Relevant bibliographies by topics / Combustion

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Combustion'

Author: Grafiati
Published: 4 June 2021
Last updated: 16 November 2024

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Journal articles on the topic "Combustion"

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Ran, Jing Yu, Li Juan Liu, Chai Zuo Li, and Li Zhang. "Numerical Study on Optimum Designing of the Air Distribution Structure of a New Cyclone Combustor." Advanced Materials Research 347-353 (October 2011): 3005–14. http://dx.doi.org/10.4028/www.scientific.net/amr.347-353.3005.

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A new type of cyclone combustor is designed based on the traditional pulverized coal liquid slag combustor in this paper. According to the characteristics of swirl combustion and flow, numerical simulation of pulverized coal combustion in a new cyclone combustor has carried out using Realizable k-ε equation model with swirl modified to gas phase and stochastic trajectory model under Lagrange coordinate system to particle phase. Flows and combustion characteristics under different working conditions are mainly studied by changing the angles of primary and secondary air inlets, and then structural characteristics of the combustor are analyzed. Results show that structural characteristics of the primary and secondary air have great influence on internal flow and combustion characteristics of the combustor. When the pitch angle, the rotation angle of the secondary air and the expansion angle of the primary air respectively are 20°, 51° and 60°, the combustion efficiency of the combustor can reach up to 98.1% and it is conducive to high-temperature liquid slagging. It is also helpful to prevented pulverized coal depositing and accumulating near the wall and then plugging the combusting channel during the starting stage in low temperature region.
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Li, Shou-Zhe, Yu-Long Niu, Shu-Li Cao, Jiao Zhang, Jialiang Zhang, and Xuechen Li. "The effect of plasma discharge on methane diffusion combustion in air assisted by an atmospheric pressure microwave plasma torch." Journal of Physics D: Applied Physics 55, no. 23 (March 11, 2022): 235203. http://dx.doi.org/10.1088/1361-6463/ac50cb.

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Abstract An atmospheric pressure air microwave plasma torch is employed to assist methane diffusion combustions using a combination of a combustor and burner. Experimentally, the effect of the air microwave plasma on combustion is investigated with respect to the flame morphology and the variation of gas components in the exhaust with the fuel equivalence ratio φ or the methane flow rate by comparing plasma-assisted combustion (PAC) and natural combustion (NC) without plasma application. The combustion degree of CH4 in PACs is found to be much enhanced in rich fuel combustion than in NC in both types of burners, which is measured by Fourier transformation infrared spectrometer (FTIR). In PACs, with the use of an air microwave plasma torch, the radicals originating from excitation, ionization, and dissociation of N2 and O2 and the high gas temperature induced in the plasma discharge play an important role in assisting the combustion.
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Yang, Xiaojian, and Guoming G. Zhu. "A control-oriented hybrid combustion model of a homogeneous charge compression ignition capable spark ignition engine." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 226, no. 10 (May 31, 2012): 1380–95. http://dx.doi.org/10.1177/0954407012443334.

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To implement the homogeneous charge compression ignition combustion mode in a spark ignition engine, it is necessary to have smooth mode transition between the spark ignition and homogeneous charge compression ignition combustions. The spark ignition–homogeneous charge compression ignition hybrid combustion mode modeled in this paper describes the combustion mode that starts with the spark ignition combustion and ends with the homogeneous charge compression ignition combustion. The main motivation of studying the hybrid combustion mode is that the percentage of the homogeneous charge compression ignition combustion is a good parameter for combustion mode transition control when the hybrid combustion mode is used during the transition. This paper presents a control oriented model of the spark ignition–homogeneous charge compression ignition hybrid combustion mode, where the spark ignition combustion phase is modeled under the two-zone assumption and the homogeneous charge compression ignition combustion phase under the one-zone assumption. Note that the spark ignition and homogeneous charge compression ignition combustions are special cases in this combustion model. The developed model is capable of simulating engine combustion over the entire operating range, and it was implemented in a real-time hardware-in-the-loop simulation environment. The simulation results were compared with those of the corresponding GT-Power model, and good correlations were found for both spark ignition and homogeneous charge compression ignition combustions.
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Ozawa, Y., J. Hirano, M. Sato, M. Saiga, and S. Watanabe. "Test Results of Low NOx Catalytic Combustors for Gas Turbines." Journal of Engineering for Gas Turbines and Power 116, no. 3 (July 1, 1994): 511–16. http://dx.doi.org/10.1115/1.2906849.

