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Gotowa bibliografia na temat „Scramjet combustor”

Autor: Grafiati

Data publikacji: 6 września 2023

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Artykuły w czasopismach na temat "Scramjet combustor"

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Xiong, Yuefei, Jiang Qin, Kunlin Cheng, Silong Zhang i Yu Feng. "Quasi-One-Dimensional Model of Hydrocarbon-Fueled Scramjet Combustor Coupled with Regenerative Cooling". International Journal of Aerospace Engineering 2022 (8.08.2022): 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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Li, Chaolong, Zhixun Xia, Likun Ma, Xiang Zhao i Binbin Chen. "Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity". Energies 12, nr 7 (31.03.2019): 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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Athithan, A. Antony, S. Jeyakumar, Norbert Sczygiol, Mariusz Urbanski i A. Hariharasudan. "The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor". Energies 14, nr 4 (5.02.2021): 831. http://dx.doi.org/10.3390/en14040831.

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This paper focuses on the influence of ramp locations upstream of a strut-based scramjet combustor under reacting flow conditions that are numerically investigated. In contrast, a computational study is adopted using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport (SST) k-ω turbulence model. The numerical results of the Deutsches Zentrum für Luft- und Raumfahrt or German Aerospace Centre (DLR) scramjet model are validated with the reported experimental values that show compliance within the range, indicating that the adopted simulation method can be extended for other investigations as well. The performance of the ramps in the strut-based scramjet combustor is analyzed based on parameters such as wall pressures, combustion efficiency and total pressure loss at various axial locations of the combustor. From the numerical shadowgraph, more shock interactions are observed upstream of the strut injection region for the ramp cases, which decelerates the flow downstream, and additional shock reflections with less intensity are also noticed when compared with the DLR scramjet model. The shock reflection due to the ramps enhances the hydrogen distribution in the spatial direction. The ignition delay is noticed for ramp combustors due to the deceleration of flow compared to the baseline strut only scramjet combustor. However, a higher flame temperature is observed with the ramp combustor. Because more shock interactions arise from the ramps, a marginal increase in the total pressure loss is observed for ramp combustors when compared to the baseline model.

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Ouyang, Hao, Weidong Liu i Mingbo Sun. "Investigations on the Influence of the In-Stream Pylon and Strut on the Performance of a Scramjet Combustor". Scientific World Journal 2014 (2014): 1–10. http://dx.doi.org/10.1155/2014/309387.

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The influence of the in-stream pylon and strut on the performance of scramjet combustor was experimentally and numerically investigated. The experiments were conducted with a direct-connect supersonic model combustor equipped with multiple cavities. The entrance parameter of combustor corresponds to scramjet flight Mach number 4.0 with a total temperature of 947 K. The research results show that, compared with the scramjet combustor without pylon and strut, the wall pressure and the thrust of the scramjet increase due to the improvement of mixing and combustion effect due to the pylon and strut. The total pressure loss caused by the strut is considerable whereas pylon influence is slight.

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Yang, Pengnian, Zhixun Xia, Likun Ma, BinBin Chen, Yunchao Feng, Chaolong Li i Libei Zhao. "Influence of the Multicavity Shape on the Solid Scramjet". International Journal of Aerospace Engineering 2021 (26.10.2021): 1–14. http://dx.doi.org/10.1155/2021/9718537.

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In this paper, a modular solid scramjet combustor with multicavity was proposed. The influence of multicavity shape on the performance of solid scramjet was investigated by the direct-connected tests. The experiments simulated a flight Mach 5.5 at 25 km. The boron-based fuel-rich propellant was used. The microstructure of combustion products was analyzed by SEM. The experimental results show that the fuel-rich mixture produced by the gas generator would ignite rapidly in the solid scramjet combustor. The combustion process showed a typical characteristic of establishment-development-maintenance-attenuation. Compared to the flame-holding cavity, the other shapes of cavities, e.g., narrow and lobe, can improve mixing and combustion. In our experiment, the combustion efficiency increased from 0.41 to 0.48, and the total pressure recovery was 0.36. In summary, the proposed solid scramjet combustor can effectively solve the ignition delay problem of the fuel-rich mixture, and the narrow/lobe cavity shows the ability to improve the mixing and combustion of the fuel-rich mixture.

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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, nr 6 (18.12.2019): 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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Lee, Jae-Hyuk, Eun-Sung Lee, Hyung-Seok Han, Min-Su Kim i Jeong-Yeol Choi. "A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition". Aerospace 10, nr 5 (28.04.2023): 415. http://dx.doi.org/10.3390/aerospace10050415.

