http://dx.doi.org/10.3788/hplpb20112305.1211.

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16

Chen, Falin, C. F. Liu, and J. Y. Yang. "Supersonic flow in the second-throat ejector-diffuser system." Journal of Spacecraft and Rockets 31, no. 1 (January 1994): 123–29. http://dx.doi.org/10.2514/3.26411.

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17

YOSHIKAWA, Hisataka, Makoto YAMAMOTO, and Sinji HONAMI. "Numerical Simulation of Subsonic Diffuser for Supersonic Air-Intake(Effects of Blowing on Diffuser Performance)." Transactions of the Japan Society of Mechanical Engineers Series B 65, no. 631 (1999): 876–81. http://dx.doi.org/10.1299/kikaib.65.876.

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18

Li, Yiqiao, Shengqiang Shen, Chao Niu, Yali Guo, and Liuyang Zhang. "The Effect of Different Pressure Conditions on Shock Waves in a Supersonic Steam Ejector." Energies 15, no. 8 (April 15, 2022): 2903. http://dx.doi.org/10.3390/en15082903.

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Анотація:

The complex flow phenomena in a three-dimensional supersonic steam ejector were simulated with a non-equilibrium condensation model including real physical properties in different pressure conditions. The different working conditions include discharge pressure, motive pressure, and suction pressure. The influence of different pressures on shock waves in the steam ejector was investigated comprehensively. The intrinsic causes of shock wave variation with pressure conditions were explained in detail. The results show that the width of the primary shock train region expand with an increase in the motive pressure or a decrease in suction pressure. The diamond shock waves move downstream with an increase in motive pressure or a decrease in suction pressure. The shocking position in the diffuser moves upstream until it reaches the diffuser entrance with an increase in discharge pressure or a decrease in motive pressure or suction pressure. The intensity and number of oblique shock waves in the diffuser increase with an increase in motive pressure and suction pressure or a decrease in discharge pressure. The existence of only one shock wave in the diffuser is a necessary and insufficient condition for the ejector to enter a double choking mode.

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19

Kim, Jong Rok. "Numerical Study on the Adverse Pressure Gradient in Supersonic Diffuser." Journal of the Korean Society of Propulsion Engineers 17, no. 4 (August 1, 2013): 43–48. http://dx.doi.org/10.6108/kspe.2013.17.4.043.

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20

Kong, Fan Shi, Heuy Dong Kim, Yingzi Jin, and Toshiaki Setoguchi. "Application of Chevron Nozzle to a Supersonic Ejector–diffuser System." Procedia Engineering 56 (2013): 193–200. http://dx.doi.org/10.1016/j.proeng.2013.03.107.

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21

Annamalai, K., T. N. V. Satyanarayana, K. A. Bhaskaran, and V. Sriramulu. "Development of design methods for short cylindrical supersonic exhaust diffuser." Experiments in Fluids 29, no. 4 (October 4, 2000): 305–8. http://dx.doi.org/10.1007/s003489900071.

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22

Liu, Yi, and Brain J. Bellhouse. "Prediction of jet flows in the supersonic nozzle and diffuser." International Journal for Numerical Methods in Fluids 47, no. 10-11 (2005): 1147–55. http://dx.doi.org/10.1002/fld.919.

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23

Rtischeva, A. S. "Gas Dynamic Design and Numerical Study of Supersonic Circuit of Wind Tunnel." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 1 (136) (March 2021): 68–84. http://dx.doi.org/10.18698/0236-3941-2021-1-68-84.

