Relevant bibliographies by topics / Supersonic combustion

Academic literature on the topic 'Supersonic combustion'

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Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Supersonic combustion"

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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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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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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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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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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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Dissertations / Theses on the topic "Supersonic combustion"

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Lou, Zhipeng. "Improved Flamelet Modeling of Supersonic Combustion." Thesis, State University of New York at Stony Brook, 2017. http://pqdtopen.proquest.com/#viewpdf?dispub=10280296.

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A computational fluid dynamics (CFD)-based study using large-eddy simulation (LES) and the flamelet-progress variable (FPV) approach for turbulence-combustion interaction has been undertaken to investigate the combustion that takes place under supersonic flow conditions. The target application is the propulsive system associated with dual-mode scramjet, which has been recognized as the most promising air-breathing system for hypersonic flight. In addition to the standard practice of using mixture fraction and its dissipation rate as independent variables of the look-up table in the flamelet procedure for non-premixed flames, pressure has been added to enable the inclusion of its effects on chemical reactions under high speed conditions. An improved method of generating the flamelet library that allows new interpolations based on the three branches of the reaction curve (S-Curve) in non-premixed combustion has been proposed during the course of the present work. Solutions of supersonic combustion in three different configurations have been used to assess the accuracy of the various proposed improvements and investigate fundamental physics of dual-mode scramjets.

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Luo, Wenlei. "Large Eddy Simulation of turbulent supersonic combustion and characteristics of supersonic flames." Thesis, University of Leeds, 2014. http://etheses.whiterose.ac.uk/7641/.

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In this thesis we investigate the supersonic combustion in scramjet combustors with strut and cavity flame holders through the Reynolds-Averaged Navier–Stokes (RANS) and Large Eddy Simulation (LES) strategies. Firstly, the Unsteady Flamelet/Progress Variable (UFPV) model for turbulent combustion in low-speed flows is introduced and extended to supersonic flows and a new strategy is developed to create probability density function look-up tables for the UFPV model. Secondly, the RANS modelling is employed to a strut-based scramjet combustor using the flamelet and UFPV models and the latter shows a better performance. Subsequently, the LES modelling is performed with the UFPV model and the UFPV model gives good predictions on comparing the numerical results to the experimental data. Thirdly, the LES modelling is employed to a cavity-based scramjet combustor. The results obtained indicate that the local extinction and autoignition events are very common phenomena in the supersonic flame and the UFPV model is able of predicting these events with reasonable accuracy. Further, an activation-energy-asymptotic-based Damköhler number concept is a valuable metric to identify flame weakening and extinction in supersonic flames. Together with the OH radicals, the distribution of the HO2 radicals can assist in identifying the autoignition events in the supersonic flame. Finally, analysing the flameholding mechanisms of the cavity, it is found that the cavity provides a stable ignition source to the fluid. Further, the combustion in the cavity is dominated by flame propagation. However, on the outer interface of the air and hydrogen streams, the combustion is mainly dominated by autoignition. Both autoignition and flame propagation contribute to the combustion in the mixing layer. Also the combustion in the cavity mixing layer has effects on the induction reactions in the wake of the hydrogen jet and reduces the induction time of the autoignition.
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Del, Rio Francesco. "Distortion mechanism in supersonic combustion ramjet engines." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2018.

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Il mio lavoro di tesi è stato incentrato sulla progettazione e la realizzazione di un prototipo di isolator (componente necessaria per il funzionamento dei motori scramjet, utilizzati per velivoli aerospaziali ipersonici) in grado di generare tramite un opportuno dispositivo il meccanismo fluidodinamico che in letteratura viene definito "distortion mechanism". Tramite la tecnica fotografica denominata Schlieren, la quale sfrutta i gradienti di densità all’interno del fluido in esame, ho fotografato le onde di shock generate dal meccanismo suddetto, rendendo così possibile la comprensione del comportamento di queste onde e delle loro interazioni con il boundary layer, con le pareti, ma soprattutto dell’influenza che esse hanno sulle prestazioni di un eventuale propulsore. Da qui è partita una analisi sulle interazioni shock-shock e shock-boundary layer: quest’ultimo fenomeno è di grande interesse in quanto si è notato che non solo viene attivato un meccanismo di distorsione dell’onda stessa, ma che addirittura si manifesta la separazione dello strato limite, generando complessi fenomeni fluidodinamici e termodinamici i quali decrementano l’efficienza non solo dell’isolator bensì del motore stesso.È stato infine previsto come le onde di shock che si propagavano nell’isolator avrebbero potuto affliggere il mixing e la combustione nell’ultimo stage del prototipo, evidenziando le conseguenze che avrebbero generato sull’efficienza generale del ciclo termodinamico. Per concludere il mio lavoro di tesi ho sviluppato alcuni tools in ambiente Matlab utili per poter calcolare le proprietà termodinamiche di un fluido che entra in un inlet di uno scramjet. Per motivi di complessità del problema e per la non assoluta certezza dei fenomeni fluidodinamici e termodinamici che realmente accadono in questi motori (in 3-D), le equazioni utilizzate all’interno del codice sono utili per un’analisi di un fluido quasi monodimensionale.
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Do, Hyungrok. "Plasma-assisted combustion in a supersonic flow /." May be available electronically:, 2009. http://proquest.umi.com/login?COPT=REJTPTU1MTUmSU5UPTAmVkVSPTI=&clientId=12498.

