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Journal articles on the topic 'Combustion chambre'

Author: Grafiati

Published: 28 June 2021

Last updated: 29 July 2025

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1

Vernocchi, Virginia, Marco Brunoldi, Silvia G. Danelli, Franco Parodi, Paolo Prati, and Dario Massabò. "Characterization of soot produced by the mini inverted soot generator with an atmospheric simulation chamber." Atmospheric Measurement Techniques 15, no. 7 (2022): 2159–75. http://dx.doi.org/10.5194/amt-15-2159-2022.

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Abstract. The performance of a mini inverted soot generator (MISG) has been investigated at ChAMBRe (Chamber for Aerosol Modelling and Bio-aerosol Research) by studying the properties of soot particles generated by ethylene and propane combustion. This work deepens and expands the existing characterization of the MISG, which also exploits an atmospheric simulation chamber (ASC). Different from previous works, MISG performance has been also tested at different fuel flows and higher global equivalence ratios. MISG exhausts were investigated after their injection inside the atmospheric simulation

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2

Léger, Bruno, Patrick André, Guy Grienche, and Gérard Schott. "Contrôle thermique de parois de chambre de combustion. Banc d'essai du laboratoire aquitain de recherche en aérothermique." Revue Générale de Thermique 35, no. 417 (1996): 625–30. http://dx.doi.org/10.1016/s0035-3159(96)80025-0.

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3

Kashdan, Julian. "Visualisation du mélange gazeux au sein de la chambre de combustion des moteurs par la fluorescence induite par laser." Photoniques, no. 52 (March 2011): 34–36. http://dx.doi.org/10.1051/photon/20115234.

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4

Evita Leninda Fahriza Ayuni, Andinusa Rahmandhika, Daryono, et al. "The Effect of Insulation Thickness on Heat Transfer Characteristics and Flammability in Tube Mesoscale Combustors." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 116, no. 2 (2024): 157–71. http://dx.doi.org/10.37934/arfmts.116.2.157171.

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Micropower generator is a micro-scale energy source that has two main components, namely a micro/mesoscale combustor and thermophotovoltaics (TPV). The micro-scale combustor is one part that functions as a combustion chamber that produces heat in micropower plants. Heptane is used as fuel, while the combustor combustion chamber with a diameter of 3.5 mm is made from duraluminium-quart glass tube. Combustion stability in the combustion chamber is influenced by several factors, such as temperature, geometry, and combustion chamber design. In order to maintain flame stability, mesh is added to th

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5

Łapinski, Damian, and Janusz Piechna. "Improvements in the turbo-engine by replacement of conventional combustion chamber by a pulse combustion chamber." Archive of Mechanical Engineering 60, no. 4 (2013): 481–94. http://dx.doi.org/10.2478/meceng-2013-0029.

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Abstract This paper comprises description of the turbo engine and evaluation of its analytical model. The analytical model was created to establish a benchmark for further evaluation of a wave rotor combustor (at constant volume). The wave rotor combustor concept was presented and discussed. Advantages of combustion at constant volume were described as well as the basic turbo engine updates required to reflect pulse combustor application. The calculation results for analytical model of a basic engine, and that equipped with pulse combustor are included in this paper. The paper describes the re

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Hery Soegiharto, Achmad Fauzan, Ali Mokhtar, Sudarman, and Satworo Adiwidodo. "Role of Flue Gas Inhibitor on Stabilizing Heptane Flame in Meso Scale Combustor." Journal of Energy, Mechanical, Material, and Manufacturing Engineering 6, no. 2 (2021): 111–18. https://doi.org/10.22219/jemmme.v6i2.19458.

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Mesoscale combustor is one of the components that serves to generate heat on a micro power generator. As one of the components of a micro power generator, meso scale combustor serves to supply heat through the combustion process. The stability of the flame in the combustion chamber meso scale combustor is influenced by the temperature of the combustion chamber. One way to maintain a high temperature in the combustion chamber is to insert a flue gas stainless steel mesh resistor.. This research aims to prove the role of flue gas mesh resistors in stabilizing the flame on the meso scale combusto

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Ding, Shibin, Qingzhi Wang, and Weizhuo Hua. "Intelligent control chamber for plasma-enhanced combustion." Journal of Physics: Conference Series 2483, no. 1 (2023): 012066. http://dx.doi.org/10.1088/1742-6596/2483/1/012066.