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Анотація:

For an advanced trisonic wind tunnel of a straight-flow type with a test section size of 1.2 × 1.2, intended for ground tests of rocket-space and aviation aircraft models, we implemented a gas-dynamic design of the circuit and did numerical simulation of the flow for the main supersonic regimes (M = 2, M = 4). The gas-dynamic design of the wind tunnel circuit was carried out on the basis of techniques developed at TsAGI and operating experience of existing facilities. The study considers both traditional configurations of the duct with the bending of the walls of all elements, i.e., nozzle, test section and diffuser in the XY plane, and alternative design developments with the bending of the diffuser walls in the XZ plane. When carrying out numerical studies in all areas of the wind tunnel, the ANSYS Fluent software package was used to solve the Navier --- Stokes equations for viscous and heat-conducting air using the turbulence model, i.e., Spalart --- Allmaras, SST. The paper investigates the effect of the wall opening angle, compensating the increasing thickness of boundary-layer longwise displacement, on the flow characteristics; shows the possibilities of obtaining a sufficiently uniform flow with the Mach number accuracy ΔM = ± 0.005 in the area of the model, and analyzes the influence of geometric parameters and boundary conditions on the efficiency of the supersonic diffuser

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24

Hamood, Hasson Shaban. "Performance Prediction of Internal Compression Supersonic Air Intake at Range of Mach Numbers (1.1-1.5)." Tikrit Journal of Engineering Sciences 23, no. 3 (August 31, 2016): 37–46. http://dx.doi.org/10.25130/tjes.23.3.04.

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In this research a numerical investigation on a supersonic air intake was done. The aim of this work is to investigate a variable geometry of cross-section area for supersonic air intake at range (1.1-1.5) Mach number, to get a maximum pressure recovery. In this work, the flow starts with a normal shock attached to the intake cowl lip. The flow is assumed compressible, inviscid, two-dimensional flow, unsteady, and axisymmetric. The equations (Continuity, Momentum, and Energy) were solved based on a finite volume method. The governing equations were solved iteratively using time marching technique. This part is analyzed for several Mach numbers, where the flow properties are determined from inlet of air intake to the diffuser exit. Results show that, the implementation of time marching scheme has succeeded in the prediction of the choked flow region, which is important in the study of the performance of convergent-divergent diffuser. Also the results indicated the absolute velocity increases along the convergent part and then start to decrease along divergent part independently on the values of free-stream Mach numbers.

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25

Couder-Castañeda, Carlos. "Simulation of Supersonic Flow in an Ejector Diffuser Using the JPVM." Journal of Applied Mathematics 2009 (2009): 1–21. http://dx.doi.org/10.1155/2009/497013.

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The ejectors are used commonly to extract gases in the petroleum industry where it is not possible to use an electric bomb due the explosion risk because the gases are flammable. The steam ejector is important in creating and holding a vacuum system. The goal of this job is to develop an object oriented parallel numerical code to investigate the unsteady behavior of the supersonic flow in the ejector diffuser to have an efficient computational tool that allows modeling different diffuser designs. The first step is the construction of a proper transformation of the solution space to generate a computational regular space to apply an explicit scheme. The second step, consists in developing the numerical code with an-object-oriented parallel methodology. Finally, the results obtained about the flux are satisfactory compared with the physical sensors, and the parallel paradigm used not only reduces the computational time but also shows a better maintainability, reusability, and extensibility accuracy of the code.

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26

Oh, Jong Y., Fuhua Ma, Shih-Yang Hsieh, and Vigor Yang. "Interactions Between Shock and Acoustic Waves in a Supersonic Inlet Diffuser." Journal of Propulsion and Power 21, no. 3 (May 2005): 486–95. http://dx.doi.org/10.2514/1.9671.

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27

Golovachev, Yu P., and S. Yu Sushchikh. "Influence of electrode commutation on magnetohydrodynamic flow in a supersonic diffuser." Technical Physics Letters 25, no. 5 (May 1999): 337–40. http://dx.doi.org/10.1134/1.1262473.

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28

Ghosh, Somnath, and Rainer Friedrich. "Direct numerical simulation of turbulent flow in an axisymmetric supersonic diffuser." Journal of Turbulence 11 (January 2010): N17. http://dx.doi.org/10.1080/14685248.2010.481817.

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29

Mahapatra, Susila, Sandeep Kumar, Kalyan P. Sinhamahapatra, and Somnath Ghosh. "Large-eddy simulation of shock-turbulence interaction in supersonic diffuser flows." Journal of Turbulence 18, no. 6 (April 3, 2017): 512–38. http://dx.doi.org/10.1080/14685248.2017.1305495.