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Picciani, Mark. "Supersonic combustion modelling using the conditional moment closure approach." Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/9309.

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This work presents a novel algorithm for supersonic combustion modelling. The method involved coupling the Conditional Moment Closure (CMC) model to a fully compressible, shock capturing, high-order flow solver, with the intent of modelling a reacting hydrogen-air, supersonic jet. Firstly, a frozen chemistry case was analysed to validate the implementation of the algorithm and the ability for CMC to operate at its frozen limit. Accurate capturing of mixing is crucial as the mixing and combustion time scales for supersonic flows are on the order of milliseconds. The results of this simulation were promising even with an unexplainable excess velocity decay of the jet core. Hydrogen mass fractions however, showed fair agreement to the experiment. The method was then applied to the supersonic reacting case of ONERA. The results showed the method was able to successfully capture chemical non-equilibrium effects, as the lift-off height and autoignition time were reasonably captured. Distributions of reactive scalars were difficult to asses as experimental data was deemed to be very inaccurate. As a consequence, published numerical results for the same test case were utilised to aid in analysing the results of the presented simulations. Due to the primary focus of the study being to assess non-equilibrium effects, the clustering of the computational grid lent itself to smeared and lower magnitude wall pressure distributions. Nevertheless, the wall pressure distributions showed good qualitative agreement to experiment. The primary conclusions from the study were that the CMC method is feasible to model supersonic combustion. However, a more detailed analysis of sub-models and closure assumptions must be conducted to assess the feasibility on a more fundamental level. Also, from the results of both the frozen chemistry and the reacting case, the effects of assuming constant species Lewis number was visible.
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Makowka, Konrad [Verfasser]. "Numerically Efficient Hybrid RANS/LES of Supersonic Combustion / Konrad Makowka." München : Verlag Dr. Hut, 2016. http://d-nb.info/1084385236/34.

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Ruan, Jiangheng Loïc. "Large eddy simulation of supersonic combustion in cavity-based scramjets." Thesis, Normandie, 2019. http://www.theses.fr/2019NORMIR14.

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Les dernières décennies ont été marquées par la course aux technologies hypersoniques. Voler à une vitesse hypersonique pourrait être possible avec les superstatoréacteurs. Mais le principal problème de ce moteur est le court temps de résidence du combustible dans la chambre de combustion, qui est de l'ordre de la milliseconde, rendant le mélange et la combustion difficile. L'ajout d'une cavité dans les superstatoréacteurs pourrait palier à ce problème grâce aux zones de recirculation de la cavité qui emprisonnent les gaz brulés, et permettent ainsi de rallumer continuellement le combustible. Grâce à l'essor de l'informatique, une simulation aux grandes échelles d'un telle configuration devient possible de nos jours. Les objectives de la thèse sont dans un premier temps d'évaluer la capacité d'une simulation aux grandes échelles à prédire des écoulements compressibles réactifs, et dans un second temps, de comprendre les phénomènes propres aux superstatoréacteurs à cavité
The last decades have been marked by great progress in hypersonic technologies. The scramjet seems to be able to cope with these hypersonic speeds even today. The main problem to overcome is the short residence time of the fuel in the combustion chamber. This time being of the order of a millisecond, mixing and combustion cannot operate efficiently making the flameholding a challenging task. The cavity-based scramjets have been considered as a promising solution because the recirculation of the combustion gases inside of it makes it possible to ignite the reaction mixture continuously. Due to the increase in high performance computing, the use of Large-Eddy Simulation for supersonic combustion is now becoming relevant. The objectives of the present study are twofold: first, assess the ability of the LES technique to predict compressible multi-species reacting flows; and second, provide some fundamental aspects of cavity-based scramjet
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Tedder, Sarah Augusta. "Advancements in dual-pump broadband CARS for supersonic combustion measurements." W&M ScholarWorks, 2010. https://scholarworks.wm.edu/etd/1539623572.