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Vitiation air heater (VAH) combustion characteristics for a direct-connect scramjet combustor (DCSC) were experimentally studied. The VAH consists of a head, modular chamber, and circular-to-rectangular shape transition (CRST) nozzle. The CRST nozzle transforms the circular cross-sectioned rocket-type VAH into a rectangular cross-sectioned scramjet combustor. The CRST nozzle exit Mach numbers at the top, middle, and bottom were measured using a tungsten wedge. The oblique shock formed by the wedge was captured using Schlieren visualization and recorded with a high-speed camera. The θ-β-M relation showed that the exit Mach number was 2.04 ± 0.04 with a chamber pressure of 1.685 ± 0.07 MPa. With the VAH design point verified, preliminary scramjet combustor ignition tests were conducted. As the fuel was not auto-ignited by the vitiated air, the forced ignition method, in which VAH ignition flame ignites the scramjet fuel, was used. The Schlieren images showed that a cavity shear layer combustion mode was formed and also showed that the forced ignition method could be used as a reference model for the ignitor-ignition method.

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Chen, Hao, Mingming Guo, Ye Tian, Jialing Le, Hua Zhang i Fuyu Zhong. "Intelligent reconstruction of the flow field in a supersonic combustor based on deep learning". Physics of Fluids 34, nr 3 (marzec 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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Yang, Pengnian, Zhixun Xia, Likun Ma, Binbin Chen, Yunchao Feng, Chaolong Li i Libei Zhao. "Direct-Connect Test of Solid Scramjet with Symmetrical Structure". Energies 14, nr 17 (6.09.2021): 5589. http://dx.doi.org/10.3390/en14175589.

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The solid scramjet has become one of the most promising engine types. In this paper, we report the first direct-connect test of a solid scramjet with symmetrical structure, carried out using boron-based fuel-rich solid propellant as fuel. During the test, which simulated a flight environment at Mach 5.6 and 25 km, the performance of the solid scramjet was obtained by measuring the pressure, thrust, and mass flow. The results show that, due to the change in the combustion area of the propellant and the deposition of the throat in the gas generator during the test, the equivalence ratio gradually increased from 0.54 to 0.63. In a solid scramjet, it is possible to obtain a symmetrical distribution of the flow field within the combustor. Moreover, in a multi-cavity combustor, the combustion state expands from the cavity to the center of the flow channel. The performance of the solid scramjet increased during the test, reaching a combustion efficiency of about 42%, a total pressure recovery coefficient of 0.35, and a thrust gain specific impulse of about 418 s. The solid scramjet with symmetrical structure is feasible. The cavity configuration adopted in this paper can reduce the ignition delay time of fuel-rich gas and improve the combustion efficiency of gas-phase combustible components. The shock trains in the isolator are conducive to the recovery of the total pressure. The performance of the solid scramjet is limited by the low combustion efficiency of the particles.

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Zhao, Zhelong, i 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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Rozprawy doktorskie na temat "Scramjet combustor"

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Rowan, Scott A. "Viscous drag reduction in a scramjet combustor /". St. Lucia, Qld, 2003. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe17438.pdf.

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Stouffer, Scott David. "The effect of flow structure on the combustion and heat transfer in a scramjet combustor". Diss., Virginia Tech, 1995. http://hdl.handle.net/10919/39116.

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Mundis, Nathan L. "Magnetohydrodynamic power generation in a scramjet using a post combustor generator". Diss., Rolla, Mo. : University of Missouri-Rolla, 2007. http://scholarsmine.umr.edu/thesis/pdf/Mundis_09007dcc8043ee98.pdf.

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Thesis (M.S.)--University of Missouri--Rolla, 2007.
Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed March 25, 2008) Includes bibliographical references (p. 95-97).

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Corbin, Christopher Ryan. "Design and Analysis of a Mach 3 Dual Mode Scramjet Combustor". Wright State University / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=wright1208370076.

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Milligan, Ryan Timothy. "DUAL MODE SCRAMJET: A COMPUTATIONAL INVESTIGATION ON COMBUSTOR DESIGN AND OPERATION". Wright State University / OhioLINK, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=wright1251725076.

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Malo-Molina, Faure Joel. "Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture". Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/33906.