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Abstract At present, there are some problems with aero-engine, such as insufficient high-altitude point/flameout boundary, smoke in large conditions, and easy flameout in slow trains with poor oil, which seriously threaten flight safety. Aiming at the problem of insufficient high altitude stable combustion range, an intelligent control combustor of plasma-enhanced combustion is proposed in this paper. The sliding arc exciter is perfectly combined with the combustor head and the pre-burning sliding arc jet igniter is used as the technical basis of the enhanced combustion. Based on the working e

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Naeemi, Saeed, and Seyed Abdolmehdi Hashemi. "Numerical investigations on the liftoff velocity of H2-air premixed combustion in a micro-cylindrical combustor with gradually changed section area." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 234, no. 17 (2020): 3497–508. http://dx.doi.org/10.1177/0954406220914925.

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Sustaining and stabilizing flames are crucial issues in micro-combustion. In some micro-electro-mechanical systems such as the micro-thermophotovoltaic system, the flame should be formed in the combustion chamber, not outside it (combustion without liftoff). So, study of the liftoff phenomenon is important and vital in these systems. The aim of this study is to evaluate effect of changing combustor section area on the critical liftoff velocity in a micro-cylindrical combustor. For this purpose, the critical liftoff velocities are numerically identified for four combustor configurations (conver

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9

Qian, Yu Fen, Yan Ying Xu, and Ti Hai Xu. "Combustion Characteristics of a Helmholtz-Type Valveless Self-Excited Pulse Combustor." Applied Mechanics and Materials 291-294 (February 2013): 1719–22. http://dx.doi.org/10.4028/www.scientific.net/amm.291-294.1719.

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Combustion characteristics of a Helmholtz-type valveless self-excited pulse combustor with continuous supply of gas and air were studied. The physical and mathematical models are established based on the actual pulse combustor, and the combustion characteristics are simulated with CFD. The results show that the possible re-ignition sources for the pulse combustion may be three. The first source may be the hot remnant gas near gas/air mixture. The second re-ignition source may be the high-temperature combustion chamber wall. The third ignition source is the unburned mixture. The pressure, tempe

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Kuang, Hui, Xianpu Zhong, Junhao Wei, Fei Xing, and Zhenyin Hai. "Research on Dynamic Temperature at Outlet of Centrally Staged Combustor Based on TDLAS Technology." Sensors 25, no. 7 (2025): 2256. https://doi.org/10.3390/s25072256.

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High-frequency oscillations occur in the centrally staged combustor during operation. To effectively suppress them, real-time monitoring of the combustor exit temperature is critical. However, traditional contact temperature measurement methods are inadequate for accurately capturing temperature variations in the turbulent flow field. Tunable Diode Laser Absorption Spectroscopy (TDLAS) with a high acquisition frequency is employed to measure the temperature of the centrally staged combustor, utilizing a non-contact sensing method. The influence of various combustion parameters on the uniformit

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11

Duan, Run Ze, Zhi Ying Chen, and Li Jun Yang. "Modeling and Simulation of Combustion Chamber." Applied Mechanics and Materials 513-517 (February 2014): 3543–47. http://dx.doi.org/10.4028/www.scientific.net/amm.513-517.3543.

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The work process of oil fuel burner consists of atomization and combustion of oil. In this process, different atomization and air-distribution methods would affect the quality of combustion and then bring out problems of life-span of the burner, energy efficiency and environmental pollution. Therefore, in this paper, different air distribution devices and different sizes of nozzles are designed, and the numerical simulation software, Fluent 6.3, was employed to simulate the flow field of different conditions in combustor,. Through the simulation, the best work condition was achieved, which cou

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Marudhappan, Raja, Chandrasekhar Udayagiri, and Koni Hemachandra Reddy. "Combustion chamber design and reaction modeling for aero turbo-shaft engine." Aircraft Engineering and Aerospace Technology 91, no. 1 (2018): 94–111. http://dx.doi.org/10.1108/aeat-10-2017-0217.

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Purpose The purpose of this paper is to formulate a structured approach to design an annular diffusion flame combustion chamber for use in the development of a 1,400 kW range aero turbo shaft engine. The purpose is extended to perform numerical combustion modeling by solving transient Favre Averaged Navier Stokes equations using realizable two equation k-e turbulence model and Discrete Ordinate radiation model. The presumed shape β-Probability Density Function (β-PDF) is used for turbulence chemistry interaction. The experiments are conducted on the real engine to validate the combustion chamb

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13

Ding, Shibin, Qingzhi Wang, and Weizhuo Hua. "Study on Plasma Combustion in Aeroengine Combustor." Journal of Physics: Conference Series 2483, no. 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 combus

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14

Kidoguchi, Y., M. Sanda, and K. Miwa. "Experimental and Theoretical Optimization of Combustion Chamber and Fuel Distribution for the Low Emission Direct-Injection Diesel Engine." Journal of Engineering for Gas Turbines and Power 125, no. 1 (2002): 351–57. http://dx.doi.org/10.1115/1.1501077.

