Journal articles: 'Supersonic combustion'

1

Huang, Shizhuo, Qian Chen, Yuwei Cheng, Jinyu Xian, and Zhengqi Tai. "Supersonic Combustion Modeling and Simulation on General Platforms." Aerospace 9, no. 7 (July 7, 2022): 366. http://dx.doi.org/10.3390/aerospace9070366.

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Supersonic combustion is an advanced technology for the next generation of aerospace vehicles. In the last two decades, numerical simulation has been widely used for the investigation on supersonic combustion. In this paper, the modeling and simulation of supersonic combustion on general platforms are thoroughly reviewed, with emphasis placed on turbulence modeling and turbulence–chemistry interactions treatment which are both essential for engineering computation of supersonic combustion. It is found that the Reynolds-averaged Navier–Stokes methods on the general platforms have provided useful experience for the numerical simulation in engineering design of supersonic combustion, while the large eddy simulation methods need to be widely utilized and further developed on these platforms. Meanwhile, the species transport models as a kind of reasonable combustion model accounting for the turbulence–chemistry interactions in supersonic combustion have achieved good results. With the development of new combustion models, especially those designed in recent years for high-speed combustion, the turbulence–chemistry interactions treatment for numerical simulation of supersonic combustion based on general platforms is expected to be further mature in the future.

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Yuan, Shengxue. "On supersonic combustion." Science in China Series A: Mathematics 42, no. 2 (February 1999): 171–79. http://dx.doi.org/10.1007/bf02876569.

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Zhao, Fei, Tianhao Di, Rong Zhu, and Wenrui Wang. "Supersonic Shrouding Methane Mixtures for Supersonic Combustion Coherent Jets." Metals 13, no. 1 (January 7, 2023): 123. http://dx.doi.org/10.3390/met13010123.

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A coherent jet oxygen supply plays a key role in the process of electric arc furnace steelmaking: it provides the necessary oxygen for the smelting of molten steel and promotes the flow of the molten pool. Compared with coherent jets in current use, the supersonic combustion coherent jet shrouded in supersonic methane gas could improve the impact capacity and stirring intensity of the molten pool. In order to reduce the smelting cost, the characteristics of the supersonic combustion coherent jet shrouding the supersonic methane and nitrogen mixtures must be studied. Computational fluid dynamics software is used to simulate the supersonic combustion coherent jet under various methane–nitrogen mixing conditions. The six-component combustion mechanism of methane and the Eddy Dissipation Concept combustion reaction model are selected. In agreement with thermal experiments, the simulation results show that the inclusion of a small amount of nitrogen has little effect on the combustion of supersonic shrouding methane gas. However, as the nitrogen content increases, the combustion region of supersonic shrouding gas becomes shorter in length, resulting in decreases in the lengths of the high-temperature, low-density region, and the high-turbulence-intensity region. These effects weaken the ability of the shrouding gas to envelop the main oxygen jet. The potential core length of the main oxygen jet decreases significantly; this decrease first accelerates and then decelerates. These results demonstrate the feasibility of including a small amount of nitrogen (about 10 wt%) in the supersonic shrouding methane gas without substantial negative impacts on the characteristics of the supersonic combustion coherent jet.

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Zhao, Fei, Rong Zhu, and Wenrui Wang. "Characteristics of the Supersonic Combustion Coherent Jet for Electric Arc Furnace Steelmaking." Materials 12, no. 21 (October 25, 2019): 3504. http://dx.doi.org/10.3390/ma12213504.

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Herein, a supersonic combustion coherent jet is proposed based on current coherent jet technology to improve the impact capacity of a coherent jet and increase the stirring intensity of the electric arc furnace (EAF) bath. Further, numerical simulations and an experimental analysis are combined to study the supersonic combustion coherent jet characteristics, including the Mach number, dynamic pressure, static temperature, vorticity, and turbulence intensity, in the EAF steelmaking environment. The results show that the supersonic combustion coherent jet exhibits stable combustion in a high-temperature EAF steelmaking environment. The supersonic combustion flame generated by the supersonic shrouding fuel gas can envelop the main oxygen jet more effectively than current coherent jets. Furthermore, the velocity attenuation, vorticity, and turbulence intensity performances of the supersonic combustion coherent jet are better when compared with those of the current coherent jet. The velocity core length of the main oxygen jet for the supersonic combustion coherent jet is 30% longer than that of the current coherent jet, resulting in an improved impact capacity and stirring intensity of the molten bath.

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Xiong, Yuefei, Jiang Qin, Kunlin Cheng, Silong Zhang, and Yu Feng. "Quasi-One-Dimensional Model of Hydrocarbon-Fueled Scramjet Combustor Coupled with Regenerative Cooling." International Journal of Aerospace Engineering 2022 (August 8, 2022): 1–14. http://dx.doi.org/10.1155/2022/9931498.