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30

Monti, Rodolfo, Diego Paterna, Raffaele Savino, and Antonio Esposito. "Low-Reynolds number supersonic diffuser for a plasma-heated wind tunnel." International Journal of Thermal Sciences 40, no. 9 (October 2001): 804–15. http://dx.doi.org/10.1016/s1290-0729(01)01267-4.

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31

Zaikovskii, V. N., V. M. Trofimov, and S. I. Shtrekalkin. "Experimental and computational investigation of heat fluxes in a supersonic diffuser." Journal of Applied Mechanics and Technical Physics 37, no. 1 (January 1996): 135–40. http://dx.doi.org/10.1007/bf02369413.

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32

Kim, Sehoon, Hyungjun Kim, and Sejin Kwon. "Transitional behavior of a supersonic flow in a two-dimensional diffuser." KSME International Journal 15, no. 12 (December 2001): 1816–21. http://dx.doi.org/10.1007/bf03185139.

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33

Inui, Yoshitaka, Akinori Kosugi, and Motoo Ishikawa. "Two-Dimensional Analysis of Supersonic Nonequilibrium Disk MHD Generator Considering Diffuser." IEEJ Transactions on Power and Energy 120, no. 2 (2000): 278–85. http://dx.doi.org/10.1541/ieejpes1990.120.2_278.

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34

Mehta, R. C., and G. Natarajan. "Numerical simulations of convergent-divergent nozzle and straight cylindrical supersonic diffuser." Advances in aircraft and spacecraft science 1, no. 4 (October 25, 2014): 399–408. http://dx.doi.org/10.12989/aas.2014.1.4.399.

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35

Jia, Yicong, Zhiyan Li, Wei Ye, and Wanwu Xu. "Numerical and experimental investigation of an adjustable dual-channel supersonic diffuser." Acta Astronautica 157 (April 2019): 102–10. http://dx.doi.org/10.1016/j.actaastro.2018.12.017.

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36

ALHUSSAN, KHALED, and CHARLES GARRIS. "EFFECT OF CHANGING THROAT DIAMETER RATIO ON A STEAM SUPERSONIC PRESSURE EXCHANGE EJECTOR." Modern Physics Letters B 19, no. 28n29 (December 20, 2005): 1715–18. http://dx.doi.org/10.1142/s0217984905010293.

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Анотація:

This paper will explain the structure of the flow induction in a non-steady supersonic fluid in which steam is the working fluid. The ratio of the throat diameter is varied and the analyses related to the induction processes are studied. This ejector is used for compression applications. The work to be presented herein is a Computational Fluid Dynamics investigation of the complex fluid mechanisms that occur inside a non-steady, three-dimensional, steam supersonic pressure exchange ejector, specifically with regard to the pressure exchange mechanisms and the induction processes between a primary fluid and a secondary fluid and how this is related to the shape of the aerodynamic shroud-diffuser surface. The results will show the correct throat diameter ratio that is capable of producing the desire affect of the flow induction in a three-dimensional supersonic, non-steady, viscous flow. The calculated throat diameter ration is about 2.90.

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37

Zheng, Lixing, Hongwei Hu, Weibo Wang, Yiyan Zhang, and Lingmei Wang. "Study on Flow Distribution and Structure Optimization in a Mix Chamber and Diffuser of a CO2 Two-Phase Ejector." Mathematics 10, no. 5 (February 23, 2022): 693. http://dx.doi.org/10.3390/math10050693.

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Анотація:

This paper establishes a mathematic model of a CO2 two-phase ejector to investigate flow distribution in the components of a mixing chamber and diffuser. The suction chamber was modeled using the characteristic line method to describe the development process of the supersonic expansion wave, and the mixing chamber, as well as diffuser models, were built based on the double-flow model. The reliability of the model was verified by experimental data. The distributions of flow parameters along the axis of the mixing chamber and diffuser were analyzed under different expansion ratios of the ejector. Structure optimizations of the mixing chamber and diffuser were conducted. The results showed that the primary flow temperature gradually increased along the axis of the mixing chamber and diffuser, but the Mach number distribution decreased for a certain ejector expansion ratio. The temperature and Mach number of the secondary flow showed the opposite trend. Moreover, at the initial stage of mixing, the fluid pressure increased rapidly, and the Mach number of the primary flow decreased rapidly. The gas-phase fraction of primary flow increased gradually in the mixing chamber and was stable in the diffuser. When the length–diameter ratio of the mixing chamber was about 10.8–12, it was beneficial to mix uniformity, and when the expansion angle of the diffuser was 4–6°, the ejector had a better ejector efficiency.

