Relevant bibliographies by topics / Adiabatic Flame Temperature

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Adiabatic Flame Temperature'

Author: Grafiati
Published: 4 June 2021
Last updated: 11 February 2022

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Journal articles on the topic "Adiabatic Flame Temperature"

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Sakhrieh, Ahmad. "The adiabatic flame temperature and laminar flame speed of methane premixed flames at varying pressures." Acta Periodica Technologica, no. 50 (2019): 220–27. http://dx.doi.org/10.2298/apt1950220s.

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This paper studies the influence of equivalence ratio, pressure and initial temperature on adiabatic flame temperature and laminar flame speed of methane-air mixture. The results indicate that adiabatic flame temperature is weakly correlated with pressure. The adiabatic flame temperature increases only by about 50?C as a result of 30 bar pressure increase. The flame speed is inversely proportional to pressure. The maximum adiabatic flame temperature and flame speed occur at the stoichiometric ratio, ?=1. The percent increase in the flame speed was about 400% when the initial temperature of the mixture is increased from 25?C to 425?C.
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Lee, Dae-Hee, and B. Bollinger. "The Development of Combustion Laboratory Test Apparatus for Mechanical Engineers." International Journal of Mechanical Engineering Education 24, no. 1 (January 1996): 1–10. http://dx.doi.org/10.1177/030641909602400101.

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A combustion laboratory test apparatus has been developed and put to use in the mechanical engineering measurement course at the California State University, Sacramento. The objectives of this apparatus are to study the characteristics of a premixed flame for a range if air/propane mixtures (from near stoichiometric to rich to highly rich) and to examine the principles of chemical thermodynamics of combustion by comparing the calculated adiabatic flame temperature to the measured adiabatic flame temperature, and by doing an energy balance on the flame. The apparatus consists of a burner that is used to ignite a regulated air/propane mixture. A thin wire thermocouple is used to measure both the flame temperature profiles and the adiabatic flame temperatures for two different air/propane mixtures (rich and highly rich). Furthermore, a copper tank containing water is heated by a near-stoichiometric mixture flame, causing heat transfer from the flame to the water. The results show that approximately 83% of the heat released from the near stoichiometric flame is transferred to the water in the copper tank.
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Conroy, P. J., P. Weinacht, and M. J. Nusca. "Parametric Erosion Investigation: Propellant Adiabatic Flame Temperature." Defence Science Journal 52, no. 1 (January 1, 2002): 77–85. http://dx.doi.org/10.14429/dsj.52.2152.

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Shehata, Mohamed S., Mohamed M. ElKotb, and Hindawi Salem. "Combustion Characteristics for Turbulent Prevaporized Premixed Flame Using Commercial Light Diesel and Kerosene Fuels." Journal of Combustion 2014 (2014): 1–17. http://dx.doi.org/10.1155/2014/363465.

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Experimental study has been carried out for investigating fuel type, fuel blends, equivalence ratio, Reynolds number, inlet mixture temperature, and holes diameter of perforated plate affecting combustion process for turbulent prevaporized premixed air flames for different operating conditions. CO2, CO, H2, N2, C3H8, C2H6, C2H4, flame temperature, and gas flow velocity are measured along flame axis for different operating conditions. Gas chromatographic (GC) and CO/CO2infrared gas analyzer are used for measuring different species. Temperature is measured using thermocouple technique. Gas flow velocity is measured using pitot tube technique. The effect of kerosene percentage on concentration, flame temperature, and gas flow velocity is not linearly dependent. Correlations for adiabatic flame temperature for diesel and kerosene-air flames are obtained as function of mixture strength, fuel type, and inlet mixture temperature. Effect of equivalence ratio on combustion process for light diesel-air flame is greater than for kerosene-air flame. Flame temperature increases with increased Reynolds number for different operating conditions. Effect of Reynolds number on combustion process for light diesel flame is greater than for kerosene flame and also for rich flame is greater than for lean flame. The present work contributes to design and development of lean prevaporized premixed (LPP) gas turbine combustors.
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Ugarte, Orlando J., and V’yacheslav Akkerman. "Computational Study of Premixed Flame Propagation in Micro-Channels with Nonslip Walls: Effect of Wall Temperature." Fluids 6, no. 1 (January 11, 2021): 36. http://dx.doi.org/10.3390/fluids6010036.

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This investigation evaluates the propagation of premixed flames in narrow channels with isothermal walls. The study is based on the numerical solution of the set of fully-compressible, reacting flow equations that includes viscosity, diffusion, thermal conduction and Arrhenius chemical kinetics. Specifically, channels and pipes with one extreme open and one extreme closed are considered such that a flame is sparked at the closed extreme and propagates towards the open one. The isothermal channel walls are kept at multiple constant temperatures in the range from Tw=300 K to 1200 K. The impact of these isothermal walls on the flame dynamics is studied for multiple radii of the channel (R) and for various thermal expansion ratios (Θ), which approximate the thermal behavior of different fuel mixtures in the system. The flame dynamics in isothermal channels is also compared to that with adiabatic walls, which were previously found to produce exponential flame acceleration at the initial stage of the burning process. The results show that the heat losses at the walls prevent strong acceleration and lead to much slower flame propagation in isothermal channels as compared to adiabatic ones. Four distinctive regimes of premixed burning in isothermal channels have been identified in the Θ−Tw−R space: (i) flame extinction; (ii) linear flame acceleration; (iii) steady or near-steady flame propagation; and (iv) flame oscillations. The physical processes in each of these regimes are discussed, and the corresponding regime diagrams are presented.
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JU, YIGUANG, HONGSHENG GUO, KAORU MARUTA, and FENGSHAN LIU. "On the extinction limit and flammability limit of non-adiabatic stretched methane–air premixed flames." Journal of Fluid Mechanics 342 (July 10, 1997): 315–34. http://dx.doi.org/10.1017/s0022112097005636.