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In order to rapidly predict the performance of hydrocarbon-fueled regeneratively cooled scramjet engine in system design, a quasi-one-dimensional model has been developed. The model consists of a supersonic combustor model with finite-rate chemistry and a cooling channel model with real gas working medium, which are governed by two sets of ordinary differential equations separately. Additional models for wall friction, heat transfer, sonic fuel injection, and mixing efficiency are also included. The two sets of ordinary differential equations are coupled and iteratively solved. The SUNDIALS code is used since the equations for supersonic combustion flow are stiff mathematically. The cooling channel model was verified by electric heating tube tests, and the supersonic combustor model was verified by experimental results for both hydrogen and hydrocarbon-fueled scramjet combustors. Three cases were comparatively studied: (1) scramjet combustor with an isothermal wall, (2) scramjet combustor with an adiabatic wall, and (3) scramjet combustor with regenerative cooling. Results showed that the model could predict the axial distributions of flow parameters in the supersonic combustor and cooling channel. Differences on ignition delay time and combustion efficiency for the three cases were observed.

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Pandey, Krishna Murari, and Sukanta Roga. "CFD Analysis of Hypersonic Combustion of H₂-Fueled Scramjet Combustor with Cavity Based Fuel Injector at Flight Mach 6." Applied Mechanics and Materials 656 (October 2014): 53–63. http://dx.doi.org/10.4028/www.scientific.net/amm.656.53.

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This paper presents a numerical analysis of the inlet-combustor interaction and flow structure through a scramjet engine at a flight Mach 6 with cavity based injection. Fuel is injected at supersonic speed of Mach 2 through a cavity based injector. These numerical simulations are aimed to study the flow structure, supersonic mixing and combustion for cavity based injection. For the reacting cases, the shock wave pattern is modified which is due to the strong heat release during combustion process. The shock structure and combustion phenomenon are not only affected by the geometry but also by the flight Mach number and the trajectory. The inlet-combustor interaction is studied with a fix location of cavity based injection. Cavity is of interest because recirculation flow in cavity would provide a stable flame holding while enhancing the rate of mixing or combustion. The cavity effect is discussed from a view point of mixing and combustion efficiency.

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7

Kozlov, V. V., G. R. Grek, Yu A. Litvinenko, A. G. Shmakov, and V. V. Vikhorev. "Combustion of a plane hydrogen microjet at subsonic and supersonic speeds." Доклады Академии наук 485, no. 3 (May 21, 2019): 300–305. http://dx.doi.org/10.31857/s0869-56524853300-305.

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In this paper, we presented the results of experimental studies of the diffusion combustion of a plain hydrogen microjet flowing from a slit micronozzle at subsonic and supersonic speeds. For the first time, four scenarios of diffusion combustion of a plain hydrogen microjet including supersonic combustion in the presence of supersonic cells in both air and hydrogen are presented. The stabilization of the subsonic combustion of a hydrogen microjet was established to be due to the presence of a «bottleneck flame region» while the stabilization of the supersonic combustion of a microjet was found to be associated with the presence of supersonic cells. The observed hysteresis of diffusion combustion of a plain hydrogen microjet depends on both the method of igniting the microjet (near or far from the nozzle exit) and the direction of change in the rate of its outflow (growth or reduction).

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8

Kinoshita, Y., T. Oda, and J. Kitajima. "Research on a Methane-Fueled Low NOx Combustor for a Mach 3 Supersonic Transporter Turbojet Engine." Journal of Engineering for Gas Turbines and Power 123, no. 4 (October 1, 2000): 787–95. http://dx.doi.org/10.1115/1.1377009.

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Methane-fueled low NOx combustor research had been conducted under the Japanese supersonic/hypersonic propulsion research program. A unique form of premixture jet swirl combustor (PJSC) was proposed for the ultra low NOx combustor of a Mach 3 turbojet engine. Fuel-air mixing tests and fundamental combustion tests were conducted to obtain the design data and combustion characteristics in the first phase of the research. A single can-type combustor was fabricated and high-temperature and high-pressure combustion tests were carried out for the evaluation on NOx emission reduction capability of the PJSC concept in the second phase. In the final phase of research, a multisector combustor was fabricated and the performance demonstration test was conducted for the final evaluation of the pollutant exhaust emission goals and the combustor performance goals set in the HYPR project. The sequential three-phased program was completed successfully, and the project goals of NOx emission, combustion efficiency, pressure loss and exit gas temperature pattern factor at the Mach 3 cruise condition, together with the ICAO regulatory levels for supersonic aircraft at LTO conditions, were all achieved in the performance demonstration test.

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9

Kolosenok S.V., Kuranov A.L., Savarovskiy A.A., Bulat P.V., Galadzhun A.A., Levihin A.A., and Nikitenko A.B. "The application of supplementary fuels for the control of supersonic reacting air-fuel mix flows in the combustion chamber." Technical Physics Letters 48, no. 13 (2022): 40. http://dx.doi.org/10.21883/tpl.2022.13.53351.18764.