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To advance the design of hypersonic vehicles, high-fidelity multi-physics CFD is used to characterize 3-D scramjet flow-fields in two novel streamline traced configurations. The two inlets, Jaws and Scoop, are analyzed and compared to a traditional rectangular inlet used as a baseline for on/off-design conditions. The flight trajectory conditions selected are Mach 6 and a dynamic pressure of 1,500 psf (71.82 kPa). Analysis of these hypersonic inlets is performed to investigate distortion effects downstream with multiple single cavity combustors acting as flame holders, and several fuel injection strategies. The best integrated scramjet inlet/combustor design is identified. The flow physics is investigated and the integrated performance impact of the two innovative scramjet inlet designs is quantified. Frozen and finite rate chemistry is simulated with 13 gaseous species and 20 reactions for an Ethylene/air finite-rate chemical model. In addition, URANS and LES modeling are compared to explore overall flow structure and to contrast individual numerical methods. The flow distortion in Jaws and Scoop is similar to some of the distortion in the traditional rectangular inlet, despite design differences. The baseline and Jaws performance attributes are stronger than Scoop, but Jaws accomplishes this while eradicating the cowl lip interaction, and lessening the total drag and spillage penalties. The innovative inlets work best on-design, whereas for off-design, the traditional inlet is best. Early pressure losses and flow distortions in the isolator aid the mixing of air and fuel, and improve the overall efficiency of the system. Although the trends observed with and without chemical reactions are similar, the former yields roughly 10% higher mixing efficiency and upstream reactions are present. These show a significant impact on downstream development. Unsteadiness in the combustor increases the mixing efficiency, varying the flame anchoring and combustion pressure effects upstream of the step.

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Griffiths, Alan David, i alan griffiths@anu edu au. "Development and demonstration of a diode laser sensor for a scramjet combustor". The Australian National University. Faculty of Science, 2005. http://thesis.anu.edu.au./public/adt-ANU20051114.132736.

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Hypersonic vehicles, based on scramjet engines, have the potential to deliver inexpensive access to space when compared with rocket propulsion. The technology, however, is in its infancy and there is still much to be learned from fundamental studies.¶ Flows that represent the conditions inside a scramjet engine can be generated in ground tests using a free-piston shock tunnel and a combustor model. These facilities provide a convenient location for fundamental studies and principles learned during ground tests can be applied to the design of a full-scale vehicle.¶ A wide range of diagnostics have been used for studying scramjet flows, including surface measurements and optical visualisation techniques.¶ The aim of this work is to test the effectiveness of tunable diode laser absorption spectroscopy (TDLAS) as a scramjet diagnostic.¶ TDLAS utilises the spectrally narrow emission from a diode laser to probe individual absorption lines of a target species. By varying the diode laser injection current, the laser emission wavelength can be scanned to rapidly obtain a profile of the spectral line. TDLAS has been used previously for gas-dynamic sensing applications and, in the configuration used in this work, is sensitive to temperature and water vapour concentration.¶ The design of the sensor was guided by previous work. It incorporated aspects of designs that were considered to be well suited to the present application. Aspects of the design which were guided by the literature included the laser emission wavelength, the use of fibre optics and the detector used. The laser emission wavelength was near 1390 nm to coincide with relatively strong water vapour transitions. This wavelength allowed the use of telecommunications optical fibre and components for light delivery. Detection used a dual-beam, noise cancelling detector.¶ The sensor was validated before deployment in a low-pressure test cell and a hydrogenair flame. Temperature and water concentration measurements were verified to within 5% up to 1550 K. Verification accuracy was limited by non-uniformity along the beam path during flame measurements.¶ Measurements were made in a scramjet combustor operating in a flow generated by the T3 shock tunnel at the Australian National University. Within the scramjet combustor, hydrogen was injected into a flame-holding cavity and the sensor was operated downstream in the expanded, supersonic, post-combustion flow. The sensor was operated at a maximum repetition rate of 20 kHz and could resolve variation in temperature and water concentration over the 3ms running time of the facility.¶ Results were repeatable and the measurement uncertainty was smaller than the turbulent fluctuations in the flow. The scramjet was operated at two fuel-lean equivalence ratios and the sensor was able to show differences between the two operating conditions. In addition, vertical traversal of the sensor revealed variation in flow conditions across the scramjet duct.¶ The effectiveness of the diagnostic was tested by comparing results with those from other measurement techniques, in particular pressure and OH fluorescence measurements, as well as comparison with computational simulation.¶ Combustion was noted at both of the tested operating conditions in data from all three measurement techniques.¶ Computation simulation of the scramjet flow significantly under-predicted the water vapour concentration. The discrepancy between experiments and simulation was not apparent in either the pressure measurements or the OH fluorescence, but was clear in the diode laser results.¶ The diode laser sensor, therefore, was able to produce quantitative results which were useful for comparison with a CFD model of the scramjet and were complimentary to information provided by other diagnostics.