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38

Li, Ke Xin, Qi Tai Eri, Chen Yang Yan, Wei An Ji, and Pei Ran Su. "Research on the Optimization Design of Supersonic Swirling Separator." Applied Mechanics and Materials 444-445 (October 2013): 332–37. http://dx.doi.org/10.4028/www.scientific.net/amm.444-445.332.

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Анотація:

Supersonic swirling separator had a good ability in separating gas-liquid. In this paper, the Laval-nozzle and straight-tube of the non-central cone supersonic swirling separator were optimized designing. The separation performance of the optimized supersonic swirling separator was researched by CFX. The results show that,with the relative pressure ratio decreasing, the shock waves which occurred in the diffuser moved towards the extraction device, the maximum Mach number decreasing. When the relative pressure ratio down to 1.4, the outlet total pressure recovered to 73% of the inlet total pressure, the flow in the divergent section of Laval-nozzle and the straight-tube was supersonic, the lowest temperature can be down to-84.5°C and the maximum centrifugal acceleration was 261,800g, which provided a swirling and cold environment for the separation of gas-liquid; With the straight-tubes length-diameter ratio increased, a normal shock wave occurred in the straight-tube. Further increased the length-diameter ratio, the normal shock wave moved towards the throat and the strength of the shock wave was increasing, which was a disadvantage to the separation of the gas-liquid.

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39

Utomo, Muhammad Adnan, and Romie Oktavianus Bura. "Design of Inward-Turning External Compression Supersonic Inlet for Supersonic Transport Aircraft." INSIST 2, no. 2 (January 25, 2019): 104. http://dx.doi.org/10.23960/ins.v2i2.90.

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Анотація:

Inward-turning external compression intake is one of the hybrid intakes that employs both external and internal compression intakes principle. This intake is commonly developed for hypersonic flight due to its efficiency and utilizing fewer shockwaves that generate heat. Since this intake employ less shockwaves, this design can be applied for low supersonic (Mach 1.4 - 2.5) intakes to reduce noise generated from the shockwaves while maintaining the efficiency. Other than developing the design method, a tool is written in MATLAB language to generate the intake shape automatically based on the desired design requirement. To investigate the intake design tool code and the performance of the generated intake shape, some CFD simulation were performed. The intake design tool code can be validated by comparing the shockwave location and the air properties in every intake's stations. The performance parameters that being observed are the intake efficiency, flow distortion level at the engine face, and the noise level generated by the shockwaves. The design tool written in MATLAB is working as intended. Two dimensional axisymmetric CFD simulations validation has been done and the design meets the minimum requirement. As for the 3D inlet geometry, with a little modification on diffuser and equipping vent to release the buildup pressure, the inlet has been successfully met the military standard on inlet performance (MIL-E-5007D). This design method also has feature to fit every possible throat cross sectional shapes and has been proven to work as designed.Keywords— Inward-turning, Supersonic, Engine Intakes, Low- noise, Design Method

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40

Ashokkumar, R., S. Sankaran, K. Srinivasan, and T. Sundararajan. "Effects of Vacuum Chamber and Reverse Flow on Supersonic Exhaust Diffuser Starting." Journal of Propulsion and Power 31, no. 2 (March 2015): 750–54. http://dx.doi.org/10.2514/1.b35156.

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41

Kong, Fanshi, Yingzi Jin, and Heuydong Kim. "Study of the Supersonic Ejector-Diffuser System with a Mixing Guide Vane." Journal of the Korean Society of Propulsion Engineers 17, no. 1 (February 1, 2013): 52–60. http://dx.doi.org/10.6108/kspe.2013.17.1.052.

