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Journal articles on the topic 'Combustion'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

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 structur

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2

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 (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 bot

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3

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 (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 compressi

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4

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 (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 combus

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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 (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 dem

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6

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 (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 v

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7

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 (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

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8

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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9

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 (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 stud

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10

Erdiwansyah, Mahidin, Husni Husin, et al. "Combustion Efficiency in a Fluidized-Bed Combustor with a Modified Perforated Plate for Air Distribution." Processes 9, no. 9 (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

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11

PRISACARIU, Vasile, and Alexandru TUDOSIE. "CONSIDERATIONS REGARDING JET ENGINE COMBUSTOR PARAMETERS." Review of the Air Force Academy XX, no. 1 (2022): 53–63. http://dx.doi.org/10.19062/1842-9238.2022.20.1.6.

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The thermo-gas dynamics of fuel combustion in the combustor of aircraft engines involves thermochemical activity and combustion dynamics, but also the geometric volume of the combustion process. Research around the topic provides clues regarding the fluctuations of the combustor’s performance depending on the fuels used and the kinetics of the gas mixture determined by the internal geometry of the combustor, clues that can help initiate numerical approaches regarding the optimization of the mixture and combustion temperatures. The article proposes an approach to the combustion process in jet e

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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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13

Cheng, Zhe, Wen Jun Wang, Wen Qing Shen, Ai Wu Fan, and Wei Liu. "Flame Stability of Methane/Air Mixture in a Heat-Recirculating-Type Mesoscale Channel with a Bluff-Body." Applied Mechanics and Materials 325-326 (June 2013): 12–15. http://dx.doi.org/10.4028/www.scientific.net/amm.325-326.12.

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To extend the stable combustion range of micro-combustor, a heat-recirculating-type planar micro-combustor fitted with a bluff-body was proposed in the present work. Numerical simulation on CH4/air premixed combustion in this combustor was performed and the stable combustion range was determined, which showed that the blow-off limit increases with the equivalence ratio and the lower flammability limit was extended. Effect of the equivalence ratio and inlet velocity on combustion efficiency and maximum temperature were investigated. The numerical results showed that combustion efficiencies were

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14

Zhang, Qun, Hua Sheng Xu, Tao Gui, Shun Li Sun, Yue Wu, and Dong Bo Yan. "Investigation on Reaction Flow Field of Low Emission TAPS Combustors." Applied Mechanics and Materials 694 (November 2014): 45–48. http://dx.doi.org/10.4028/www.scientific.net/amm.694.45.

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A twin annular premixing swirler (TAPS) combustor model of low emissions was developed in this study. And computational studies on combustion process in the combustor model were carried out. Standard k-ε Turbulence Model, PDF non-premixed combustion model, Zeldovich thermal NOx formation model and DPM two-phase model were employed. The distributions of some key performance parameters such as gas temperature, flow velocity, concentrations of NOx and CO emissions were obtained and analyzed. At the same time, combustion mechanics inside the TAPS combustor model were investigated. The computationa

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15

Liu, C. H., R. M. Perez-Ortiz, and J. H. Whitelaw. "Vaporizer Performance." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 206, no. 4 (1992): 265–73. http://dx.doi.org/10.1243/pime_proc_1992_206_126_02.

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Measured values of fuel droplet velocity, size and flux are presented for a vaporizer based on a T-shaped duct with upstream atomization by a single axial jet and by six radial jets. They were obtained for a practical range of kerosene and air flowrates and inlet air temperatures with the vaporizer in free air and in a sector of an annular combustor with combustion. Phase Doppler velocimetry was used to measure droplet velocity and size distributions and was complemented by photographic visualization of the flames within the combustor. The results obtained outside the combustor, and without co

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16

Cowell, L. H., R. T. LeCren, and C. E. Tenbrook. "Two-Stage Slagging Combustor Design for a Coal-Fueled Industrial Gas Turbine." Journal of Engineering for Gas Turbines and Power 114, no. 2 (1992): 359–66. http://dx.doi.org/10.1115/1.2906599.

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A full-size combustor for a coal-fueled industrial gas turbine engine has been designed and fabricated. The design is based on extensive work completed through one-tenth scale combustion tests. Testing of the combustion hardware will be completed with a high pressure air supply in a combustion test facility before the components are integrated with the gas turbine engine. The combustor is a two-staged, rich-lean design. Fuel and air are introduced in the primary combustion zone where the combustion process is initiated. The primary zone operates in a slagging mode inertially removing coal ash

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17

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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18

Anand, M. S., and F. C. Gouldin. "Combustion Efficiency of a Premixed Continuous Flow Combustor." Journal of Engineering for Gas Turbines and Power 107, no. 3 (1985): 695–705. http://dx.doi.org/10.1115/1.3239791.