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Besides gas-dynamic methods, chemical ones are also suitable for the implementation of stable supersonic combustion of hydrocarbon fuels. Organoelemental compounds are known for their high reactivity, so attention was paid to organosilicon liquid during the research on the experimental model. The obtained estimates of the laminar flame speed in a mixture of vapors of this liquid with air were 0.72-0.8 m/s, which is higher than that of ethylene successfully used in supersonic combustion tests. The tested compound can be considered as a candidate for supplementary fuel to control the supersonic reactive flows in the combustion chambers of ramjet engines. Keywords: supersonic combustion, supplementary fuels, laminar flame speed, combustion efficiency

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10

Gutierrez, Albio D., and Luis F. Alvarez. "Simulation of Plasma Assisted Supersonic Combustion over a Flat Wall." Mathematical Modelling of Engineering Problems 9, no. 4 (August 31, 2022): 862–72. http://dx.doi.org/10.18280/mmep.090402.

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This work presents a simplified methodology to couple the physics of a nanosecond pulsed discharge to the process of supersonic combustion in a flat wall combustor configuration. Plasma and supersonic combustion are separately simulated and then coupled by seeding plasma-generated radicals on the combustion domain. The plasma model is built assuming spatial uniformity and considering only the kinetic effects of the nanosecond pulsed discharge. Therefore, a zero-dimensional kinetic scheme accounting for the generation of plasma species is utilized. For the combustion model, the complete set of Favre-averaged compressible Navier Stokes equations along with finite rate chemistry is solved through a control-volume based technique via the commercial software Ansys Fluent. The computational results are compared against experimental studies showing that the proposed methodology can capture the main kinetic effects of the nanosecond pulsed discharge on supersonic combustion. OH concentration contours reveal the presence of an enhanced flame when the plasma is applied following the trends from experimental OH PLIF images. In addition, time evolving temperature and OH concentration contours show that the ignition delay time is reduced with the application of the discharge.

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11

Billig, F. S. "Research on supersonic combustion." Journal of Propulsion and Power 9, no. 4 (July 1993): 499–514. http://dx.doi.org/10.2514/3.23652.

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12

Billig, Frederick S. "Supersonic combustion ramjet missile." Journal of Propulsion and Power 11, no. 6 (November 1995): 1139–46. http://dx.doi.org/10.2514/3.23952.

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13

Baev, V. K., V. I. Golovichev, and P. K. Tret'yakov. "Combustion in supersonic flow." Combustion, Explosion, and Shock Waves 23, no. 5 (1988): 511–21. http://dx.doi.org/10.1007/bf00756533.

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14

Leonov, Sergey. "Electrically Driven Supersonic Combustion." Energies 11, no. 7 (July 2, 2018): 1733. http://dx.doi.org/10.3390/en11071733.

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15

Chen, Hao, Mingming Guo, Ye Tian, Jialing Le, Hua Zhang, and Fuyu Zhong. "Intelligent reconstruction of the flow field in a supersonic combustor based on deep learning." Physics of Fluids 34, no. 3 (March 2022): 035128. http://dx.doi.org/10.1063/5.0087247.

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The data-driven intelligent reconstruction of a flow field in a supersonic combustor aids the real-time monitoring of wave system evolution in a scramjet flow field structure, allowing the determination of the combustion state for active flow control. In this paper, a deep learning architecture based on a multi-branch fusion convolutional neural network (MBFCNN) is proposed to reconstruct the flow field in a supersonic combustor. Experiments on hydrogen-fueled scramjets with different equivalence ratios were carried out in a direct-connected supersonic pulse combustion wind tunnel with an inflow Mach number of 2.5 to establish a dataset for MBFCNN network training and testing. The trained model successfully reconstructed the flow field structure from measured wall pressure data. The flow field reconstruction model provided a rich information source for the evolution of the wave system structure under the self-ignition conditions of the hydrogen-fueled scramjet, greatly improving the detection accuracy. The proposed deep learning architecture method was compared with basic convolutional neural network and symmetric convolutional neural network methods. The three methods all accurately reconstructed the flow field of the supersonic combustor. However, the proposed MBFCNN provided the best reconstruction results, and its average linear correlation coefficient in the test set was 0.952. The proposed MBFCNN had a lower mean square error and higher peak signal-to-noise ratio than the other two methods, which verified that the proposed model is eminently able to reconstruct and predict the flow field of a supersonic combustor.

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Tu, Qiuya, and Corin Segal. "Isolator/Combustion Chamber Interactions During Supersonic Combustion." Journal of Propulsion and Power 26, no. 1 (January 2010): 182–86. http://dx.doi.org/10.2514/1.46156.

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17

Wu, Hai Yyan, Meng Ding, and Yi Su. "The Study of Cavity Flow and Transpiration Cooling in Supersonic Combustion." Applied Mechanics and Materials 390 (August 2013): 370–74. http://dx.doi.org/10.4028/www.scientific.net/amm.390.370.

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To unravel the flow and heat transfer mechanism of the cavity in supersonic combustion, this paper studied the interaction of cavities and shear-layers by experiments and numerical simulation. The experiments of Nero-particle Plane Laser Scatter (NPLS) and Plane Laser-Induced Fluorescence (PLIF) were conducted to study the cavity shear-layer. In the same supersonic condition the flow was studied by the method of Large Eddy Simulation (LES). And we discussed the cavity shear-layer influence to supersonic flow and combustion, analyzed the evolvement of injection shear-layer, probed into the heat transfer of supersonic combustion, and studied the transpiration cooling of cavities. The results show: in supersonic combustion, the initial flame spreads to the upstream through the cavity shear layer, the highest wall temperature occur at the rear edge of cavity, and transpiration cooling can effectively protect the wall materials.