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Effects of combustion chamber geometry and initial mixture distribution on the combustion process were investigated in a direct-injection diesel engine. In the engine experiment, a high squish combustion chamber with a squish lip could reduce both NOx and particulate emissions with retarded injection timing. According to the results of CFD computation and phenomenological modeling, the high squish combustion chamber with a central pip is effective to keep the combusting mixture under the squish lip until the end of combustion and the combustion region forms rich and highly turbulent atmosphere

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15

Satworo, Adiwidodo, Nyoman Gede Wardana I, Yuliati Lilis, and Nur Sasongko Mega. "PERFORMANCE OF CYLINDRICAL AND PLANAR MESOSCALE COMBUSTOR WITH DOUBLE NARROW SLIT FLAME HOLDER FOR MICROPOWER GENERATOR." Eastern-European Journal of Enterprise Technologies 2, no. 8 (104) (2020): 35–43. https://doi.org/10.15587/1729-4061.2020.198570.

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This research compared the performance of a cylindrical mesoscale combustor against two planar mesoscale combustors, which include the shape of the flame front, temperature of the combustor axis and the combustor wall, and the resulting flammability limit. The combustor used has a circular, square and rectangular cross-section. All three combustors have the same cross-section area and combustion chamber volume. The flame holder used is a double narrow slit. The fuel used is liquefied petroleum gas with a pure oxygen oxidizer. The experiment results showed that the cylindrical combustor produce

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16

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

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

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17

Serbin, Serhiy, Mykola Radchenko, Anatoliy Pavlenko, Kateryna Burunsuz, Andrii Radchenko, and Daifen Chen. "Improving Ecological Efficiency of Gas Turbine Power System by Combusting Hydrogen and Hydrogen-Natural Gas Mixtures." Energies 16, no. 9 (2023): 3618. http://dx.doi.org/10.3390/en16093618.

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Currently, the issue of creating decarbonized energy systems in various spheres of life is acute. Therefore, for gas turbine power systems including hybrid power plants with fuel cells, it is relevant to transfer the existing engines to pure hydrogen or mixtures of hydrogen with natural gas. However, significant problems arise associated with the possibility of the appearance of flashback zones and acoustic instability of combustion, an increase in the temperature of the walls of the flame tubes, and an increase in the emission of nitrogen oxides, in some cases. This work is devoted to improvi

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18

Pošta, J., B. Kadleček, and T. Hladík. "Engine combustion chamber tightness diagnostics." Research in Agricultural Engineering 49, No. 3 (2012): 115–18. http://dx.doi.org/10.17221/4961-rae.

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The modern combustion engines and their systems are getting more complicated and sophisticated nowadays. It is no more possible to verify their function or actual technical state directly. Thus various methods of indirect diagnostics are being developed more and more rapidly. The on-board diagnostics is being increasingly applied to monitor and measure suitable diagnostic signals during operation, deviations from required or expected values are then recorded. This trend requires the application of completely disassembly-free techniques of measurements and the real-time analyzing of measured fi

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19

Podlesniy, Dmitry, Eugene Polianczyk, Maxim Tsvetkov, Leonid Yanovsky, and Andrey Zaichenko. "The Combustion of Lean Ethanol–Air Mixtures in a Swiss-Roll Combustor." Processes 12, no. 12 (2024): 2690. http://dx.doi.org/10.3390/pr12122690.

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A novel meso-scale 3-channel 5-turn Swiss-roll type combustor was designed and tested. The non-catalytic combustion of lean ethanol–air mixtures was experimentally investigated in relation to the oxygen excess ratio (α), which varied from 1.5 to 7. Depending on the control parameters used, two distinct regimes of combustion were experimentally observed: one with a combustion zone within the central chamber and another with a combustion zone in the inflow channel. The combustion temperature was virtually independent of stoichiometry. For richer mixtures and lower flow rates, the combustion zone

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20

Yerzhan, Assem, and Mustafa İlbaş. "Numerical Simulation of Premixed Turbulent Methane Combustion in a Multi-Inlet Cyclone Combustor." Politeknik Dergisi 28, no. 1 (2024): 261–66. https://doi.org/10.2339/politeknik.1447381.

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The multi-inlet cyclone combustion chamber simulated in this study has 14 tangential gas/air inlets, each with an internal diameter of 9.525 mm, and is inclined 30° towards the front end of the combustion chamber in 2 symmetrical rows of seven. This study used CFD code to numerically simulate a multi-inlet cyclone combustor fueled by methane. The standard k-Ɛ model was chosen to simulate turbulent flow. Eddy Dissipation was used to simulate the combustion of a premixed mixture. The simulation was carried out for an air:fuel ratio (φ) of 1.0. The design velocity at the entrance to the combustio

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Lee, Dae Hoon, Dae-Eun Park, Euisik Yoon, and Sejin Kwon. "A MEMS Piston-Cylinder Device Actuated by Combustion." Journal of Heat Transfer 125, no. 3 (2003): 487–93. http://dx.doi.org/10.1115/1.1565095.