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Extinction limits and the lean flammability limit of non-adiabatic stretched premixed methane–air flames are investigated numerically with detailed chemistry and two different Planck mean absorption coefficient models. Attention is paid to the combined effect of radiative heat loss and stretch at low stretch rate. It is found that for a mixture at an equivalence ratio lower than the standard lean flammability limit, a moderate stretch can strengthen the combustion and allow burning. The flame is extinguished at a high stretch rate due to stretch and is quenched at a low stretch rate due to radiation loss. A O-shaped curve of flame temperature versus stretch rate with two distinct extinction limits, a radiation extinction limit and a stretch extinction limit respectively on the left- and right-hand sides, is obtained. A C-shaped curve showing the flammability limit of the stretched methane–air flame is obtained by plotting these two extinction limits in the mixture strength coordinate. A good agreement is shown on comparing the predicted results with the experimental data. For equivalence ratio larger than a critical value, it is found that the O-shaped temperature curve opens up in the middle of the stable branch, so that the stable branch divides into two stable flame branches; a weak flame branch and a normal flame branch. The weak flame can survive between the radiation extinction limit and the opening point (jump limit) while the normal flame branch can survive from its stretch extinction limit to zero stretch rate. Finally, a G-shaped curve showing both extinction limits and jump limits of stretched methane–air flames is presented. It is found that the critical equivalence ratio for opening up corresponds to the standard flammability limit measured in microgravity. Furthermore, the results show that the flammability limit (inferior limit) of the stretched methane–air flame is lower than the standard flammability limit because flames are strengthened by a moderate stretch at Lewis number less than unity.
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Jeon, Min-Kyu, and Nam Il Kim. "Fuel pyrolysis and its effects on soot formation in non-premixed laminar jet flames of methane, propane, and DME." Mathematical Modelling of Natural Phenomena 13, no. 6 (2018): 56. http://dx.doi.org/10.1051/mmnp/2018052.

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High-temperature combustion techniques have recently attracted interest with regard to the improvement of the thermal efficiency of combustion systems. Fuel pyrolysis is an important factor, as it can affect such flame structures at high temperatures. In this study, the pyrolysis of methane, propane, and dimethyl ether (DME) was measured and the results were compared with theoretical predictions. Pyrolyzed fuels were quenched to room temperature before being introduced onto the burner. Thus, the pyrolysis effects on laminar non-premixed jet flames could be distinguished from many other complex thermal effects. It was found that the flame length was not notably extended in spite of the great increase in the volumetric flow rates resulting from the pyrolysis. In contrast, fuel pyrolysis could significantly affect the soot formation process,and the number of smoke points could be sharply reduced depending on the pyrolysis temperature. Distributions of the luminous intensity and scattering intensity levels in the soot region were discussed in terms of the soot temperatures obtained with a two-color method. Although the adiabatic flame temperatures of the pyrolyzed fuels were theoretically increased, the actual soot temperatures could be reduced when the soot particles were excessively formulated, as in the case with propane flames.
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Aljerf, Loai, and Nuha AlMasri. "Flame Propagation Model and Combustion Phenomena: Observations, Characteristics, Investigations, Technical Indicators, and Mechanisms." Journal of Energy Conservation 1, no. 1 (July 30, 2018): 31–40. http://dx.doi.org/10.14302/issn.2642-3146.jec-18-2232.

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Critical conditions are usually obtained for ignition in a self-heating solid system consisting of two components generating heat independently, one component being inexhaustible and the other exhaustible by either simple first order or autocatalytic reaction. Ignition depends upon whether the exhaustible component can cause a temperature rise in excess of the upper stationary, but unstable, value possible for the inexhaustible component reacting alone. The system provides a theoretical model for some commonly occurring examples of self-heating and ignition in porous solids containing oxidisable oils. It is shown that: (a) the ignition criterion of the model, which involves a nonarbitrary critical temperature increase, has a high degree of physical reality; (b) the model is, in principle, capable of predicting ignition from primary kinetic and thermal data; (c) it is likely to be possible often to make a reliable prediction of critical size for self-ignition in a two-component system at ordinary atmospheric temperatures by a simple extrapolation from small-scale ignition data, obtained at higher temperatures, in the same way as for ignition due to a single reaction. Examination of both adiabatic and non-adiabatic flame theories showed that a 'steady state' exists only under the special condition that a heat sink exists at the initial temperature. For the general case of freely propagating, non-adiabatic flames only a quasi-steady state can be achieved.
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Abe, Keisuke, Ade Kurniawan, Masafumi Sanada, Takahiro Nomura, and Tomohiro Akiyama. "Combustion Synthesis Ironmaking: Investigation on Required Carbon Amount in Raw Material from the Viewpoint of Adiabatic Flame Temperature Calculation." Indonesian Journal of Chemistry 19, no. 3 (May 29, 2019): 696. http://dx.doi.org/10.22146/ijc.38359.