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Catalytic combustion is an ultralow NOx combustion method, so it is expected that this method will be applied to a gas turbine combustor. However, it is difficult to develop a catalytic combustor because catalytic reliability at high temperature is still insufficient. To overcome this difficulty, we designed a catalytic combustor in which premixed combustion was combined. By this device, it is possible to obtain combustion gas at a combustion temperature of 1300°C while keeping the catalytic temperature below 1000°C. After performing preliminary tests using LPG, we designed two types of combustor for natural gas with a capacity equivalent to one combustor used in a 20 MW class multican-type gas turbine. Combustion tests were conducted at atmospheric pressure using natural gas. As a result, it was confirmed that a combustor in which catalytic combustor segments were arranged alternately with premixing nozzles could achieve low NOx and high combustion efficiency in the range from 1000°C to 1300°C of the combustor exit gas temperature.
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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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Kinoshita, Y., J. Kitajima, Y. Seki, and A. Tatara. "Experimental Studies on Methane-Fuel Laboratory Scale Ram Combustor." Journal of Engineering for Gas Turbines and Power 117, no. 3 (July 1, 1995): 394–400. http://dx.doi.org/10.1115/1.2814108.

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The laboratory scale ram combustor test program has been investigating fundamental combustion characteristics of a ram combustor, which operates from Mach 2.5 to 5 for the super/hypersonic transport propulsion system. In our previous study, combustion efficiency had been found poor, less than 70 percent, due to a low inlet air temperature and a high velocity at Mach 3 condition. To improve the low combustion efficiency, a fuel zoning combustion concept was investigated by using a subscale combustor model first. Combustion efficiency more than 90 percent was achieved and the concept was found very effective. Then a laboratory scale ram combustor was fabricated and combustion tests were carried out mainly at the simulated condition of Mach 5. A vitiation technique was used to simulate a high temperature of 1263 K. The test results indicate that ignition, flame stability, and combustion efficiency were not significant, but the NOx emissions are a critical problem for the ram combustor at Mach 5 condition.
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Chein, Reiyu, Yen-Cho Chen, Jui-Yu Chen, and J. N. Chung. "Premixed Methanol–Air Combustion Characteristics in a Mini-scale Catalytic Combustor." International Journal of Chemical Reactor Engineering 14, no. 1 (February 1, 2016): 383–93. http://dx.doi.org/10.1515/ijcre-2014-0061.

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AbstractMethanol catalytic combustion in a mini-scale tubular quartz-made combustor is investigated in this study. An alumina sphere was employed as the support for the platinum catalyst. The experimental results showed that the combustion can be self-ignited at room temperature. Using the combustor wall temperature to characterize the combustor performance, it was found that the combustion temperature can reach a high value within a short time. The experimental results indicated that the combustor performance depends greatly on the fuel/air supply. A higher temperature can be obtained with a higher fuel/air flow rate. The insulated and non-insulated combustor experimental results indicated that heat loss to the environment is an important factor in governing the combustion characteristics due to the large surface/volume ratio. A higher temperature can also be obtained when the combustor is insulated. Because most of the combustion took place at the combustor entrance region, the experimental result suggested that the combustor length can be shortened, leading to a more compact design allowing the combustor integration with various applications. A simple numerical model was built to provide a greater understanding of the combustion characteristics and examine the heat loss effect on combustor performance.
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Ding, Shibin, Qingzhi Wang, and Weizhuo Hua. "Study on Plasma Combustion in Aeroengine Combustor." Journal of Physics: Conference Series 2483, no. 1 (May 1, 2023): 012054. http://dx.doi.org/10.1088/1742-6596/2483/1/012054.

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Abstract To explore the plasma combustion affect the performance of the aircraft engine combustor, 16 components in the aviation kerosene 25-step reaction mechanism on the basis of considering step 9 simplify the plasma reaction mechanism, set up considering plasma electron collision reaction excited state relaxation and excited states participate in the process of chemical reaction kerosene combustion reaction model, The numerical calculation of the combustion process in the combustor is carried out, and the numerical calculation results of the combustion process with or without plasma combustion are compared and analyzed. The results show that the core reaction zone of the combustion chamber fuel is relatively forward under the conventional mechanism condition, and the average temperature of the combustion chamber outlet is 1910K. The temperature and high-temperature zone of the combustor where the plasma mechanism is applied are mainly distributed in the combustor outlet, mixing hole and main combustion hole, and the average temperature is 2050K. Meanwhile, the kerosene combustion efficiency also increases from 82.4% to 90.1%, increasing by about 7.7%. The results show that the addition of a plasma mechanism can deepen the chemical reaction degree of kerosene and release more heat to improve the combustion efficiency of kerosene.
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Sing Mei, Sim, Aslina Anjang Ab Rahman, Mohd Shukur Zainol Abidin, and Nurul Musfirah Mazlan. "d2 Law and Penetration Length of Jatropha and Camelina Bio-Synthetic Paraffinic Kerosene Spray Characteristics at Take-Off, Top of Climb and Cruise." Aerospace 8, no. 9 (September 4, 2021): 249. http://dx.doi.org/10.3390/aerospace8090249.