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18

Jin, Sangwook, Hojin Choi, Hyung Ju Lee, Jong-Ryul Byun, Juhyun Bae, and Dongchang Park. "Combustion Characteristics Based on Injector Shapeof Supersonic Combustor." Journal of the Korean Society of Propulsion Engineers 23, no. 3 (June 1, 2019): 76–87. http://dx.doi.org/10.6108/kspe.2019.23.3.076.

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19

Wang, Taiyu, Zhenguo Wang, Zun Cai, Jian Chen, Mingbo Sun, Zeyu Dong, and Bin An. "Effects of combustor geometry on the combustion process of an RBCC combustor in high-speed ejector mode." Modern Physics Letters B 33, no. 27 (September 30, 2019): 1950330. http://dx.doi.org/10.1142/s0217984919503305.

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The combustion characteristics of high-speed ejector mode in a 2-dimensional strut-based RBCC (rocket-based combined cycle) combustor had been investigated numerically in a Mach 2.5 supersonic flow. The numerical approach had been validated by comparing numerical results with available experimental data. Besides, three different hydrogen-air chemical reaction mechanisms had also been compared. The effect of the combustor geometry on the combustion process was then discussed by analyzing the heat release distribution and flow field. It was found that the wall configuration, closeout angle of the converging location and converging ratio all have significant influences on the heat release distribution and flow field structures. It is demonstrated that a converging–diverging wall configuration is beneficial for the combustion process with significant heat release increase compared to the other wall configurations. In addition, the closeout angle of the converging location is also closely related to the combustion performance, and there exists an optimized closeout angle in a specific combustor geometry. It is also revealed that the major heat release region moves upstream obviously with increase in the converging ratio, leading to an enhanced combustion process. However, the converging ratio is still to be optimized to keep a balance between heat release increase and total pressure loss of the supersonic flow.

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Zhang, Zhe, Xing Jin, and Wen-xiong Xi. "Combustion characteristics of supersonic strut-cavity combustor under plasma jet-assisted combustion." Journal of Central South University 28, no. 1 (January 2021): 311–24. http://dx.doi.org/10.1007/s11771-021-4604-2.

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21

Wang, Hongbo, Zhenguo Wang, Mingbo Sun, and Haiyan Wu. "Combustion modes of hydrogen jet combustion in a cavity-based supersonic combustor." International Journal of Hydrogen Energy 38, no. 27 (September 2013): 12078–89. http://dx.doi.org/10.1016/j.ijhydene.2013.06.132.

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Tahsini, AM. "Combustion efficiency and pressure loss balance for the supersonic combustor." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 6 (December 18, 2019): 1149–56. http://dx.doi.org/10.1177/0954410019895885.

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The purpose of this paper is to investigate the effects of intake’s compression process of the scramjet on its flight performance. The hydrogen injection to the supersonic cross-flow is considered as the problem configuration. The finite volume solver is developed to simulate the compressible reacting turbulent flow using the proper reaction mechanism as the finite rate chemistry. The combustion efficiency and the drag force are the most important parameters on the scramjet flight performance, and finding the design point to balance the higher combustion efficiency and the lower minimum drag, which depends on the total pressure loss, can be used to optimize the supersonic combustors. The performance of the supersonic intake is considered here using some oblique shock waves with equal flow-deflection angles to compute the combustor’s inlet condition. The variation of combustion efficiency and total pressure loss is presented for different combustor’s inlet conditions. The results are presented for the constant jet to inlet pressure ratios and also for the constant equivalence ratios, in which the last one is much appropriate and utilized to find the optimum design point of the intake and the combustor, for assumed flight condition.

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Gao, Tianyun, Jianhan Liang, Mingbo Sun, and Zhan Zhong. "Dynamic combustion characteristics in a rectangular supersonic combustor with single-side expansion." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 10 (August 3, 2016): 1862–72. http://dx.doi.org/10.1177/0954410016662062.

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Dynamic combustion characteristics of a rectangular scramjet combustor with single-side expansion were studied experimentally and numerically. Experiments were implemented with an isolator entrance Mach number of 3.46, and an air stagnation temperature of 1430 K. Ethylene was utilized to fuel the combustor over an equivalence ratio range of 0.20 < φ < 0.63. Results indicated that the combustion modes varied from different equivalence ratios. For an intermediate φ = 0.375, an intermittent dynamic combustion occurred. During the dynamic process, the flame sometimes stabilized in the jet wake of the top cavity, and at other time it oscillated between dual parallel cavities. The pseudo-shock train traveled periodically along the length of the combustor, and the penetration depths of the two injectors exchanged. Quantitative analysis illustrated that the average frequency of unsteady combustion was approximately 200 Hz. The reason for the occurrence of the self-sustained dynamic process was related to the interactions between the shock-induced separated region and heat release.

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Dinde, Prashant, A. Rajasekaran, and V. Babu. "3D numerical simulation of the supersonic combustion of H2." Aeronautical Journal 110, no. 1114 (December 2006): 773–82. http://dx.doi.org/10.1017/s0001924000001640.