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Space- and time-resolved measurements of temperature and species mole fractions of nitrogen, oxygen, and hydrogen were obtained with a dual-pump coherent anti-Stokes Raman spectroscopy (CARS) system in hydrogen-fueled supersonic combustion free jet flows. These measurements were taken to provide time-resolved fluid properties of turbulent supersonic combustion for use in the creation and verification of computational fluid dynamic (CFD) models. CFD models of turbulent supersonic combustion flow currently facilitate the design of air- breathing supersonic combustion ramjet (scramjet) engines. Measurements were made in supersonic axi-symmetric free jets of two scales. First, the measurement system was tested in a laboratory environment using a laboratory-scale burner (∼10 mm at nozzle exit). The flow structures of the laboratory-burner were too small to be resolved with the CARS measurements volume, but the composition and temperature of the jet allowed the performance of the system to be evaluated. Subsequently, the system was tested in a burner that was approximately 6 times larger, whose length scales are better resolved by the CARS measurement volume. During both these measurements, weaknesses of the CARS system, such as sensitivity to vibrations and beam steering and inability to measure temperature or species concentrations in hydrogen fuel injection regions were identified. Solutions were then implemented in improved CARS systems. One of these improved systems is a dual-pump broadband CARS technique called, Width Increased Dual-pump Enhanced CARS (WIDECARS). The two lowest rotational energy levels of hydrogen detectable by WIDECARS are H2 S(3) and H2 S(4). The detection of these lines gives the system the capability to measure temperature and species concentrations in regions of the flow containing pure hydrogen fuel at room temperature. WIDECARS is also designed for measurements of all the major species (except water) in supersonic combustion flows fueled with hydrogen and hydrogen/ethylene mixtures (N2, O 2, H2, C2H4, CO, and CO2). This instrument can characterize supersonic combustion fueled with surrogate fuel mixtures of hydrogen and ethylene. This information can lead to a better understanding of the chemistry and performance of supersonic combustion fueled with cracked jet propulsion (JP)-type fuel.
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Sexton, Scott Michael. "Progress Toward Analytic Predictions of Supersonic Hydrocarbon-Air Combustion| Computation of Ignition Times and Supersonic Mixing Layers." Thesis, University of California, San Diego, 2018. http://pqdtopen.proquest.com/#viewpdf?dispub=10687717.

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Combustion in scramjet engines is faced with the limitation of brief residence time in the combustion chamber, requiring fuel and preheated air streams to mix and ignite in a matter of milliseconds. Accurate predictions of autoignition times are needed to design reliable supersonic combustion chambers. Most efforts in estimating non-premixed autoignition times have been devoted to hydrogen-air mixtures. The present work addresses hydrocarbon-air combustion, which is of interest for future scramjet engines.

Computation of ignition in supersonic flows requires adequate characterization of ignition chemistry and description of the flow, both of which are derived in this work. In particular, we have shown that activation energy asymptotics combined with a previously derived reduced chemical kinetic mechanism provides analytic predictions of autoignition times in homogeneous systems. Results are compared with data from shock tube experiments, and previous expressions which employ a fuel depletion criterion.

Ignition in scramjet engines has a strong dependence on temperature, which is found by perturbing the chemically frozen mixing layer solution. The frozen solution is obtained here, accounting for effects of viscous dissipation between the fuel and air streams. We investigate variations of thermodynamic and transport properties, and compare these to simplified mixing layers which neglect these variations. Numerically integrating the mixing layer problem reveals a nonmonotonic temperature profile, with a peak occurring inside the shear layer for sufficiently high Mach numbers.

These results will be essential in computation of ignition distances in supersonic combustion chambers.

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Billingsley, Matthew C. "Plasma Torch Atomizer-Igniter for Supersonic Combustion of Liquid Hydrocarbon Fuels." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/36331.