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A comparison of d2 law and penetration length of biofuels with Jet–A through the incorporation of fuel properties and actual combustor inlet data at various flight trajectories is presented. This study aims to identify fuel properties and flight operating conditions that most influence droplet characteristics accurately. The study comprises two phases involving a simulation using GSP to predict combustor inlet data for the respective flight operating conditions and a simulation using ANSYS Fluent V18.1 to obtain combustion characteristics of biofuels and Jet–A. The biofuels chosen in this study are Jatropha Bio-synthetic Paraffinic Kerosene (JSPK) and Camelina Bio-synthetic Paraffinic Kerosene (CSPK), evaluated as pure (100%) and blend (50%) with Jet–A. Thrust specific fuel consumption (TSFC) of biofuels is improved due to lower fuel consumed by the engine. The d2 law curve shows a heat-up period that takes place at the early stage of the combustion process. The penetration length of the fuels is shorter at take-off. Combusting biofuels reduce combustion temperature and the penetration length of the droplet.
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Erdiwansyah, Mahidin, Husni Husin, Nasaruddin, Muhtadin, Muhammad Faisal, Asri Gani, Usman, and Rizalman Mamat. "Combustion Efficiency in a Fluidized-Bed Combustor with a Modified Perforated Plate for Air Distribution." Processes 9, no. 9 (August 24, 2021): 1489. http://dx.doi.org/10.3390/pr9091489.

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Combustion efficiency is one of the most important parameters especially in the fluidized-bed combustor. Investigations into the efficiency of combustion in fluidized-bed combustor fuels using solid biomass waste fuels in recent years are increasingly in demand by researchers around the world. Specifically, this study aims to calculate the combustion efficiency in the fluidized-bed combustor. Combustion efficiency is calculated based on combustion results from the modification of hollow plates in the fluidized-bed combustor. The modified hollow plate aims to control combustion so that the fuel incorporated can burn out and not saturate. The combustion experiments were tested using palm oil biomass solid waste fuels such as palm kernel shell, oil palm midrib, and empty fruit bunches. The results of the measurements showed that the maximum combustion temperature for the palm kernel shell fuel reached 863 °C for M1 and 887 °C for M2. The maximum combustion temperature measurements for M1 and M2 from the oil palm midrib fuel testing reached 898 °C and 858 °C, respectively, while the maximum combustion temperature for M1 and M2 from the empty fruit bunches fuel was 667 °C and M2 847 °C, respectively. The rate of combustion efficiency with the modification of the hole plate in the fluidized-bed combustor reached 96.2%. Thermal efficiency in fluidized-bed combustors for oil palm midrib was 72.62%, for PKS was 70.03%, and for empty fruit bunches was 52.43%. The highest heat transfer rates for the oil palm midrib fuel reached 7792.36 W/m2, palm kernel shell 7167.38 W/m2, and empty fruit bunches 5127.83 W/m2. Thus, the modification of the holed plate in the fluidized-bed combustor chamber showed better performance of the plate than without modification.
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Dissertations / Theses on the topic "Combustion"

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Tajiri, Kazuya. "Simulations of combustion dynamics in pulse combustor." Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12175.

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Fernandes, Renato. "Metodologia de projeto de queimadores a jato para fornos de clínquer." [s.n.], 2011. http://repositorio.unicamp.br/jspui/handle/REPOSIP/264846.