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Combustion measurement in a cylindrical micro combustor, the construction procedure and test run of a MEMS reciprocating device are described. The sizing of the MEMS device was based on the findings of combustion measurements. Thermodynamic analysis of the pressure measurement resulted in available work up to 2.4 Joules in a combustor height of 2 mm and more with combustion efficiency of 0.6∼0.7. With combustor height less than 2 mm, combustion was incomplete due to excessive heat loss to the wall. In order to achieve the chamber height imposed by the combustion measurement, a fabrication proc

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22

Wang, Yun, and Zhuo Xiong Zeng. "Numerical Simulation of Combusting Flow Field in Ram-Compressed Rotor Chamber." Advanced Materials Research 291-294 (July 2011): 2857–60. http://dx.doi.org/10.4028/www.scientific.net/amr.291-294.2857.

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The rotating ramjet is a new conceptive engine based on the ram-compressed technology rely on high-speed rotating rotor, the engine’s core component is an internal combustion rotor, which has the functions of compressing air, combusting and doing work by exhausting. In order to predict the combusting flow field in Ram-compressed Rotor chamber, the model of Ram-compressed Rotor was set up. The fuel composition was defined in software prePDF. Realizable was used for the gas phase turbulence. Fuel particles phase makes use of stochastic tracking model. The Structure characteristics of the combust

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23

Serbin, Sergey. "THERMO ACOUSTIC PROCESSES IN LOW EMISSION COMBUSTION CHAMBER OF GAS TURBINE ENGINE CAPACITY 25 MW." Science Journal Innovation Technologies Transfer, no. 2019-2 (May 5, 2019): 86–90. http://dx.doi.org/10.36381/iamsti.2.2019.86-90.

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The appliance of modern tools of the computational fluid dynamics for the investigation of the pulsation processes in the combustion chamber caused by the design features of flame tubes and aerodynamic interaction compressor, combustor and turbine is discussed. The aim of the research is to investigate and forecast the non-stationary processes in the gas turbine combustion chambers. The results of the numerical experiments which were carried out using three-dimensional mathematical models in gaseous fuels combustion chambers reflect sufficiently the physical and chemical processes of the unste

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Hao, Zhang, Yan Mi, and Li Jiahang. "Influence of Axial Flow Field Parameter Fluctuations on Performance of Scramjet Combustor." Journal of Physics: Conference Series 2913, no. 1 (2024): 012005. https://doi.org/10.1088/1742-6596/2913/1/012005.

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Abstract When air-breathing aircraft is flying over a wide area, the upflow of the combustor central axis will change greatly, and the flow field parameters will fluctuate along the axis. Therefore, it is necessary to carry out a study on the influence of axis flow field parameter fluctuation on combustion chamber performance, so as to provide relevant theoretical support for the combustion chamber of air-breathing aircraft in wide-area flight design. Based on the N-S gas-phase control model, combined with combustion model, turbulence model, burning rate model and mass transfer model, a numeri

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Fortunato, Valentina, Andres Giraldo, Mehdi Rouabah, Rabia Nacereddine, Michel Delanaye, and Alessandro Parente. "Experimental and Numerical Investigation of a MILD Combustion Chamber for Micro Gas Turbine Applications." Energies 11, no. 12 (2018): 3363. http://dx.doi.org/10.3390/en11123363.

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In the field of energy production, cogeneration systems based on micro gas turbine cyclesappear particularly suitable to reach the goals of improving efficiency and reducing pollutants.Moderate and Intense Low-Oxygen Dilution (MILD) combustion represents a promising technologyto increase efficiency and to further reduce the emissions of those systems. The present work aims atdescribing the behavior of a combustion chamber for a micro gas turbine operating in MILD regime.The performances of the combustion chamber are discussed for two cases: methane and biogascombustion. The combustor performed

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Lee, Y. W., and T. L. Jiang. "Effects of Fuel Impingement-Cooling on the Combustion Flow in a Small Bipropellant Liquid Rocket Thruster." Journal of Mechanics 31, no. 2 (2015): 161–70. http://dx.doi.org/10.1017/jmech.2014.81.

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ABSTRACTIn the present study, a three-dimensional computer code, based on the computer software KIVA-3, was developed for the combustion-flow simulation of a bipropellant liquid rocket thruster. A jets-impingement model is proposed for the unlike-doublet jet impingement issue. The computer code is employed to simulate a small bipropellant liquid rocket engine installed with three unlike-doublet injectors of NTO and MMH as well as six fuel injectors injecting MMH toward the combustor wall for cooling. Effects of the fuel-injection cooling on the combustion flow, combustion efficiency, and wall

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Chen, Yi, Li Fei, Liming He, Lei Zhang, Chunchang Zhu, and Jun Deng. "The Influence of Dielectric Barrier Discharge Plasma on the Characteristics of Aero-Engine Combustion Chamber." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 37, no. 2 (2019): 369–77. http://dx.doi.org/10.1051/jnwpu/20193720369.