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Results from numerical simulations of supersonic combustion of H2 are presented. The combustor has a single stage fuel injection parallel to the main flow from the base of a wedge. The simulations have been performed using FLUENT. Realisable k-ε model has been used for modelling turbulence and single step finite rate chemistry has been used for modelling the H2-Air kinetics. All the numerical solutions have been obtained on grids with average value for wall y+ less than 40. Numerically predicted profiles of static pressure, axial velocity, turbulent kinetic energy and static temperature for both non-reacting as well as reacting flows are compared with the experimental data. The RANS calculations are able to predict the mean and fluctuating quantities reasonably well in most regions of the flow field. However, the single step kinetics predicts heat release much more rapid than what was seen in the experiments. Nonetheless, the overall pressure rise in the combustor due to combustion is predicted well. Also, the k-ε model is not able to predict the fluctuating quantities in the base region of the wedge where there is strong anisotropy in the presence of combustion.

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25

Kozlov, V. V., G. R. Grek, M. M. Katasonov, M. V. Litvinenko, Yu A. Litvinenko, A. S. Tambovtsev, and A. G. Shmakov. "Features of the Round Hydrogen Microjet Combustion in a Coaxial Air Jet." Siberian Journal of Physics 14, no. 2 (2019): 21–34. http://dx.doi.org/10.25205/2541-9447-2019-14-2-21-34.

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Results of experimental studies of features of the round hydrogen microjet combustion in a coaxial air jet are presented in this work. It is shown that the combustion scenario is connected with existence of the «bottleneck flame region». This fact correlates with the similar scenarios of the diffusion hydrogen microjet combustion at subsonic efflux velocity investigated by us earlier. It is revealed that the spherical shape of the “bottleneck flame region” is transformed to a cylindrical shape. It is found that the round hydrogen microjet combustion in a coaxial air jet at supersonic efflux velocity is accompanied by existence of supersonic cells both in a hydrogen microjet and in a wake of coaxial air jet. Round hydrogen microjet supersonic combustion in a coaxial air jet is connected with a flame separation from a nozzle exit.

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Liu, Hao, Wen Yan Song, and Shun Hua Yang. "Large Eddy Simulation of Hydrogen-Fueled Supersonic Combustion with Strut Injection." Applied Mechanics and Materials 66-68 (July 2011): 1769–73. http://dx.doi.org/10.4028/www.scientific.net/amm.66-68.1769.

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In order to obtain more accurate simulation results and properties of combustion in supersonic combustion flow fields, modules of large eddy simulation of reactive turbulent flow and fifth-order WENO scheme was developed. Large eddy simulation of hydrogen-fueled supersonic combustion with strut injection was conducted. Simulations results compare were with experimental measurements, which including wall pressure, velocity, velocity fluctuation and temperature.

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Suppandipillai, Jeyakumar, Jayaraman Kandasamy, R. Sivakumar, Mehmet Karaca, and Karthik K. "Numerical investigations on the hydrogen jet pressure variations in a strut based scramjet combustor." Aircraft Engineering and Aerospace Technology 93, no. 4 (April 5, 2021): 566–78. http://dx.doi.org/10.1108/aeat-08-2020-0162.

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Purpose This paper aims to study the influences of hydrogen jet pressure on flow features of a strut-based injector in a scramjet combustor under-reacting cases are numerically investigated in this study. Design/methodology/approach The numerical analysis is carried out using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport k-ω turbulence model in contention to comprehend the flow physics during scramjet combustion. The three major parameters such as the shock wave pattern, wall pressures and static temperature across the combustor are validated with the reported experiments. The results comply with the range, indicating the adopted simulation method can be extended for other investigations as well. The supersonic flow characteristics are determined based on the flow properties, combustion efficiency and total pressure loss. Findings The results revealed that the augmentation of hydrogen jet pressure via variation in flame features increases the static pressure in the vicinity of the strut and destabilize the normal shock wave position. Indeed, the pressure of the mainstream flow drives the shock wave toward the upstream direction. The study perceived that once the hydrogen jet pressure is reached 4 bar, the incoming flow attains a subsonic state due to the movement of normal shock wave ahead of the strut. It is noticed that the increase in hydrogen jet pressure in the supersonic flow field improves the jet penetration rate in the lateral direction of the flow and also increases the total pressure loss as compared with the baseline injection pressure condition. Practical implications The outcome of this research provides the influence of fuel injection pressure variations in the supersonic combustion phenomenon of hypersonic vehicles. Originality/value This paper substantiates the effect of increasing hydrogen jet pressure in the reacting supersonic airstream on the performance of a scramjet combustor.

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Tomioka, S., T. Kohchi, R. Masumoto, M. Izumikawa, and A. Matsuo. "Supersonic Combustion with Supersonic Injection Through Diamond-Shaped Orifices." Journal of Propulsion and Power 27, no. 6 (November 2011): 1196–203. http://dx.doi.org/10.2514/1.b34164.

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Gruber, M. R., and A. S. Nejad. "New supersonic combustion research facility." Journal of Propulsion and Power 11, no. 5 (September 1995): 1080–83. http://dx.doi.org/10.2514/3.23940.