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Experimental data in the form of radial profiles of mean temperature, gas composition and velocity at the combustor exit and combustion efficiency are reported and discussed for a swirling flow, continuous combustor. The combustor is composed of two confined, concentric independently swirling jets: an outer, annular air jet and a central premixed fuel-air jet, the fuel being propane or methane. Combustion is stabilized by a swirl-generated central recirculation zone. The primary objective of this research is to determine the effect of fuel substitution and of changes in outer flow swirl condit

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19

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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20

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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21

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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22

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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23

Liu, Aiguo, Ruiyang Fan, Qiaochu Liu, Lei Xi, and Wen Zeng. "Numerical and Experimental Study on Combustion Characteristics of Micro-Gas Turbine Biogas Combustor." Energies 15, no. 21 (2022): 8302. http://dx.doi.org/10.3390/en15218302.

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The use of biogas in land-based gas turbines for power generation is a promising approach to reducing greenhouse gases and our dependence on fossil fuels. The focus of this research was to investigate the fuel/air mixing and combustion performance in an DLE (dry low emission) type can combustor designed for a micro-gas turbine. The fuel and air mixing uniformity was studied considering the air flow characteristic and fuel injection performance through the numerical simulation. The influence of the fuel/air mixing characteristics on the combustion characteristics was studied by numerical simula

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Cao, H. L., J. N. Zhao, K. Zhang, D. B. Wang, and X. L. Wei. "Diffusion Combustion Characteristics of H₂/Air in the Micro Porous Media Combustor." Advanced Materials Research 455-456 (January 2012): 413–18. http://dx.doi.org/10.4028/www.scientific.net/amr.455-456.413.

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In order to improve thermal to-electric energy conversion efficiency of the micro gas turbine power generation system, a novel micro porous media combustor is designed and experimental investigation on the H2/air diffusion combustion is performed to obtain its combustion characteristics. High efficiency diffusion combustion of H2/air can be stabilized in the very wide operating range, especially at higher excess air ratio. Exhaust gas temperature is markedly improved and meanwhile heat loss ratio is evidently decreased. Moreover, in the certain operating ranges, the greater the combustion ther

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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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De Giorgi, M. G., G. Cinieri, G. Marseglia, Z. Ali Shah, and Ghazanfar Mehdi. "Combustion Efficiency of Carbon-neutral Fuel using Micro-Combustor Designed for Aerospace Applications." Journal of Physics: Conference Series 2716, no. 1 (2024): 012091. http://dx.doi.org/10.1088/1742-6596/2716/1/012091.

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Abstract Recent advancements in the field of micro combustor research are growing for achieving high-performance systems in micro power generation and microelectromechanical devices. To mitigate the hazardous emissions from carbon fuels, as an alternative, zero-carbon-free fuels ammonia, and hydrogen are being explored in micro combustion processes. The distinctive feature of a micro combustor lies in its significantly higher area to volume ratio in comparison with traditional combustion systems, leading to accelerated combustion reaction rates. However, the small size of micro combustors pose

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Som, S. K., and N. Y. Sharma. "Energy and Exergy Balance in the Process of Spray Combustion in a Gas Turbine Combustor." Journal of Heat Transfer 124, no. 5 (2002): 828–36. http://dx.doi.org/10.1115/1.1484393.

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A theoretical model of exergy balance based on availability transfer and flow availability in the process of spray combustion in a gas turbine combustor has been developed to evaluate the total thermodynamic irreversibility and second law efficiency of the process at various operating conditions, for fuels with different volatilities. The velocity, temperature and concentration fields in the combustor, required for the evaluation of the flow availabilities and process irreversibilities, have been computed numerically from a two phase separated flow model of spray combustion. The total thermody

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Yang, Yao, Gaofeng Wang, Yuanqi Fang, YIfan Xia, and Liang Zhong. "IMAGING DIAGNOSTICS OF COMBUSTION INSTABILITY IN PREMIXED SWIRLING COMBUSTION." Journal of the Global Power and Propulsion Society 4 (May 22, 2020): 80–93. http://dx.doi.org/10.33737/jgpps/120536.