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A test platform was developed to investigate the performance of aero-engine combustor by the dielectric barrier discharge (DBD) plasma assisted combustion (PAC) in the simulated maximum condition. Conventional combustion experiments and plasma-assisted combustion conditions were conducted to study the effect of PAC on the performances including average outlet temperature, combustion efficiency and pattern factor under four different excessive air coefficients five different voltages. The comparative experiment shows that the combustion efficiency is improved after PAC compared with the normal

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Liu, Gaoling, Mingli Cui, Xulin Luo, Guodong Wang, Bowei Yao, and Xuesong Li. "Flash Boiling Combustion Performance of Ethanol Fuel in Controlled Reaction Environment." E3S Web of Conferences 598 (2024): 01010. http://dx.doi.org/10.1051/e3sconf/202459801010.

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The utilization of alternative fuels such as alcohols and ethers has received substantial attention for the purpose of carbon neutralization and replacing traditional fossil fuels. However, the combustion of pure alternative fuels, for instance, pure ethanol, is relatively more challenging due to its lower volatility and heat released. This research aims to study the combustion of pure ethanol fuel (E100) in a constant volume combustion chamber (CVCC) with optical access. Flash boiling atomization via elevating the fuel temperature is adopted to improve fuel atomization and consequential combu

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29

Pries, Michael, Andreas Fiolitakis, and Peter Gerlinger. "Numerical Investigation of a High Momentum Jet Flame at Elevated Pressure: A Quantitative Validation with Detailed Experimental Data." Journal of the Global Power and Propulsion Society 4 (December 18, 2020): 264–73. http://dx.doi.org/10.33737/jgpps/130031.

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The development of efficient low emission combustion systems requires methods for an accurate and reliable prediction of combustion processes. Computational Fluid Dynamics (CFD) in combination with combustion modelling is an important tool to achieve this goal. For an accurate computation adequate boundary conditions are crucial. Especially data for the temperature distribution on the walls of the combustion chamber are usually not available. The present work focuses on numerical simulations of a high momentum jet flame in a single nozzle FLOX® type model combustion chamber at elevated pressur

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Kapucu, Mehmet, Jim B. W. Kok, and Artur K. Pozarlik. "Acoustic Design Parameter Change of a Pressurized Combustor Leading to Limit Cycle Oscillations." Energies 17, no. 8 (2024): 1885. http://dx.doi.org/10.3390/en17081885.

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When aiming to cut down on the emission of nitric oxides by gas turbine engines, it is advantageous to have them operate at low combustion temperatures. This is achieved by lean premixed combustion. Although lean premixed combustion is a proven and promising technology, it is also very sensitive to thermoacoustic instabilities. These instabilities occur due to a coupling between the unsteady heat release rate of the flame and the acoustic field inside the combustion chamber. In this paper, this coupling is investigated in detail. Two acoustic design parameters of a swirl-stabilized pressurized

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DUMITRACHE, Alexandru, and Florin FRUNZULICA. "A NUMERICAL ANALYSIS OF COMBUSTION PROCESS IN AN AXISYMMETRIC COMBUSTION CHAMBER." SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE 18, no. 1 (2016): 433–40. http://dx.doi.org/10.19062/2247-3173.2016.18.1.59.

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Seume, J. R., N. Vortmeyer, W. Krause, et al. "Application of Active Combustion Instability Control to a Heavy Duty Gas Turbine." Journal of Engineering for Gas Turbines and Power 120, no. 4 (1998): 721–26. http://dx.doi.org/10.1115/1.2818459.

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During the prototype shop tests, the Model V84.3A ring combustor gas turbine unexpectedly exhibited a noticeable “humming” caused by self-excited flame vibrations in the combustion chamber for certain operating conditions. The amplitudes of the pressure fluctuations in the combustor were unusually high when compared to the previous experience with silo combustor machines. As part of the optimization program, the humming was investigated and analyzed. To date, combustion instabilities in real, complex combustors cannot be predicted analytically during the design phase. Therefore, and as a preve

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Wang, Kefu, Feng Li, Tao Zhou, and Yiqun Ao. "Numerical Study of Combustion and Emission Characteristics for Hydrogen Mixed Fuel in the Methane-Fueled Gas Turbine Combustor." Aerospace 10, no. 1 (2023): 72. http://dx.doi.org/10.3390/aerospace10010072.