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Orientador: Waldir Antônio Bizzo
Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecânica
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Resumo: Os queimadores a jato são caracterizados pela elevada quantidade de movimento na direção axial e elevada potência, estes queimadores são muito empregados em fornos rotativos, principalmente na indústria do cimento e da calcinação. O projeto de queimadores a jato é realizado usualmente aproximando o escoamento de ar primário no queimador por um modelo de escoamento compressível isentrópico em um bocal, esta aproximação leva a elevada divergência entre o projeto e a performance do equipamento em operação. Nesta tese foram desenvolvidos e empregados modelos de escoamento compressível com atrito, troca de calor e variação de área de seção para o escoamento do ar primário no interior do queimador, esta modelagem permite integrar todo o projeto do queimador desde a especificação de motores, sopradores, simulação da rede de tubos que compõe queimador, incluindo o manifold, válvulas de controle, placas de orifício, mangotes etc, inclusive relacionando o escoamento do ar primário com o jato formado pelo queimador através do emprego e também do desenvolvimento de índices aerodinâmicos que representem o jato. Os pontos de inovação incluem além da modelagem proposta também o desenvolvimento de modelo para escoamento em swirlers, aplicação da lei de Crocco em escoamentos com mudança súbita de área de seção, aplicação de modelos de entrainment etc. A modelagem matemática proposta foi empregada no desenvolvimento de um sistema computacional na qual foi usado para simular diversos queimadores em escala industrial, e as simulações obtidas foram comparadas com as medições de campo realizadas nos queimadores. Os resultados das simulações foram muito representativos com divergências de no máximo 5,0 % entre as propriedades do escoamento simuladas com as propriedades mensuradas, por exemplo, pressão, temperatura, vazão etc
Abstract: Jet burners are characterized by their high power and their high momentum in the axis direction. For that reason, these burners are widely used in rotary kilns, especially in the cement and calcination industry. The project of jet burners is based on the approximation of the primary air flow in the burner, through the development of an isentropic compressible flow model for one nozzle. This approximation leads to high differences between the project and the actual performance of the equipment. For the purposes of this thesis, models of compressible flow with friction, heat exchange and variable cross section area for primary air flow inside the burner were developed and applied. The application of these models makes possible the integration of the whole burner project, i.e. specification of motors, blowers, and the simulation of the burner's tubing system, which comprises manifold, control valves, orifices flow meters, hoses, etc. These models also provides means to relate the primary air flow to the jet formed by the burner, through the application and development of aerodynamic indexes that represent the jet. Besides proposed modeling techniques, innovations in this thesis include the development of a model for representing flow in swirlers, an application of the Crocco law for flow through sudden changing cross sections, application of entrainment models, etc. Mathematical modeling was applied in the development of a computational system, which was used to simulate diverse industrial burners. Resulting simulations were compared with measures taken from actual burners. Results obtained were highly representative, showing a variance of 5.0% at the most between simulated flow properties and measured properties, i.e. pressure, temperature, flow rate, etc
Mestrado
Termica e Fluidos
Mestre em Engenharia Mecânica
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Leng, Jing. "Combustion processes within a gas fired pulsed combustor." Thesis, University of Cambridge, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.307945.

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Bishop, Robert Phelps. "Combustion efficiency in internal combustion engines." Thesis, Massachusetts Institute of Technology, 1985. http://hdl.handle.net/1721.1/15164.

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Thesis (B.S.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1985.
MICROFICHE COPY AVAILABLE IN ARCHIVES AND ENGINEERING
Bibliography: leaf 26.
by Robert Phelps Bishop.
B.S.
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Hossain, Abu Norman. "Combustion of solid fuel in a fluidized bed combustor." Ohio : Ohio University, 1998. http://www.ohiolink.edu/etd/view.cgi?ohiou1176492911.

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Hossain, Abu Noman. "Combustion of solid fuel in a fluidized bed combustor." Ohio University / OhioLINK, 1998. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1176492911.

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Lei, Yafeng. "Combustion and direct energy conversion in a micro-combustor." Texas A&M University, 2005. http://hdl.handle.net/1969.1/4311.