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Ratner, Albert, James F. Driscoll, Hwanil Huh, and Rodney A. Bryant. "Combustion Efficiencies of Supersonic Flames." Journal of Propulsion and Power 17, no. 2 (March 2001): 301–7. http://dx.doi.org/10.2514/2.5742.

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31

Elhawary, Shehab, Aminuddin Saat, Mohammad Amri Mazlan, and Mazlan Abdul Wahid. "Ignition Characteristics of Supersonic Combustion." IOP Conference Series: Materials Science and Engineering 884 (July 21, 2020): 012107. http://dx.doi.org/10.1088/1757-899x/884/1/012107.

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32

Billig, Frederick S. "Combustion processes in supersonic flow." Journal of Propulsion and Power 4, no. 3 (May 1988): 209–16. http://dx.doi.org/10.2514/3.23050.

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33

Waesche, R. H. Woodward. "The Basics of Supersonic Combustion." Journal of Propulsion and Power 5, no. 5 (September 1989): 513. http://dx.doi.org/10.2514/3.51299.

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34

Колосенок, С. В., А. Л. Куранов, А. А. Саваровский, П. В. Булат, А. А. Галаджун, А. А. Левихин, and А. Б. Никитенко. "Применение вспомогательных топлив для управления сверхзвуковыми потоками реагирующих топливно-воздушных смесей в канале камеры сгорания." Письма в журнал технической физики 47, no. 19 (2021): 19. http://dx.doi.org/10.21883/pjtf.2021.19.51507.18764.

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Besides gas-dynamic methods, chemical ones are also suitable for the implementation of stable supersonic combustion of hydrocarbon fuels. Organoelemental compounds are known for their high reactivity, so attention was paid to organosilicon liquid during the research on the experimental model. The obtained estimates of the laminar flame speed in a mixture of vapors of this liquid with air were 0.72-0.8 m/s, which is higher than that of ethylene successfully used in supersonic combustion tests. The tested compound can be considered as a candidate for supplementary fuel to control the supersonic reactive flows in the combustion chambers of ramjet engines.

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35

Goldfeld, Marat, and Alexey Starov. "Scheme of Hydrogen Ignition in Duct with Shock Waves." Siberian Journal of Physics 9, no. 2 (June 1, 2014): 116–27. http://dx.doi.org/10.54362/1818-7919-2014-9-2-116-127.

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In article results of the analysis of processes of self-ignition and combustion propagation are given in the multi-injector combustion chamber with high supersonic speeds of an air flow. It is established that fuel ignition at high Mach numbers, bringing to flame propagation on all volume of combustor and combustion stabilization, happens not in recirculation area behind a step, and in the field of interaction of shock waves with an boundary layer on walls or behind this area downstream near an angular point of the combustion chamber. The scheme of development of process of combustion in the combustion chamber with significantly three-dimensional configuration is in details considered

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Zhao, Zhelong, and Xianyu Wu. "Control Oriented Model for Expander Cycle Scramjet." MATEC Web of Conferences 257 (2019): 01004. http://dx.doi.org/10.1051/matecconf/201925701004.

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As a efficient and simple design, expander cycle is widely applied in LRE engineering, but it is seldomly used on scramjet research. In order to establish a complete mathematical model for expander cycle scramjet, a control-oriented model for expander cycle scramjet is proposed in this paper. This model consists of four major parts: combustor, cooling channel, turbo pump and nozzle and gives the result of pressure, temperature, mach number and velocity distribution of combustor and cooling channel and is capable of simulate both pure supersonic combustion mode and supersonic shock wave mode of the combustor. Each part is given by specific mathematical description, which contains the calculation of airflow, combustion, heat transfer and thermal cracking of kerosene. By putting all these parts together, a complete model is formed. This model is proposed to calculate the performance and condition of the engine precisely, comprehensively, swiftly and can be directly used in further study.

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Li, Chaolong, Zhixun Xia, Likun Ma, Xiang Zhao, and Binbin Chen. "Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity." Energies 12, no. 7 (March 31, 2019): 1235. http://dx.doi.org/10.3390/en12071235.

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Scramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport (SST) k − ω turbulence model are used to analyze the effects of the cavity and its position on the combustor. The feasibility of the SFRSCRJ combustor with cavity is demonstrated based on the validation of the numerical method. Results show that the scramjet combustor configuration with a backward-facing step can resist high pressure generated by the combustion in the supersonic combustor. The total combustion efficiency of the SFRSCRJ combustor mainly depends on the combustion of particles in the fuel-rich gas. A proper combustion organization can promote particle combustion and improve the total combustion efficiency. Among the four configurations considered, the combustion efficiency of the mid-cavity configuration is the highest, up to about 70%. Therefore, the cavity can effectively increase the combustion efficiency of the SFRSCRJ combustor.

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Masumoto, Ryou, Sadatake Tomioka, Kenji Kudo, Atsuo Murakami, Kanenori Kato, and Hiroyuki Yamasaki. "Experimental Study on Combustion Modes in a Supersonic Combustor." Journal of Propulsion and Power 27, no. 2 (March 2011): 346–55. http://dx.doi.org/10.2514/1.b34020.