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To realize supersonic combustion of hydrocarbons, an effective atomizer-igniter combination with the capabilities of fuel preheating, atomization, penetration, mixing, ignition and flameholding is desired. An original design concept incorporating these capabilities was built and tested at Virginia Tech, and was found to provide good penetration, effective atomization, and robust ignition and flameholding. Quiescent testing with kerosene and JP-7 provided initial performance data. The atomizer-injector design was then modified for insertion into a supersonic wind tunnel, and tested with kerosene in an unheated Mach 2.4 flow with typical freestream conditions of To = 280 K and Po = 360 kPa. Water injection was utilized in both cases for comparison and to analyze atomization behavior. In the quiescent environment, the regeneratively cooled plasma torch igniter was found to significantly increase electrode life while heating, atomizing, and igniting the liquid fuel. Jet breakup length was measured and characterized, and mean droplet size was estimated using an existing correlation. Several qualitative observations regarding quiescent combustion were made, including torch power effects and the process of flame formation. In the supersonic environment, the effect of fuel injection direction was analyzed. Best results were obtained when fuel was injected with a velocity component opposite to the direction of main tunnel flow. Repeatable ignition occurred in the supersonic boundary layer at the fuel stagnation location near the plasma torch plume. Direct, filtered, shadowgraph, and schlieren photographs, temperature measurements, and visible emission spectroscopy provided evidence of combustion and the details of the flame structure. The new atomizer-igniter design provided robust and reliable ignition and flameholding of liquid hydrocarbon fuels in an unheated supersonic flow at M=2.4, with no ramp, step, or other physical penetration into the flowpath.
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Books on the topic "Supersonic combustion"

1

Sun, Mingbo, Hongbo Wang, Zun Cai, and Jiajian Zhu. Unsteady Supersonic Combustion. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3595-6.

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Timnat, Y. M. Diagnostics in supersonic combustion. New York: AIAA, 1987.

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Gutmark, E. Noncircular jet dynamics in supersonic combustion. New York: American Institute of Aeronautics and Astronautics, 1987.

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Don, Hoying, and Universities Space Research Association, eds. Supersonic combustion engine testbed: Heat lightning. Houston, Tex: Universities Space Research Association, 1990.

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Northam, G. Burton. Supersonic combustion ramjet research at Langley. New York: AIAA, 1986.

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McDaniel, James C. A laser-induced-fluorescence visualization study of transverse, sonic fuel injection in a nonreacting supersonic combustor. New York: AIAA, 1986.

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Marble, Frank E. Progress toward shock enhancement of supersonic combustion processes. New York: AIAA, 1987.

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Yip, T. Gary. Ignition delay and characteristic reaction length in shock induced supersonic combustion. New York: AIAA, 1989.

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Rubins, Philip M. A review of supersonic combustion research at AEDC with hypersonic applications. Washington, D. C: American Institute of Aeronautics and Astronautics, 1993.

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Drummond, J. Philip. Mixing enhancement in a supersonic combustor. Washington, D. C: American Institute of Aeronautics and Astronautics, 1989.

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Book chapters on the topic "Supersonic combustion"

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Sun, Mingbo, Hongbo Wang, Zun Cai, and Jiajian Zhu. "Introduction." In Unsteady Supersonic Combustion, 1–55. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3595-6_1.

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Sun, Mingbo, Hongbo Wang, Zun Cai, and Jiajian Zhu. "Acoustic Oscillation in Supersonic Combustor." In Unsteady Supersonic Combustion, 57–112. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3595-6_2.

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Sun, Mingbo, Hongbo Wang, Zun Cai, and Jiajian Zhu. "Flow Dominating Instability in Supersonic Flows." In Unsteady Supersonic Combustion, 113–76. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3595-6_3.

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Sun, Mingbo, Hongbo Wang, Zun Cai, and Jiajian Zhu. "Cavity Ignition in Supersonic Flows." In Unsteady Supersonic Combustion, 177–239. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3595-6_4.

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Sun, Mingbo, Hongbo Wang, Zun Cai, and Jiajian Zhu. "Flame Flashback in Supersonic Flows." In Unsteady Supersonic Combustion, 241–305. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3595-6_5.

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Sun, Mingbo, Hongbo Wang, Zun Cai, and Jiajian Zhu. "Flame Behaviors Near Blowoff in Supersonic Flows." In Unsteady Supersonic Combustion, 307–45. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3595-6_6.

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Kumar, A., and M. Y. Hussaini. "Discussion on Supersonic Combustion." In ICASE/NASA LaRC Series, 16–20. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2884-4_2.

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Libby, Paul A. "Observations Concerning Supersonic Combustion." In Fluid Mechanics and Its Applications, 1–11. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5432-1_1.