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The push toward the miniaturization of electromechanical devices and the resulting need for micro-power generation (milliwatts to watts) with low-weight, long-life devices has led to the recent development of the field of micro-scale combustion. Since batteries have low specific energy (~200 kJ/kg) and liquid hydrocarbon fuels have a very high specific energy (~50000 kJ/kg), a miniaturized power-generating device, even with a relatively inefficient conversion of hydrocarbon fuels to power, would result in increased lifetime and/or reduced weight of an electronic or mechanical system that currently requires batteries for power. Energy conversion from chemical energy to electrical energy without any moving parts can be achieved by a thermophotovoltaic (TPV) system. The TPV system requires a radiation source which is provided by a micro-combustor. Because of the high surface area to volume ratio for micro-combustor, there is high heat loss (proportional to area) compared to heat generation (proportional to volume). Thus the quenching and flammability problems are more critical in a micro-scale combustor. Hence innovative schemes are required to improve the performance of micro-combustion. In the current study, a micro-scale counter flow combustor with heat recirculation is adapted to improve the flame stability in combustion modeled for possible application to a TPV system. The micro-combustor consists of two annular tubes with an inner tube of diameter 3 mm and 30 mm long and an outer tube of 4.2 mm diameter and 30 mm long. The inner tube is supplied with a cold premixed combustible mixture, ignited and burnt. The hot produced gases are then allowed to flow through outer tube which supplies heat to inner tube via convection and conduction. The hot outer tube radiates heat to the TPV system. Methane is selected as the fuel. The model parameters include the following: diameter d , inlet velocity u , equivalence ratio φ and heat recirculation efficiency η between the hot outer flow and cold inner flow. The predicted performance results are as followings: the lean flammability limit increased from 7.69% to 7.86% and the quenching diameter decreased from 1.3 mm to 0.9 mm when heat recirculation was employed. The overall energy conversion efficiency of current configuration is about 2.56.
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Chow, Siu-Kei. "Flow and combustion characteristics of a liquid-fuelled combustor." Thesis, Imperial College London, 1991. http://hdl.handle.net/10044/1/46714.

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Ichihashi, Fumitaka. "Investigation of Combustion Instability in a Single Annular Combustor." University of Cincinnati / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1299617901.

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Ribeiro, Natália da Silva [UNESP]. "Estudo termogravimétrico da combustão e oxicombustão de misturas carvão mineral-biomassa." Universidade Estadual Paulista (UNESP), 2017. http://hdl.handle.net/11449/149903.

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Conselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq)
Nesta dissertação, investiga-se através da análise termogravimétrica o comportamento da combustão de amostras de carvão mineral, bagaço de cana-de-açúcar, bagaço de sorgo biomassa e das misturas de carvão-biomassa. A biomassa e o carvão possuem propriedades físico-químicas diferentes que proporcionam comportamento térmico diferente durante o processo de co-combustão, desta forma o objetivo desta pesquisa é caracterizar o comportamento térmico de misturas de carvão mineral com bagaço de cana-de-açúcar e bagaço de sorgo em atmosferas simuladas de combustão (O2/N2) e oxicombustão (O2/CO2). Os experimentos foram realizados em duplicata em um analisador termogravimétrico utilizando uma razão de aquecimento de 10 °C/min. Foi considerada uma granulometria uniforme para todos os materiais (63 µm) com a finalidade de garantir uma mistura homogênea. Foram estudadas quatro proporções de biomassa na mistura (10, 25, 50 e 75%). A partir das técnicas de termogravimetria (TG) e termogravimetria derivada (DTG) foram determinados parâmetros tais como Índice de combustão, sinergismo e energia de ativação, bem como avaliada a influência da atmosfera de combustão sobre esses parâmetros. Os resultados indicam que o bagaço de cana-de-açúcar apresenta valor de energia de ativação inferior ao registrado para o bagaço de sorgo e desempenho de combustão superior ao do bagaço de sorgo. Para as misturas, os melhores resultados foram registrados até a proporção de 25% de biomassa na mistura. Avaliando individualmente cada material, quando se substitui o N2 por CO2 pode-se observar um aumento na reatividade da reação, uma maior oxidação dos materiais e uma melhora nos parâmetros avaliados. Para ambas as misturas não foram observadas mudanças significativas no perfil de combustão quando o N2 é substituído por CO2. No entanto, a presença da biomassa na co-combustão com o carvão, além dos benefícios econômicos e ambientais, aumentou o desempenho da combustão do carvão mineral em ambas as atmosferas.
This dissertation investigates by thermogravimetric analysis the behavior of the combustion of coal, sugarcane bagasse, sorghum biomass bagasse and coal-biomass blends. The biomass and coal have different physicochemical properties that provide different thermal behavior during the process of co-combustion, thus the aim of this research is to characterize the thermal behavior of coal mixed with sugarcane bagasse and sorghum bagasse in simulated atmospheres of combustion (O2/N2) and oxycombustion (O2/CO2). The experiments were performed in duplicate in a thermogravimetric analyzer using a heating rate of 10 ° C/min. A uniform particle size for all materials (63 μm) in order to ensure a homogeneous mixture was considered. Four biomass ratios were studied in the blend (10, 25, 50 and 75%). From the techniques of Thermogravimetry (TG) and Derivative Thermogravimetry (DTG) curves were determined parameters such as: Combustion index, synergism and activation energy and evaluated the influence of combustion atmosphere on these parameters. The results indicate that the sugarcane bagasse presents a lower activation energy value than sorghum bagasse and combustion performance higher than sorghum bagasse. For mixtures, best results were recorded up to 25% proportion of biomass in the blend. Individually evaluating each material, when replacing N2 by CO2 can be seen an increase in the reactivity of the reaction, the increased oxidation of the materials and an improvement in the evaluated parameters. For both blends, no significant changes in combustion profile when N2 substituted by CO2. However, the presence of biomass in co-combustion with coal in addition to economic and environmental benefits increased the combustion performance of coal in both atmospheres.
CNPq: 134366/2015-8
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Books on the topic "Combustion"