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Griffiths, Alan David. "Development and demonstration of a diode laser sensor for a scramjet combustor /". View thesis entry in Australian Digital Theses, 2005. http://thesis.anu.edu.au/public/adt-ANU20051114.132736/index.html.

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Etheridge, Steven J. "Effect of Flow Distortion on Fuel Mixing and Combustion in an Upstream-Fueled Cavity Flameholder for a Supersonic Combustor". University of Cincinnati / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1353100774.

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McDaniel, Keith Scott. "Three Dimensional Simulation of Time-Dependent Scramjet Isolator /Combustor Flowfields Implemented on Parallel Architectures". NCSU, 2001. http://www.lib.ncsu.edu/theses/available/etd-20001228-204538.

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McDaniel, Keith S. Three Dimensional Simulation of Time-DependentScramjet Isolator / Combustor Flowfields Implemented onParallel Architectures, ( Under the directions of Dr. J. R. Edwards). The development of a parallel Navier-Stokes solver for computing time-dependent,three-dimensional reacting flowfields within scramjet (supersonic combusting ramjet)engines is presented in this work. The algorithm combines low-diffusion upwinding methods, timeaccurate implicit integration techniques, and domain decomposition strategies to yield an effectiveapproach for large-scale simulations. The algorithm is mapped to a distributed memoryIBM SP-2 architecture and a shared memory Compaq ES-40 architecture using the MPI-1 message-passingstandard. Two and three-dimensional simulations of time-dependent hydrogen fuel injection into a modelscramjet isolator / combustor configuration at two equivalence ratios are performed. Thesesimulations are used to gain knowledge of engine operability, inlet performance, isolatorperformance, fuel air mixing, flame holding, mode transition, and engine unstart.Results for an injection at a ratio of 0.29 show qualitative agreement withexperiment for the two-dimensional case, but revealed a slow progression towardengine unstart for the three-dimensional case. Injection at an equivalence ratio of 0.61resulted in engine unstart for both two-dimensional and three-dimensional cases.Engine unstart for the three-dimensional case occurs as a response to the formation and growthof large pockets of reversed flow along the combustor side wall. These structuresdevelop at an incipient pressure above 154 kPa and result in significant blockage of the core flow,additional compression, and chemical reaction within the boundary layer. All of these factors promotea much more rapid unstart as compared with the two-dimensional case.

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Książki na temat "Scramjet combustor"

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Center, Langley Research, red. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

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Center, Langley Research, red. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

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Jacobs, P. A. Preliminary calibration of a generic scramjet combustor. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1991.

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Jacobs, P. A. Flow establishment in a generic scramjet combustor. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1990.

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A, Jacobs Peter, i Langley Research Center, red. Flow establishment in a generic scramjet combustor. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

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A, Jacobs Peter, i Langley Research Center, red. Preliminary calibration of a generic scramjet combustor. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, [1991], 1991.

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Dash, Sanford M. Computational models for the analysis/design of hypersonic scramjet nozzles - Part 1: Combustor and nozzle models. New York: AIAA, 1986.

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1934-, Hoffman Joe D., i United States. National Aeronautics and Space Administration., red. Hypervelocity scramjet combustor-nozzle, analysis and design: Final report for NASA grant NAG-1-854 for the period 15 February 1988 to 31 December 1991. [Washington, DC: National Aeronautics and Space Administration, 1992.

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T, Curran E., i Murthy S. N. B, red. Scramjet propulsion. Reston, Va: American Institute of Aeronautics and Astronautics, 2000.

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Schetz, Joseph A. Studies in scramjet flowfields. [S.l.]: American Institute of Aeronautics and Astronautics, 1987.

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Części książek na temat "Scramjet combustor"

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Morgan, R. G., i F. Zander. "Radiatively cooled scramjet combustor". W Shock Waves, 1135–40. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85181-3_55.

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Swithenbank, J., B. C. R. Ewan, S. B. Chin, L. Shao i Y. Wu. "Mixing Power Concepts in Scramjet Combustor Design". W ICASE/NASA LaRC Series, 531–84. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2884-4_26.