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Ramanujachari, V. "Supersonic Combustion Ramjet Technology." In Advances in Combustion Technology, 183–207. Boca Raton: CRC Press, 2022. http://dx.doi.org/10.1201/9781003049005-8.

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Ingenito, Antonella. "Design of Supersonic/Hypersonic Vehicles." In Subsonic Combustion Ramjet Design, 9–17. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-66881-5_3.

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Conference papers on the topic "Supersonic combustion"

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Fureby, Christer. "LES for Supersonic Combustion." In 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-5979.

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TIMNAT, Y. "Diagnostics in supersonic combustion." In 23rd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1787.

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BILLIG, F. "Research on supersonic combustion." In 30th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-1.

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Gamba, Mirko, Victor Miller, Godfrey Mungal, and Ronald Hanson. "Combustion characteristics of an inlet/supersonic combustor model." In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-612.

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Mathur, A., M. Goldfeld, A. Mishunin, and A. Starov. "Investigation of Hydrocarbon Fuels Combustion in Supersonic Combustor." In 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-3487.

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Tishkoff, Julian, J. Drummond, T. Edwards, A. Nejad, Julian Tishkoff, J. Drummond, T. Edwards, and A. Nejad. "Future directions of supersonic combustion research - Air Force/NASA workshop on supersonic combustion." In 35th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-1017.

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Cymbalist, Niccolo, and Paul Dimotakis. "On autoignition-dominated supersonic combustion." In 45th AIAA Fluid Dynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-2315.

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Ingenito, Antonella, Claudio Bruno, Eugenio Giacomazzi, and Johan Steelant. "Supersonic Combustion: Modelling and Simulations." In 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-8035.

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KRAUSS, ROLAND, R. WHITEHURST, III, JOHN ABITT, III, CORIN SEGAL, and JAMES MCDANIEL. "Initial supersonic combustion facility measurements." In 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2462.

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Schlussel, Ethan J., Dominic F. Gallegos, and Gregory Young. "Supersonic Combustion of Solid Fuels." In AIAA AVIATION 2023 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-4135.

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Reports on the topic "Supersonic combustion"

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Carter, Campbell D. Supersonic Combustion Ramjet Research. Fort Belvoir, VA: Defense Technical Information Center, August 2012. http://dx.doi.org/10.21236/ada563331.

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Bowman, C. T., R. K. Hanson, M. G. Mungal, and W. C. Reynolds. Turbulent Reacting Flows and Supersonic Combustion. Fort Belvoir, VA: Defense Technical Information Center, March 1992. http://dx.doi.org/10.21236/ada251065.

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Bowman, C. T., R. K. Hanson, M. G. Mungal, and W. C. Reynolds. Turbulent Reacting Flows and Supersonic Combustion. Fort Belvoir, VA: Defense Technical Information Center, March 1991. http://dx.doi.org/10.21236/ada236759.

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Bowman, C. T., R. K. Hanson, M. G. Mugal, and W. C. Reynolds. Turbulent Reacting Flows and Supersonic Combustion. Fort Belvoir, VA: Defense Technical Information Center, January 1990. http://dx.doi.org/10.21236/ada221793.

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Misra, Prabhakar. Laser Spectroscopy of Combustion Intermediates in a Supersonic Jet Expansion. Fort Belvoir, VA: Defense Technical Information Center, March 1994. http://dx.doi.org/10.21236/ada283201.

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Dimotakis, Paul E., and Anthony Leonard. Mixing, Chemical Reactions, and Combustion in Subsonic and Supersonic Turbulent Flows. Fort Belvoir, VA: Defense Technical Information Center, September 1998. http://dx.doi.org/10.21236/ada353373.

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Balepin, Vladimir. Supersonic Post-Combustion Inertial CO2 Extraction System Final Report. Office of Scientific and Technical Information (OSTI), April 2017. http://dx.doi.org/10.2172/1394653.

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Manke, Gerald C. The Measurement of Gain in a Supersonic, Combustion-Driven Generator for NCl(a1Delta). Fort Belvoir, VA: Defense Technical Information Center, February 2005. http://dx.doi.org/10.21236/ada430093.

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

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Ghenai, C., G. P. Philippidis, and C. X. Lin. Active Control Strategies to Optimize Supersonic Fuel-Air Mixing for Combustion Associated with Fully Modulated Transverse Jet in Cross Flow. Fort Belvoir, VA: Defense Technical Information Center, December 2005. http://dx.doi.org/10.21236/ada443378.

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