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Warnatz, Jürgen, Ulrich Maas, and Robert W. Dibble. Combustion. Berlin, Heidelberg: Springer Berlin Heidelberg, 1999. http://dx.doi.org/10.1007/978-3-642-98027-5.

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Warnatz, Jürgen, Ulrich Maas, and Robert W. Dibble. Combustion. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-662-04508-4.

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Warnatz, Jürgen, Ulrich Maas, and Robert W. Dibble. Combustion. Berlin, Heidelberg: Springer Berlin Heidelberg, 1996. http://dx.doi.org/10.1007/978-3-642-97668-1.

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4

Glassman, Irvin. Combustion. 2nd ed. Orlando [Fla.]: Academic Press, 1987.

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1952-, Yetter Richard A., ed. Combustion. 4th ed. Amsterdam: Academic Press, 2008.

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Cottilard, Sophie A. Catalytic combustion. Hauppauge, N.Y: Nova Science Publishers, 2011.

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Raghavan, Vasudevan. Combustion Technology. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-74621-6.

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Liberman, Michael A. Combustion Physics. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-85139-2.

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Raghavan, Vasudevan. Combustion Technology. Chichester, UK: John Wiley &;#38; Sons, Ltd, 2016. http://dx.doi.org/10.1002/9781119241775.

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Gupta, Aman, Shubham Sharma, and Sunny Narayan. Combustion Engines. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2016. http://dx.doi.org/10.1002/9781119284543.

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Book chapters on the topic "Combustion"

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Zohuri, Bahman, and Patrick McDaniel. "Combustion." In Thermodynamics In Nuclear Power Plant Systems, 249–66. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-13419-2_11.

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Struchtrup, Henning. "Combustion." In Thermodynamics and Energy Conversion, 541–61. Berlin, Heidelberg: Springer Berlin Heidelberg, 2014. http://dx.doi.org/10.1007/978-3-662-43715-5_25.

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Simonson, John. "Combustion." In Thermodynamics, 461–517. London: Macmillan Education UK, 1993. http://dx.doi.org/10.1007/978-1-349-12466-4_9.

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Basu, Prabir. "Combustion." In Circulating Fluidized Bed Boilers, 89–119. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-06173-3_4.

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Sherwin, Keith, and Michael Horsley. "Combustion." In Thermofluids, 411–31. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4899-4433-7_21.

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Zohuri, Bahman, and Patrick McDaniel. "Combustion." In Thermodynamics in Nuclear Power Plant Systems, 247–64. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-93919-3_11.

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Heckel, Pamela E. "Combustion." In SpringerBriefs in Environmental Science, 29–42. Dordrecht: Springer Netherlands, 2015. http://dx.doi.org/10.1007/978-94-017-9701-6_2.

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Sherwin, Keith, and Michael Horsley. "Combustion." In Thermofluids, 81–83. Boston, MA: Springer US, 1996. http://dx.doi.org/10.1007/978-1-4899-6870-8_21.

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Sherwin, Keith. "Combustion." In Introduction to Thermodynamics, 234–58. Dordrecht: Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-011-1514-8_11.

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Cleaves, Henderson James. "Combustion." In Encyclopedia of Astrobiology, 499–500. Berlin, Heidelberg: Springer Berlin Heidelberg, 2015. http://dx.doi.org/10.1007/978-3-662-44185-5_322.

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Conference papers on the topic "Combustion"

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Culick, F. "Combustion instabilities - Mating dance of chemical, combustion, and combustor dynamics." In 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-3178.

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Inamura, Takao, Mikihiro Sei, Mamoru Takahashi, and Akinaga Kumakawa. "Combustion characteristics of ramjet combustor." In 32nd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-2665.