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An experimental study on combustion instability is presented with focus on propane-air premixed swirling flames. Swirling flames under self-excited oscillation are studied by imaging of visible light and OH* chemiluminescence filter under several typical conditions. The dynamical characteristics of swirling flames were analysed by Dynamic Mode Decomposition (DMD) method. Three types of unstable modes in the combustor system were observed, which correspond to typical acoustic resonant modes (LF mode, C1/4 mode and P1/2 mode) of the combustor system. The combustion instability is in the longitud

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Najib Aminu Ismail, Mazlan Abdul Wahid, Aminuddin Sa'at, Abubakar Shitu, and Mohammed Bashir Abdulrahman. "Effect of Recirculation Ratio on the Combustion Characteristics of an Asymmetric Swirling Flameless Combustor using Biogas." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 108, no. 1 (2023): 52–65. http://dx.doi.org/10.37934/arfmts.108.1.5265.

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This study investigates the influence of recirculation ratio on the combustion characteristics of an asymmetric swirling flameless combustor. The recirculation ratio, defined as the ratio of the total recirculation mass flow rate to the primary air mass flow rate, plays a crucial role in determining the performance and emission characteristics of combustion systems. The asymmetric swirling flameless combustor offers potential advantages in terms of enhanced fuel flexibility, reduced pollutant emissions, and improved combustion stability. Through varying the recirculation ratio, the combustion

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Lee, Jaeyoung, Chang Bum Sohn, Young Sik Jeong, and Young Bae Kim. "A Numerical Analysis of Premixed Hydrogen–Methane Flame with Three Different Header Types of Combustor." Fire 7, no. 10 (2024): 361. http://dx.doi.org/10.3390/fire7100361.

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This study investigated the impact of thin-flame combustor design on hydrogen flame characteristics and combustion performance through numerical simulations. Differences in the flame shape and combustibility between pure methane and pure hydrogen combustion were analyzed. Three combustor header shapes (flat, concave, and convex) were modeled to assess the influence of header shape on flame behavior. The results revealed distinct flow patterns, with the concave header promoting strong central flows and the convex header dispersing the flow outward. Temperature field analysis indicated that the

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Wang, Fei, Xueming Li, Shuai Feng, and Yunfei Yan. "Influence of Porous Media Aperture Arrangement on CH4/Air Combustion Characteristics in Micro Combustor." Processes 9, no. 10 (2021): 1747. http://dx.doi.org/10.3390/pr9101747.

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Micro-electro-mechanical systems (MEMS) occupy an important position in the national economy and military fields, and have attracted great attention from a large number of scholars. As an important part of the micro-electromechanical system, the micro-combustor has serious heat loss due to its small size, unstable combustion and low combustion efficiency. Aiming at enhancing the heat transfer of the micro-combustor, improving the combustion stability and high-efficiency combustion, this paper embedded porous media in the combustor, and the effects of different parameters on the combustion char

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Isvoranu, Dragos D., and Paul G. A. Cizmas. "Numerical Simulation of Combustion and Rotor-Stator Interaction in a Turbine Combustor." International Journal of Rotating Machinery 9, no. 5 (2003): 363–74. http://dx.doi.org/10.1155/s1023621x03000344.

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This article presents the development of a numerical algorithm for the computation of flow and combustion in a turbine combustor. The flow and combustion are modeled by the Reynolds-averaged Navier-Stokes equations coupled with the species-conservation equations. The chemistry model used herein is a two-step, global, finite-rate combustion model for methane and combustion gases. The governing equations are written in the strong conservation form and solved using a fully implicit, finite-difference approximation. The gas dynamics and chemistry equations are fully decoupled. A correction techniq

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Castro, Zamir Sánchez, Hugo Reinel García Bernal, and Oscar Andrés Mendieta Menjura. "Efecto del precalentamiento del aire primario y la humedad del bagazo de caña de azúcar durante la combustión en lecho fijo." Corpoica Ciencia y Tecnología Agropecuaria 14, no. 1 (2013): 5. http://dx.doi.org/10.21930/rcta.vol14_num1_art:263.

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<p>Los hornos utilizados para la elaboración de panela presentan pérdidas energéticas debido a una combustión incompleta del bagazo de caña de azúcar y al calor sensible en los gases de chimenea. Durante el proceso de producción de panela, el bagazo de caña de azúcar se utiliza como combustible, con fracciones másicas de humedad entre 30% y 50%, las cuales afectan el rendimiento de la combustión de una biomasa en lecho fijo. Gracias a que el precalentamiento del aire disminuye el tiempo de secado, su implementación en muchos sistemas de combustión de biomasa ha incrementado la eficienc

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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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Brookes, S. J., R. S. Cant, I. D. J. Dupere, and A. P. Dowling. "Computational Modeling of Self-Excited Combustion Instabilities." Journal of Engineering for Gas Turbines and Power 123, no. 2 (2001): 322–26. http://dx.doi.org/10.1115/1.1362662.