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Kim, Chae-Hyoung, and In-Seuck Jeung. "Forced Combustion Characteristics Related to Different Injection Locations in Unheated Supersonic Flow." Energies 12, no. 9 (May 8, 2019): 1746. http://dx.doi.org/10.3390/en12091746.

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This work focuses on forced combustion with regards to the relationship between vent mixer models and several injection locations in unheated supersonic flow. A plasma jet torch was used to ignite the hydrogen-air mixture in a laboratory-scaled combustor duct. The flow field of the combustion was visualized with pressure and gas-sampling measurements. The vent mixers indicate good dispersion characteristics of the mixture for both parallel and normal 1 injections. However, forced combustion is dominantly governed by the injection rate toward the plasma jet (hot source) because the combustible region is restricted under the cold main flow. For this reason, the parallel injection, which provides the hydrogen-air mixture directly toward the plasma jet, shows good combustion performance. The normal 1 injection interacted with the vent mixers and shows slightly good combustion performance. Lastly, the normal 2 injection is little affected by the vent mixers and has poor combustion performance.

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40

Yan, Chong, Yibing Xu, Ruizhe Cao, and Ying Piao. "Investigation of Very Large Eddy Simulation Method for Applications of Supersonic Turbulent Combustion." Aerospace 10, no. 4 (April 21, 2023): 384. http://dx.doi.org/10.3390/aerospace10040384.

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The very large eddy simulation (VLES) method was investigated for supersonic reacting flows in the present work. The advantages and characteristics of the VLES model and the widely used improved delayed detached eddy simulation (IDDES) method were revealed through a supersonic ramped-cavity cold flow. Compared to the IDDES model, the VLES model transformed from RANS mode to LES mode faster, resulting in a smaller gray region caused by the mode transition. However, the original volume-averaging truncation length scale could lead to poor predictions of the velocity profiles and wall pressure distribution. By introducing a hybrid truncation length scale combining the maximum grid length and the shear layer adaptive (SLA) length with different coefficients, the accuracy of the VLES method was significantly improved, and the issue of the low shear layer position was solved. Moreover, owing to the resolution control function, the VLES method could adaptively model more turbulent kinetic energy and maintain a good accuracy in a coarser mesh. Finally, the modified VLES method was applied in conjunction with a hybrid combustion model constructed by the partially stirred reactor (PaSR) model and the Ingenito supersonic combustion model (ISCM) in simulations of the supersonic flame in the DLR scramjet combustor. After introducing the correction of the molecular collision frequency by the ISCM, the results obtained by the hybrid combustion model were more consistent with the experimental results, especially for the time-averaging temperature profile in the ignition zone.

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Kozlov, V. V., G. R. Grek, M. V. Litvinenko, Yu A. Litvinenko, A. S. Tambovzev, and A. G. Shmakov. "Air Round Microjet Interaction with Coaxial Hydrogen Jet at It Combustion for Supersonic Speed Jets Efflux." Siberian Journal of Physics 14, no. 3 (2019): 53–63. http://dx.doi.org/10.25205/2541-9447-2019-14-3-53-63.

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Results of experimental studies of the round air microjet interaction with a coaxial hydrogen jet at its combustion for supersonic speed jets efflux are presented in this work. It is revealed that combustion of the coaxial hydrogen jet with growth of its speed efflux is accompanied by all scenarios, observed at study of the round and plane hydrogen microjets diffusion combustion. However, “bottleneck flame region” undergoes considerable geometrical deformations because of specifics of a flame of a coaxial jet. It is shown that “bottleneck flame region” is transformed from Y-shaped to spherical shape in the activity of growth of a coaxial jet speed efflux. It is found that a round air microjet interaction with a coaxial hydrogen jet at its combustion is accompanied by several new phenomena: existence of cone-shaped area a coaxial jet combustion near a nozzle exit; existence of small-scale supersonic cells on a resultant flame; absence of the hydrogen combustion efflux from combustion region of a coaxial jet near nozzle exit; flame-out from combustion region of a coaxial jet near nozzle exit that leads to hydrogen ignition downstream, its intensive combustion and sharp acoustic noise occurrence; existence of a turbulent flame, to its separation from a nozzle exit and transition to supersonic combustion of a resultant jet.

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Vinogradov, Viacheslav A., Yurii M. Shikhman, and Corin Segal. "A Review of Fuel Pre-injection in Supersonic, Chemically Reacting Flows." Applied Mechanics Reviews 60, no. 4 (July 1, 2007): 139–48. http://dx.doi.org/10.1115/1.2750346.

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Developing an efficient, supersonic combustion-based, air breathing propulsion cycle operating above Mach 3.5, especially when conventional hydrocarbon fuels are sought and particularly when liquid fuels are preferred to increase density, requires mostly effective mechanisms to improve mixing efficiency. One way to extend the time available for mixing is to inject part of the fuel upstream of the vehicle’s combustion chamber. Injection from the wall remains one of the most challenging problems in supersonic aerodynamics, including the requirement to minimize impulse losses, improve fuel-air mixing, reduce inlet∕combustor interactions, and promote flame stability. This article presents a review of studies involving liquid and, in selected cases, gaseous fuel injected in supersonic inlets or in combustor’s insulators. In all these studies, the fuel was injected from a wall in a wake of thin swept pylons at low dynamic pressure ratios (qjet∕qair=0.6–1.5), including individual pylon∕injector geometries and combinations in the inlet and combustor’s isolator, a variety of injection conditions, different injectants, and evaluated their effects on fuel plume spray, impulse losses, and mixing efficiency. This review article cites 47 references.