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Scarinci, Thomas, and John L. Halpin. "Industrial Trent Combustor — Combustion Noise Characteristics." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-009.

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Thermoacoustic resonance is a difficult technical problem that is experienced by almost all lean-premixed combustors. The Industrial Trent combustor is a novel dry-low-emissions (DLE) combustor design, which incorporates three stages of lean premixed fuel injection in series. The three stages in series allow independent control of two stages — the third stage receives the balance of fuel to maintain the desired power level — at all power conditions. Thus, primary zone and secondary zone temperatures can be independently controlled. This paper examines how the flexibility offered by a 3-stage lean premixed combustion system permits the implementation of a successful combustion noise avoidance strategy at all power conditions and at all ambient conditions. This is because at a given engine condition (power level and day temperature) a characteristic “noise map” can be generated on the engine, independently of the engine running condition. The variable distribution of heat release along the length of the combustor provides an effective mechanism to control the amplitude of longitudinal resonance modes of the combustor. This approach has allowed the Industrial Trent combustion engineers to thoroughly “map out” all longitudinal combustor acoustic modes and design a fuel schedule that can navigate around regions of combustor thermoacoustic resonance. Noise mapping results are presented in detail, together with the development of noise prediction methods (frequency and amplitude) that have allowed the noise characteristics of the engine to be established over the entire operating envelope of the engine.
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Nakae, Tomoyoshi. "Combustion Control for Low NOx Combustor." In 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-3726.

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Lemcherfi, Aaron I., Rohan Gejji, Tristan L. Fuller, William E. Anderson, and Carson D. Slabaugh. "Investigation of Combustion Instabilities in a Full Flow Staged Combustion Model Rocket Combustor." In AIAA Propulsion and Energy 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-3948.

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Barhaghi, Darioush G., and Daniel Lörstad. "Investigation of Combustion in a Dump Combustor Using Different Combustion and Turbulence Models." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-44095.

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Modelling combustion in gas turbine combustors remains to be a challenge since several different physical phenomena interact in the process. One of the most important aspects of the combustion in a gas turbine combustor is the chemistry-turbulence interaction. In order to study the effect of the combustion and turbulence models, a dump combustor geometry is selected. Two combustion models namely, finite rate chemistry and flamelet based models, together with different turbulent models including LES 1eq k-model, RANS k-epsilon and k-omega models are implemented using both CFX and OpenFoam codes. The predicted temperature and velocity fields are compared to the existing experimental results. It is shown that different turbulence models behave very differently and there are large discrepancies between the experimental and predicted results. Some part of the discrepancies may be due to unknown heat losses through the combustor wall in the experiment.
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Ge*, Bing, Yuze Li, Yuliang Jia, Min Jin, and Shusheng Zang. "Study on Combustion instability of Secondary Combustion in an Axial Staged Model Combustor." In GPPS Hong Kong24. GPPS, 2023. http://dx.doi.org/10.33737/gpps23-tc-269.

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The experimental study is carried out to reveal the influence of the disturbance of main combustion air inlet on the axial staged combustion. The response of the combustion characteristics in the primary and secondary combustion chambers are obtained by acoustically forcing the inlet air to oscillate. The results indicate that the dominant frequency of combustion oscillation in the axial staged combustor is basically as the same as that of acoustic excitation. The pressure is more pronounced at the forced frequency of 270 Hz. Compared with the stable combustion state, the reburning flame is lifted and shrinks when the main air is oscillated. The spatial band area of the flame centroid fluctuations is transformed from the height (Y) direction to the streamwise (Z) direction. Combustion oscillation reduces the fluctuation range of reburning flame in the Y direction but expands in the Z direction. It is found that the dominant frequency of 201 Hz appears along in both Y and Z directions at the stable combustion status. In the case of forced oscillation, the dominant frequency of 270 Hz occurs along the Z and Y directions, and the amplitude of the original fluctuation of the reburning flame in the Z direction increases.
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Singh, Kapil, Bala Varatharajan, Ertan Yilmaz, Fei Han, and Kwanwoo Kim. "Effect of Hydrogen Combustion on the Combustion Dynamics of a Natural Gas Combustor." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51343.