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The aeroderivative gas turbine is widely used as it demonstrates many advantages. Adding hydrogen to natural gas fuels can improve the performance of combustion. Following this, the effects of hydrogen enrichment on combustion characteristics were analyzed in an aeroderivative gas turbine combustor using CFD simulations. The numerical model was validated with experimental results. The conditions of the constant mass flow rate and the constant energy input were studied. The results indicate that adding hydrogen reduced the fuel residues significantly (fuel mass at the combustion chamber outlet

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Chand, Dharmahinder Singh, Daamanjyot Barara, Gautam Ganesh, and Suraj Anand. "Comparison of Efficiency of Conventional Shaped Circular and Elliptical Shaped Combustor." MATEC Web of Conferences 151 (2018): 02002. http://dx.doi.org/10.1051/matecconf/201815102002.

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There have been concerted efforts towards improving the fuel efficiency of the jet engines in the past, with an aim of reducing the incomplete combustion. The process of combustion in a jet engine takes place in the combustor. A study was conducted for enhancement of air-fuel mixing process by computational analysis of an elliptically shaped combustor for a gas turbine engine. The results of computational analysis of an elliptical shape combustor were compared with a circular shape combustor used in gas turbine engines with a identical cross sectional area. The comparison of the computationall

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Hwang, Donghyun, Cheolwoong Kang, and Kyubok Ahn. "Effect of Mixing Section Acoustics on Combustion Instability in a Swirl-Stabilized Combustor." Energies 15, no. 22 (2022): 8492. http://dx.doi.org/10.3390/en15228492.

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An experimental study was performed to investigate the characteristics of two different combustion instability modes in a swirl-stabilized combustor. The first is the eigenfrequency corresponding to the half-wave of the combustion chamber section, and the second is the quarter-wave eigenmode of the inlet mixing section. The purpose of this study is to understand the effects of the swirl number on each combustion instability mode and analyze their generalized characteristics. Premixed gases composed of hydrocarbon fuels (C2H4 and CH4) and air were burned by independently varying the experimenta

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Rajashekhar, Chandrashekharapua Ramachandraiah, Tumkur Krishnamurthy Chandrashekar, Chebbiyyan Umashankar, and Rajagopal Harish Kumar. "STUDIES ON EFFECTS OF COMBUSTION CHAMBER GEOMETRY AND INJECTION PRESSURE ON BIODIESEL COMBUSTION." Transactions of the Canadian Society for Mechanical Engineering 36, no. 4 (2012): 429–38. http://dx.doi.org/10.1139/tcsme-2012-0030.

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Combustion of biodiesels has inherent problems due to their high viscosity and low volatility. This paper relates the modification of engine combustion chamber design, for inducing turbulence to improve the combustibility of combustible mixture. A survey of literature shows that experimental studies have not been done on a tri-chambered piston for evaluating influence on the performance and emission characteristics using diesel blends as well. The objective of this work is to study the effect of combustion chamber geometry and injection pressure on performance and emissions of a biodiesel (Jat

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Yu, Xin, Zhen Cao, JiangBo Peng, et al. "Statistical Analysis of Flame Oscillation Characterization of Oxy-Fuel in Heavy Oil Boiler Using OH Planar Laser-Induced Fluorescence." Journal of Spectroscopy 2019 (July 2, 2019): 1–10. http://dx.doi.org/10.1155/2019/7085232.

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The present work investigated the flame structures and oscillations of oxy-fuel combustions in a heavy oil boiler using OH planar laser-induced fluorescence imaging. Combustion instabilities, such as flame oscillation and combustion fluctuation, can assess the performance of an industrial burner in the boiler. The peak position variation in OH concentration was associated with the change of the reaction zone that corresponded with the fluctuation of the heat-release zone in the combustion chamber, which provides a valuable reference for the design of the combustion chamber. The experimental re

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Xu, Shida, Feilong Song, Xin Chen, Hesong Zhang, Xingkui Yang, and Jianping Zhou. "Experimental Diagnosis on Combustion Characteristic of Shock Wave Focusing Initiation Engine." Entropy 24, no. 7 (2022): 1007. http://dx.doi.org/10.3390/e24071007.

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A shock wave focusing initiation engine was assembled and tested in an experimental program. The effective pyrolysis rate of the pre-combustor was evaluated over a range of supplementary fuel ratio in this paper. Results highlight two operational modes of the resonant cavity: (1) pulsating combustion mode, (2) stable combustion mode. The appearance of the two combustion modes is jointly affected by the flow and the structural characteristic value of the combustion chamber. This paper uses images, time-frequency analysis, and nonlinear time series analysis methods to identify and distinguish th

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Pan, J. F., Z. Y. Hou, Y. X. Liu, et al. "Design and working performance study of a novel micro parallel plate combustor with two nozzles for micro thermophotovotaic system." Thermal Science 19, no. 6 (2015): 2185–94. http://dx.doi.org/10.2298/tsci141109069p.