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43

Kozlov, V. V., M. V. Litvinenko, Yu A. Litvinenko, A. S. Tambovzev, and A. G. Shmakov. "Diffusion Combustion during Interaction of a Supersonic Round Microjet of Air with a Coaxial (Coflowing Ring) Jet of Hydrogen." Doklady Physics 66, no. 1 (January 2021): 5–8. http://dx.doi.org/10.1134/s102833582102004x.

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Abstract The results of experimental investigations of the features of diffusion combustion during the interaction of a round supersonic microjet of air in the center and a coaxial (coflowing ring) jet of hydrogen. Such combustion is accompanied by a number of new phenomena: the formation of a cone-shaped flame near the nozzle сutoff, the locking of the combustion region in this cone, the presence of small-scale supersonic cells in the resulting flow, and the formation of laminar sections and their turbulization.

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Nair, Prasanth P., Amsha S, Abhilash Suryan, and Sandro Nizetic. "Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency." International Journal of Energy Research 45, no. 1 (March 6, 2020): 231–53. http://dx.doi.org/10.1002/er.5257.

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Relangi, Naresh, Antonella Ingenito, and Suppandipillai Jeyakumar. "The Implication of Injection Locations in an Axisymmetric Cavity-Based Scramjet Combustor." Energies 14, no. 9 (May 4, 2021): 2626. http://dx.doi.org/10.3390/en14092626.

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This paper presents the effect of cavity-based injection in an axisymmetric supersonic combustor using numerical investigation. An axisymmetric cavity-based angled and transverse injections in a circular scramjet combustor are studied. A three-dimensional Reynolds-averaged Navier–Stokes (RANS) equation along with the k-ω shear-stress transport (SST) turbulence model and species transport equations are considered for the reacting flow studies. The numerical results of the non-reacting flow studies are validated with the available experimental data and are in good agreement with it. The performance of the injection system is analyzed based on the parameters like wall pressures, combustion efficiency, and total pressure loss of the scramjet combustor. The transverse injection upstream of the cavity and at the bottom wall of the cavity in a supersonic flow field creates a strong shock train in the cavity region that enhances complete combustion of hydrogen-air in the cavity region compared to the cavity fore wall injection schemes. Eventually, the shock train in the flow field enhances the total pressure loss across the combustor. However, a marginal variation in the total pressure loss is observed between the injection schemes.

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WANG, JIANGFENG, CHEN LIU, and YIZHAO WU. "NUMERICAL SIMULATION OF SPRAY ATOMIZATION IN SUPERSONIC FLOWS." Modern Physics Letters B 24, no. 13 (May 30, 2010): 1299–302. http://dx.doi.org/10.1142/s0217984910023475.

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With the rapid development of the air-breathing hypersonic vehicle design, an accurate description of the combustion properties becomes more and more important, where one of the key techniques is the procedure of the liquid fuel mixing, atomizing and burning coupled with the supersonic crossflow in the combustion chamber. The movement and distribution of the liquid fuel droplets in the combustion chamber will influence greatly the combustion properties, as well as the propulsion performance of the ramjet/scramjet engine. In this paper, numerical simulation methods on unstructured hybrid meshes were carried out for liquid spray atomization in supersonic crossflows. The Kelvin-Helmholtz/Rayleigh-Taylor hybrid model was used to simulate the breakup process of the liquid spray in a supersonic crossflow with Mach number 1.94. Various spray properties, including spray penetration height, droplet size distribution, were quantitatively compared with experimental results. In addition, numerical results of the complex shock wave structure induced by the presence of liquid spray were illustrated and discussed.

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Tomioka, Sadatake, Atsuo Murakami, Kenji Kudo, and Tohru Mitani. "Combustion Tests of a Staged Supersonic Combustor with a Strut." Journal of Propulsion and Power 17, no. 2 (March 2001): 293–300. http://dx.doi.org/10.2514/2.5741.

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48

Patrick, Chris. "Understanding supersonic combustion with numerical simulation." Scilight 2021, no. 21 (May 21, 2021): 211106. http://dx.doi.org/10.1063/10.0005106.

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Cui, Tao, Shengbo Yang, and Daren Yu. "Ideal Heat Release of Supersonic Combustion." Journal of Propulsion and Power 29, no. 3 (May 2013): 621–27. http://dx.doi.org/10.2514/1.b34735.

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Ladeinde, Foluso, and Zhipeng Lou. "Improved Flamelet Modeling of Supersonic Combustion." Journal of Propulsion and Power 34, no. 3 (May 2018): 750–61. http://dx.doi.org/10.2514/1.b36779.

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Journal articles on the topic 'Supersonic combustion'

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