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It is well known that lean premixed combustion systems potentially offer better emissions performance than conventional non-premixed designs. However, premixed combustion systems are more susceptible to combustion instabilities than non-premixed systems. Combustion instabilities (large-scale oscillations in heat release and pressure) have a deleterious effect on equipment, and also tend to decrease combustion efficiency. Designing out combustion instabilities is a difficult process and, particularly if many large-scale experiments are required, also very costly. Computational fluid dynamics (C

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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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Sanata, Andi, Nasrul Ilminnafik, Muhammad Maulana Asyhar, Hendry Y. Nanlohy, Franciscus Xaverius Kristianta, and Imam Sholahuddin. "Characterization of Combustion in Cylindrical Meso-Scale Combustor with Wire Mesh Flame Holder as Initiation of Energy Source for Future Vehicles." Automotive Experiences 7, no. 1 (2024): 97–110. http://dx.doi.org/10.31603/ae.10715.

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The research aims to analyze and reveal combustion characteristics in a Cylindrical Meso Scale (CMS) Combustor with a wire mesh flame holder as a reference for designing a compact, efficient, and high-density energy source for future vehicles. This experiment analyzes the combustion ’s of a butane gas (C4H10)-air mixture in a cylindrical meso-scale (CMS) combustor with the addition of wire mesh flame holder on the stability of the combustion flame, as initiation of future vehicle energy source. The diameter of the CMS combustor with wire mesh flame holder is varied to give an idea of the effec

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Colantonio, R. O. "The Applicability of Jet-Shear-Layer Mixing and Effervescent Atomization for Low-NOx Combustors." Journal of Engineering for Gas Turbines and Power 120, no. 1 (1998): 17–23. http://dx.doi.org/10.1115/1.2818073.

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An investigation has been conducted to develop appropriate technologies for a low-NOx, liquid-fueled combustor. The combustor incorporates an effervescent atomizer used to inject fuel into a premixing duct. Only a fraction of the combustion air is used in the premixing process. This fuel-rich mixture is introduced into the remaining combustion air by a rapid jet-shear-layer mixing process involving radial fuel–air jets impinging on axial air jets in the primary combustion zone. Computational modeling was used as a tool to facilitate a parametric analysis appropriate to the design of an optimum

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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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Som, S. K., S. S. Mondal, and S. K. Dash. "Energy and Exergy Balance in the Process of Pulverized Coal Combustion in a Tubular Combustor." Journal of Heat Transfer 127, no. 12 (2005): 1322–33. http://dx.doi.org/10.1115/1.2101860.

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A theoretical model of exergy balance, based on availability transfer and flow availability, in the process of pulverized coal combustion in a tubular air-coal combustor has been developed to evaluate the total thermodynamic irreversibility and second law efficiency of the process at various operating conditions. The velocity, temperature, and concentration fields required for the evaluation of flow availability have been computed numerically from a two-phase separated flow model on a Eulerian-Lagrangian frame in the process of combustion of pulverized coal particles in air. The total thermody

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Claeys, J. P., K. M. Elward, W. J. Mick, and R. A. Symonds. "Combustion System Performance and Field Test Results of the MS7001F Gas Turbine." Journal of Engineering for Gas Turbines and Power 115, no. 3 (1993): 537–46. http://dx.doi.org/10.1115/1.2906741.

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This paper presents the results of the combustion system test of the MS7001F installed at the Virginia Power Chesterfield station. Tests of water and steam injection for NOx control were performed. Results of emissions, combustor dynamics, and combustor hardware performance are presented. Emissions test results include NOx, CO, unburned hydrocarbons, VOC, and formaldehyde levels. Combustor dynamic activity over a range of diluent injection ratios, and the performance of an actively cooled transition duct are also discussed. Combustion system mechanical performance is described following the fi

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Wakabayashi, T., S. Ito, S. Koga, et al. "Performance of a Dry Low-NOx Gas Turbine Combustor Designed With a New Fuel Supply Concept." Journal of Engineering for Gas Turbines and Power 124, no. 4 (2002): 771–75. http://dx.doi.org/10.1115/1.1473154.

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This paper describes the performance of a dry low-NOx gas turbine combustor designed with a new fuel supply concept. This concept uses automatic fuel distribution achieved by an interaction between the fuel jet and the airflow. At high loads, most of the fuel is supplied to the lean premixed combustion region for low-NOx, while at low loads, it is supplied to the pilot combustion region for stable combustion. A numerical simulation was carried out to estimate the equivalence ratio in the fuel supply unit. Next, through the pressurized combustion experiments on the combustor with this fuel supp

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Nair, Vineeth, and R. I. Sujith. "Multifractality in combustion noise: predicting an impending combustion instability." Journal of Fluid Mechanics 747 (April 23, 2014): 635–55. http://dx.doi.org/10.1017/jfm.2014.171.