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Micro-combustors are a key component in combustion-driven micro power generators, and their performance is significantly affected by their structure. For the application of micro-thermophotovoltaic (MTPV) system, a high and uniform temperature distribution along the walls of the micro combustor is desired. In this paper, a three-dimensional numerical simulation has been conducted on a new-designed parallel plate micro combustor with two nozzles. The flow field and the combustion process in the micro combustor, and the temperature distribution on the wall as well as the combustion efficiency we

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Gao, Huanhuan, Zaiguo Fu, Zhuoxiong Zeng, Jiang Liu, and Peifen Weng. "Effects of Swirling Strength of the Premixed Gas Flow on Pollutant Emission in a Heavy-Duty Gas Turbine." E3S Web of Conferences 118 (2019): 04038. http://dx.doi.org/10.1051/e3sconf/201911804038.

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The combustion process and pollutant emission of an annular combustion chamber for a heavy-duty gas turbine were investigated by numerical method. The realizable k-ε model and finite rate/eddy dissipation model were adopted for calculations of turbulence and combustion. The effects of different swirling numbers of the double-swirler inlet on the temperature distribution and the thermal NOx formation in the combustion chamber were analyzed. The results show that the change of the swirling number of the outer swirling flow has a greater influence on the generation of the thermal NOx when compare

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Wang, Tianyu, Jinlu Yu, Bingbing Zhao, Weida Cheng, Lei Zhang, and Yongkun Sun. "Study on plasma combustion process in aero engine combustor." Journal of Physics: Conference Series 2228, no. 1 (2022): 012034. http://dx.doi.org/10.1088/1742-6596/2228/1/012034.

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Abstract In order to explore the effect of plasma combustion on the performance of aeroengine combustion chamber, a simplified 9-Step plasma reaction mechanism was added to the 16 component 25 step reaction mechanism of aviation kerosene, and a kerosene combustion chemical reaction process model considering the excited state relaxation reaction of plasma electron collision reaction and the chemical reaction involved in excited state was established, The numerical calculation of combustion process in combustion chamber was carried out, and the numerical calculation results of combustion process

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Tian, Hua, Jingchen Cui, Tianhao Yang, Yao Fu, Jiangping Tian, and Wuqiang Long. "Experimental Research on Controllability and Emissions of Jet-Controlled Compression Ignition Engine." Energies 12, no. 15 (2019): 2936. http://dx.doi.org/10.3390/en12152936.

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Low-temperature combustions (LTCs), such as homogeneous charge compression ignition (HCCI), could achieve high thermal efficiency and low engine emissions by combining the advantages of spark-ignited (SI) engines and compression-ignited (CI) engines. Robust control of the ignition timing, however, still remains a hurdle to practical use. A novel technology of jet-controlled compression ignition (JCCI) was proposed to solve the issue. JCCI combustion phasing was controlled by hot jet formed from pre-chamber spark-ignited combustion. Experiments were done on a modified high-speed marine engine f

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Komarov, I. I., D. M. Kharlamova, A. N. Vegera та V. Y. Naumov. "Study on effect CO2 diluent on fuel cоmbustion in methane-oxygen combustion chambers". Vestnik IGEU, № 2 (30 квітня 2021): 14–22. http://dx.doi.org/10.17588/2072-2672.2021.2.014-022.

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Studying closed gas turbine cycles on supercritical carbon dioxide is currently a promising issue in the development of power energy sector in terms of increasing energy efficiency and minimizing greenhouse gas emissions into the atmosphere. Combustion of methane with oxygen in the combustion chamber occurs not in the nitrogen environment, but in the environment of carbon dioxide, that is the working fluid of the cycle, which is an inhibitor of chemical reactions. A large mass content of such a diluent of the reaction mixture in the volume of the chamber leads to the risks of significant chemi

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Hosseini, Seyed, Evan Owens, John Krohn, and James Leylek. "Experimental Investigation into the Effects of Thermal Recuperation on the Combustion Characteristics of a Non-Premixed Meso-Scale Vortex Combustor." Energies 11, no. 12 (2018): 3390. http://dx.doi.org/10.3390/en11123390.