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42

Annamalai, K., K. Visvanathan, V. Sriramulu, and K. A. Bhaskaran. "Evaluation of the performance of supersonic exhaust diffuser using scaled down models." Experimental Thermal and Fluid Science 17, no. 3 (July 1998): 217–29. http://dx.doi.org/10.1016/s0894-1777(98)00002-8.

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43

Ziaei-Rad, S., and M. Ziaei-Rad. "Inverse design of supersonic diffuser with flexible walls using a Genetic Algorithm." Journal of Fluids and Structures 22, no. 4 (May 2006): 529–40. http://dx.doi.org/10.1016/j.jfluidstructs.2006.01.006.

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44

Zhang, Jinsheng, Huacheng Yuan, Yunfei Wang, and Guoping Huang. "Experiment and numerical investigation of flow control on a supersonic inlet diffuser." Aerospace Science and Technology 106 (November 2020): 106182. http://dx.doi.org/10.1016/j.ast.2020.106182.

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45

Lijo, Vincent, Heuy Dong Kim, Shigeru Matsuo, and Toshiaki Setoguchi. "A study of the supersonic ejector–diffuser system with an inlet orifice." Aerospace Science and Technology 23, no. 1 (December 2012): 321–29. http://dx.doi.org/10.1016/j.ast.2011.08.009.

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46

Park, Byung Hoon, Ji Hyung Lee, and Woongsup Yoon. "Studies on the starting transient of a straight cylindrical supersonic exhaust diffuser: Effects of diffuser length and pre-evacuation state." International Journal of Heat and Fluid Flow 29, no. 5 (October 2008): 1369–79. http://dx.doi.org/10.1016/j.ijheatfluidflow.2008.04.006.

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47

Friso, Dario. "Mathematical Modelling of the Entrainment Ratio of High Performance Supersonic Industrial Ejectors." Processes 10, no. 1 (January 2, 2022): 88. http://dx.doi.org/10.3390/pr10010088.

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Анотація:

For many years now, manufacturers have been producing supersonic ejectors with a high entrainment ratio for the chemical, oil, and food industries. In the present work, mathematical modelling of the entrainment ratio of such industrial ejectors is carried out, in which a variation of the diffuser efficiency is also assumed to be a function of the Mach number of the motive gas. To determine this unknown relationship, the mathematical modelling was overturned by inserting the entrainment ratios of ten different high-performance industrial ejectors, as identified through an experimental investigation. The mathematical modelling, completed through the use of the relationship between the diffuser efficiency and the Mach number of the motive gas, was applied to sixty-eight ejectors, built and tested experimentally over the last twenty years as part of research aimed at the development of thermal ejector refrigeration systems (ERSs), to obtain the entrainment ratios proposed by the manufacturers (industrial entrainment ratios). A comparison of the experimental entrainment ratios with respect to the industrial ones demonstrated that the former were always lower, ranging from a minimum of −17% to a maximum of −82%. These results indicate that the lab-built ejectors for ERS prototypes can be improved. Therefore, in the future, researchers should apply numerical analysis iteratively, starting from a given geometry of the ejector, and modifying it until the numerical analysis provides the industrial value of the entrainment ratio.

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48

Kumari, Komal, Susila Mahapatra, Somnath Ghosh, and Joseph Mathew. "Invariants of velocity gradient tensor in supersonic turbulent pipe, nozzle, and diffuser flows." Physics of Fluids 30, no. 1 (January 2018): 015104. http://dx.doi.org/10.1063/1.5004468.

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49

Kim, Heuydong, Youngki Lee, Toshiaki Setoguchi, and Shen Yu. "Numerical simulation of the supersonic flows in the second throat ejector-diffuser systems." Journal of Thermal Science 8, no. 4 (December 1999): 214–22. http://dx.doi.org/10.1007/s11630-999-0009-5.

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50

Kim, Heuy-Dong, Toshiaki Setoguchi, Shen Yu, and S. Raghunathan. "Navier-Stokes computations of the supersonic ejector-diffuser system with a second throat." Journal of Thermal Science 8, no. 2 (June 1999): 79–83. http://dx.doi.org/10.1007/s11630-999-0028-2.

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