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AbstractThe transition in dynamics from low-amplitude, aperiodic, combustion noise to high-amplitude, periodic, combustion instability in confined, combustion environments was studied experimentally in a laboratory-scale combustor with two different flameholding devices in a turbulent flow field. We show that the low-amplitude, irregular pressure fluctuations acquired during stable regimes, termed ‘combustion noise’, display scale invariance and have a multifractal signature that disappears at the onset of combustion instability. Traditional analysis often treats combustion noise and combustio

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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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Cheng, Yuwei, Qian Chen, Xiaofei Niu, and Shufeng Cai. "Large Eddy Simulation and Dynamic Mode Decomposition of Supersonic Combustion Instability in a Strut-Based Scramjet Combustor." Aerospace 10, no. 10 (2023): 857. http://dx.doi.org/10.3390/aerospace10100857.

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Supersonic combustion instability studies are crucial for the future maturation of scramjet engines. In the present paper, the supersonic combustion instability in a strut-based scramjet combustor is investigated through large eddy simulation and dynamic mode decomposition. The results show significant pressure oscillation in the strut-based scramjet combustor when the air parameters at the combustor inlet and the fuel parameters at the injector outlet are under certain conditions, and these pressure oscillation situations correspond to supersonic combustion instability. The oscillations have

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Yang, Pengnian, Zhixun Xia, Likun Ma, et al. "Influence of the Multicavity Shape on the Solid Scramjet." International Journal of Aerospace Engineering 2021 (October 26, 2021): 1–14. http://dx.doi.org/10.1155/2021/9718537.

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In this paper, a modular solid scramjet combustor with multicavity was proposed. The influence of multicavity shape on the performance of solid scramjet was investigated by the direct-connected tests. The experiments simulated a flight Mach 5.5 at 25 km. The boron-based fuel-rich propellant was used. The microstructure of combustion products was analyzed by SEM. The experimental results show that the fuel-rich mixture produced by the gas generator would ignite rapidly in the solid scramjet combustor. The combustion process showed a typical characteristic of establishment-development-maintenanc

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Wang, Yue, Minqi Zhang, Shuhang Chang, Shengji Li, and Xuefeng Huang. "Laser-Induced Ignition and Combustion Behavior of Individual Graphite Microparticles in a Micro-Combustor." Processes 8, no. 11 (2020): 1493. http://dx.doi.org/10.3390/pr8111493.

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Microscale combustion has potential application in a micro power generator. This paper studied the ignition and combustion behavior of individual graphite microparticles in a micro-combustor to explore the utilization of carbon-based fuels at the microscale system. The individual graphite microparticles inside the micro-combustor were ignited by a highly focused laser in an air flow with natural convection at atmospheric temperature and pressure. The results show that the ignition of graphite microparticles was heterogeneous. The particle diameter had a small weak effect on ignition delay time

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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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Mat Zian, Norhaslina, Hasril Hasini, and Nur Irmawati Om. "Preliminary CFD Investigation of Syngas Combustion at Different Operating Pressures." Applied Mechanics and Materials 786 (August 2015): 215–19. http://dx.doi.org/10.4028/www.scientific.net/amm.786.215.

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Study on the flow and combustion behavior inside gas turbine combustor used in thermal power plant is described in this paper. The combustion process takes place using synthetic gas and emphasis is given to the effect of pressure variation on flame profile, temperature distribution and emissions as compared to the conventional combustion using methane. The operating pressure of the can-type combustor varies in the range of 1-10 atm. while the syngas composition is assumed to have fixed values of 10% CH4, 55% CO, 30% H2 and 5% N2. Preliminary result shows that the flow inside the can-combustor

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Mat Zian, Norhaslina, Hasril Hasini, and Nur Irmawati Om. "Preliminary CFD Investigation of Syngas Combustion at Different Operating Pressure." Applied Mechanics and Materials 819 (January 2016): 277–81. http://dx.doi.org/10.4028/www.scientific.net/amm.819.277.

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Study on the flow and combustion behavior inside gas turbine combustor used in thermal power plant is described in this paper. The combustion process takes place using synthetic gas and emphasis is given to the effect of pressure variation on flame profile, temperature distribution and emissions as compared to the conventional combustion using methane. The operating pressure of the can-type combustor varies in the range of 1-10 atm. while the syngas composition is assumed to have fixed values of 10% CH4, 55% CO, 30% H2 and 5% N2. Preliminary result shows that the flow inside the can-combustor

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