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In small-scale combustors, the ratio of area to the combustor volume increases and hence heat loss from the combustor’s wall is significantly enhanced and flame quenching occurs. To solve this problem, non-premixed vortex flow is employed to stabilize flames in a meso-scale combustion chamber to generate small-scale power or thrust for propulsion systems. In this experimental investigation, the effects of thermal recuperation on the characteristics of asymmetric non-premixed vortex combustion are studied. The exhaust gases temperature, emissions and the combustor wall temperature are measured

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Hwang, Won-Sub, Bu-Kyeng Sung, Woojoo Han, et al. "Real-Gas-Flamelet-Model-Based Numerical Simulation and Combustion Instability Analysis of a GH2/LOX Rocket Combustor with Multiple Injectors." Energies 14, no. 2 (2021): 419. http://dx.doi.org/10.3390/en14020419.

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A large eddy simulation (LES) and combustion instability analysis are performed using OpenFOAM for the multiple shear-coaxial injector combustor DLR-BKD (in German Deutsches Zentrum für Luft–Brennkammer D, German Aerospace Center–Combustion Chamber D), which is a laboratory-scale combustor operating in a real-gas environment. The Redlich–Kwong–Peng–Robinson equation of state and steady-laminar flamelet model are adopted in the simulation to accurately capture the real-gas combustion effects. Moreover, the stable combustion under the LP4 condition is numerically analyzed, and the characteristic

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Davidović, Nikola S., Nenad M. Kolarević, Miloš B. Stanković, and Marko V. Miloš. "Research of expendable turbojet tubular combustion chamber." Advances in Mechanical Engineering 14, no. 5 (2022): 168781322210959. http://dx.doi.org/10.1177/16878132221095999.

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This paper presents research related to the tubular combustion chamber of an expendable turbojet. Although annular combustors are dominant at present, tubular combustors are still attractive because they are simpler to produce and require lower amounts of air flow for testing. The objective of this research was to assess the combustor’s primary zone configuration, and four configurations were tested to obtain experimental answers for use in future work. The configuration of the combustion chamber is a simple and classic design in line with its expendable purpose. The test methodology was to pe

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KAEWKOHKIAT, Yingyong, Smith EIAMSA-ARD, Khwanchit WONGCHAREE, D. THUNGSOTANON, and Pongjet PROMVONGE. "D102 COMBUSTION OF RICE HUSK IN A FLUIDIZED BED COMBUSTOR WITH WAVY-SURFACED CHAMBERS(Biomass-1)." Proceedings of the International Conference on Power Engineering (ICOPE) 2009.1 (2009): _1–195_—_1–199_. http://dx.doi.org/10.1299/jsmeicope.2009.1._1-195_.

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Nakata, T., M. Sato, T. Ninomiya, and T. Hasegawa. "A Study on Low NOx Combustion in LBG-Fueled 1500°C-Class Gas Turbine." Journal of Engineering for Gas Turbines and Power 118, no. 3 (1996): 534–40. http://dx.doi.org/10.1115/1.2816680.

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Developing integrated coal gasification combined-cycle systems ensures cost-effective and environmentally sound options for supplying future power generation needs. The reduction of NOx emissions and increasing the inlet temperature of gas turbines are the most significant issues in gas turbine development in Integrated Coal Gasification Combined Cycle (IGCC) power generation systems. The coal gasified fuel, which is produced in a coal gasifier of an air-blown entrained-flow type has a calorific value as low as 1/10 of natural gas. Furthermore, the fuel gas contains ammonia when a gas cleaning

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Guo, Bin, Mitsuhisa Ichiyanagi, Makoto Horie, et al. "Combustion Analysis of Ammonia/Oxygen Mixtures at Various Equivalence Ratio Conditions Using a Constant Volume Combustor with Sub-chamber." Automotive Experiences 4, no. 3 (2021): 161–70. https://doi.org/10.31603/ae.6132.

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The greenhouse effect issue is becoming more serious, and renewable energy is playing an increasingly important role. Among all alternative fuels, ammonia has been attracting attention as a carbon-free energy carrier for hydrogen, because of its large energy density per volume and easy storage and transportation. On the other hand, ammonia has a low combustion speed, which is an important issue for the use of ammonia as a vehicle fuel. To increase the mean flame speed of ammonia, the present study used the burned gas ejected from the sub-chamber for the compression of the mixture in the main c

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He, Yang, and Chul-Ho Kim. "Effect of Nozzle Port Shape of Fuel Injector of Micro Gas Turbine Engine Combustor on Mixture Gas Formation for Combustion." Fluids 7, no. 6 (2022): 184. http://dx.doi.org/10.3390/fluids7060184.

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The objective of this study was to optimize the design of the injection nozzle hole of the fuel injector of a model MGT engine. To achieve a higher combustion efficiency of the mixed gas in the combustion chamber, first, well-mixed homogeneous gas should be formed to accelerate the flame propagation in the chamber to reach a higher combustion temperature and pressure. In this study, four different shapes of the nozzle hole of the fuel injector were designed, and the mixed gas formation characteristics in the chamber were numerically analyzed. Three parameters—the penetration, diffusivity, and

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