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Zheng, Z. H., i J. L. Le. "Massively parallel computation of three-dimensional scramjet combustor". W Shock Waves, 897–902. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-27009-6_136.

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Drummond, J. P. "Discussion on Mixing Power Concepts in Scramjet Combustor Design". W ICASE/NASA LaRC Series, 585–87. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2884-4_27.

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Chevalier, Alain, Marc Bouchez, Dominique Bouchaud, Isabelle Auneau i Nicole Montmayeur. "An industrial point of view on scramjet combustor design". W Fluid Mechanics and Its Applications, 163–72. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5432-1_13.

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Du, Jinfeng, Chun Guan, Yuchun Chen, Haomin Li i Zhihua Wang. "Analysis of Overall Performance of Multi-stage Combustor Scramjet Engine". W Lecture Notes in Electrical Engineering, 1835–46. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_147.

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Liang, J. H., i C. Y. Wang. "Numerical Simulations of Tranverse Jet Reacting Flows in Scramjet Combustor". W Computational Mechanics ’95, 923–28. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-79654-8_150.

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Naveen, K., Mukesh Kapoor, M. S. Prasad i S. Arunvinthan. "Design and Analysis of a Novel Cloverleaf Combustor for Scramjet Engine". W Lecture Notes in Mechanical Engineering, 51–63. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6469-3_5.

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Purwar, Anupam. "Thermo-Structural Design of Strut Based Flame Holder for Scramjet Combustor". W Research into Design for Communities, Volume 1, 105–15. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-3518-0_10.

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Shin, Junsu, i Hong-Gye Sung. "Comparison of Hybrid RANS/LES Methods for Supersonic Combustion in a Model Scramjet Combustor". W Progress in Hybrid RANS-LES Modelling, 233–42. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-70031-1_19.

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Streszczenia konferencji na temat "Scramjet combustor"

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Zander, Fabian, i Richard Morgan. "Composite Scramjet Combustor". W 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-7354.

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Chen, Yen-Sen, Y. Y. Lian, Bill Wu i J. S. Wu. "Scramjet Combustor Computational Modeling". W 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-5386.

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Mathur, T., K. C. Lin, P. Kennedy, M. Gruber, J. Donbar, T. Jackson i F. Billig. "Liquid JP-7 combustion in a scramjet combustor". W 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-3581.

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Bouchez, Marc, Nicole Montmayeur, Christophe Leboucher i Michel Souchet. "Scramjet combustor design in France". W International Aerospace Planes and Hypersonics Technologies. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-6094.

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KAY, I., W. PESCHKE i R. GUILE. "Hydrocarbon-fueled scramjet combustor investigation". W 26th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2337.

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Abdel-Salam, Tarek, Surundra Tiwari i Tajeldin Mohieldin. "Study of Supersonic Combustion Characteristics in a Scramjet Combustor". W 16th AIAA Computational Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-3550.

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Abdel-Salam, T., S. Tiwari i T. Mohieldin. "Dual-mode flowfield in scramjet combustor". W 35th AIAA Thermophysics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-2966.

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Ingenito, Antonella, Claudio Bruno i Donato Cecere. "LES of the Hyshot Scramjet Combustor". W 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-758.

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Ladeinde, Foluso. "Pressure Effects in a Scramjet Combustor". W AIAA Propulsion and Energy 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-3534.

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Uhrig, Gilles, i Jean Michel Larrieu. "Towards An All-Composite SCRAMJET Combustor". W 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-3883.

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Raporty organizacyjne na temat "Scramjet combustor"

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Brown, Michael S., Skip Williams, Chadwick D. Lindstrom i Dominic L. Barone. Progress in Applying Tunable Diode Laser Absorption Spectroscopy to Scramjet Isolators and Combustors. Fort Belvoir, VA: Defense Technical Information Center, maj 2010. http://dx.doi.org/10.21236/ada522512.

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Clemens, Noel T. Experimental/Computational Studies of Combined-Cycle Propulsion: Physics and Transient Phenomena in Inlets and Scramjet Combustors. Fort Belvoir, VA: Defense Technical Information Center, maj 2010. http://dx.doi.org/10.21236/ada525600.

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Boles, John, i Ryan Milligan. Technology for Sustained Supersonic Combustion Task Order 0006: Scramjet Research with Flight-Like Inflow Conditions. Fort Belvoir, VA: Defense Technical Information Center, styczeń 2013. http://dx.doi.org/10.21236/ada586382.

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