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In a carbon-constrained world, Integrated Gasification Combined Cycle (IGCC) systems achieve excellent environmental performance and offer a more economical pre-combustion CO2 removal compared to other coal-based systems. The residual gas after carbon removal is comprised primarily of hydrogen and nitrogen mixtures. Achieving stable combustion of hydrogen-rich fuel mixtures while producing ultra-low NOx emissions (much lower than current diffusion combustion technology) is challenging. The goal of this study was to characterize the stability of lean premixed combustion systems operating with hydrogen and establish boundaries for stable operation. Modeling and experimental efforts were directed towards demonstration of the feasibility of such systems while meeting the emissions requirements. The higher flame speed and heat-release rate achievable with hydrogen-containing fuels can change the dynamics and stability characteristics of the combustors compared to natural gas. A combustion rig was modeled using an in-house combustion dynamics analysis code. In the model, flame heat-release fluctuations were captured by considering the effect of upstream fuel-air ratio fluctuations and flow speed fluctuations. CFD simulations were used to obtain combustion parameters. The results showed the effect of using hydrogen instead of methane and the simulations correctly predicted the combustor modes and their instability for hydrogen as well as methane combustion.
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TAMURA, HIROSHI, FUMIEI ONO, AKINAGA KUMAKAWA, and NOBUYUKI YATSUYANAGI. "LOX/methane staged combustion rocket combustor investigation." In 23rd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1856.

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Yu, Yen, Mark Pfeil, Stanford Rosen, William Anderson, and Steve Son. "Effects of NanoAluminum on Droplet Combustion and Combustion Instabilities in a Single Element Rocket Combustor." In 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-7154.

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Reports on the topic "Combustion"

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Banerjee, Subhodeep, and Robin Hughes. Biomass Combustion in a Circulating Fluidized Bed Combustor. Office of Scientific and Technical Information (OSTI), September 2020. http://dx.doi.org/10.2172/1659115.

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Hughes, Robin, and Subhodeep Banerjee. Biomass Combustion in a Circulating Fluidized Bed Combustor. Office of Scientific and Technical Information (OSTI), September 2020. http://dx.doi.org/10.2172/1660765.

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Parr, T., K. Wilson, K. Schadow, J. Cole, and N. Widmer. Sludge Combustor Using Swirl and Active Combustion Control. Fort Belvoir, VA: Defense Technical Information Center, January 2000. http://dx.doi.org/10.21236/ada382663.

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Beshouri. PR-309-04200-R01 Modeling Methodology for Parametric Emissions Monitoring System for Combustion Turbines. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), March 2005. http://dx.doi.org/10.55274/r0010731.

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Prior attempts to develop a generic Parametric Emissions Monitoring methodology for combustion turbines, particularly low emissions units, have failed due either to the reduction of a complex problem to too few degrees of freedom or the brute force reliance on regression analysis. Field test data collected by the research team clearly illustrated that a successful PEMS model will need to incorporate multiple zones to account for pilot fuel versus pre-mixed combustion, and changes in air/fuel ratio at the flame front. The information reported herein shows that, ideally, the PEMS model should rely on speed, fuel flow, compressor discharge pressure and temperature, and ambient conditions as the inputs. The model can utilize (combustion turbine) turbine discharge temperatures as cross checks and/or for tuning. Make and model specific geometric characteristics should include compressor air flow versus speed, air splits between the combustor and the cooling air, and the fuel splits between diffusion and premixed. Finally, the model should be able to accommodate fuel that varies in composition based on provided gas speciation.
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Gutmark, Ephralm J., and Guoqiang Li. Combustion Control in Industrial Multi-Swirl Stabilized Spray Combustor. Fort Belvoir, VA: Defense Technical Information Center, August 2005. http://dx.doi.org/10.21236/ada441269.

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A. Levasseur, S. Goodstine, J. Ruby, M. Nawaz, C. Senior, F. Robson, S. Lehman, et al. Combustion 2000. US: United Technologies Corp, June 2001. http://dx.doi.org/10.2172/898342.

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Skone, Timothy J. Distribution combustion. Office of Scientific and Technical Information (OSTI), January 2018. http://dx.doi.org/10.2172/1559440.

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Skone, Timothy J. Processing combustion. Office of Scientific and Technical Information (OSTI), January 2018. http://dx.doi.org/10.2172/1559827.

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Ohlemiller, T. J. Smoldering combustion. Gaithersburg, MD: National Bureau of Standards, 1986. http://dx.doi.org/10.6028/nbs.ir.85-3294.

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Ojeda, William de. Low Temperature Combustion Demonstrator for High Efficiency Clean Combustion. Office of Scientific and Technical Information (OSTI), July 2010. http://dx.doi.org/10.2172/1043162.

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