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Combustion synthesis (CS) is a simple and very fast method to synthesize a target material. New ironmaking method via the CS using carbon-infiltrated iron ore was proposed, and the possible conditions for the method were investigated. Adiabatic flame temperatures (Tad) of the CS reaction, maximum reachable temperatures in an adiabatic system, were calculated to estimate the sample temperature during the CS. To reach the adiabatic temperature of 1811 K, 23.9, 27.9, and 29.3 wt.%-C were required for Fe2O3, Fe3O4, and FeO, respectively. When the carbon amount is higher than the calculated one, molten iron which is separated from slag components should be obtained via the CS.
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Yue, Meng, Mao-Zhao Xie, Jun-Rui Shi, Hong-Sheng Liu, Zhong-Shan Chen, and Ya-Chao Chang. "Numerical and Experimental Investigations on Combustion Characteristics of Premixed Lean Methane–Air in a Staggered Arrangement Burner with Discrete Cylinders." Energies 13, no. 23 (December 3, 2020): 6397. http://dx.doi.org/10.3390/en13236397.

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Premixed combustion of lean methane–air in an artificial porous media burner with staggered alumina cylinders was experimentally and numerically performed. Numerical simulations were conducted at gas mixture velocities of 0.43–0.86 m/s and equivalence ratios of 0.162 and 0.243, respectively. Through comparison with experimental results, temperature distribution, peak temperature and flame propagation velocity are analyzed and discussed in detail. The numerical calculated temperature profile over the axis of the combustor coincided well with test data in the post-flame zone, however a certain deviation was found in the preheated zone. A two-dimensional flame shape was observed and the flame thickness was the size of cylinder diameter. The peak temperature increased with the gas mixture inlet velocity at the certain equivalence ratio, and its peak value was about 1.8–2.16 times higher than the adiabatic combustion temperature under the desired equivalence ratio, which indicates that super-adiabatic combustion was the case for all the numerical simulations. The flame propagating velocity had a positive correlation with the gas mixture inlet velocity.
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Dissertations / Theses on the topic "Adiabatic Flame Temperature"

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Virk, Akashdeep Singh. "Heat Transfer Characterization in Jet Flames Impinging on Flat Plates." Thesis, Virginia Tech, 2015. http://hdl.handle.net/10919/52985.

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The experimental work involves calculation of radial distribution of heat transfer coefficient at the surface of a flat Aluminium plate being impinged by a turbulent flame jet. Heat transfer coefficient distribution at the surface is computed from the measured heat flux and temperature data using a reference method and a slope method. The heat transfer coefficient (h) has a nearly bell shaped radial distribution at the plate surface for H/d =3.3. The value of h drops by 37 % from r/d =0 to r/d= 2. Upon increasing the axial distance to H/d = 5, the stagnation point h decreased by 15%. Adiabatic surface temperature (AST) distribution at the plate surface was computed from the measured heat flux and temperature. AST values were found to be lower than the measured gas temperature values at the stagnation point. Radial distribution of gas temperature at the surface was estimated by least squares linear curve fitting through the convection dominated region of net heat flux data and was validated by experimental measurements with an aspirated thermocouple. For low axial distances (H/d =3.3), the gas temperature dropped by only 15 % from r/d = 0 to r/d = 2. Total heat flux distribution is separated into radiative and convective components with the use of calculated heat transfer coefficient and estimated gas temperatures. At H/d = 3.3, the radiation was found to be less than 25 % of the net heat flux for r/d ≤ 2.
Master of Science
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Le, Thuy Minh Hai. "Flammability Characteristics of Hydrogen and Its Mixtures with Light Hydrocarbons at Atmospheric and Sub-atmospheric Pressures." Thesis, 2013. http://hdl.handle.net/1969.1/150966.

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Knowledge of flammability limits is essential in the prevention of fire and explosion. There are two limits of flammability, upper flammability limit (UFL) and lower flammability limit (LFL), which define the flammable region of a combustible gas/vapor. This research focuses on the flammability limits of hydrogen and its binary mixtures with light hydrocarbons (methane, ethane, n-butane, and ethylene) at sub-atmospheric pressures. The flammability limits of hydrogen, light hydrocarbons, and binary mixtures of hydrogen and each hydrocarbon were determined experimentally at room temperature (20ºC) and initial pressures ranging from 1.0 atm to 0.1 atm. The experiments were conducted in a closed cylindrical stainless steel vessel with upward flame propagation. It was found that the flammable region of hydrogen initially widens when the pressure decreases from 1.0 atm to 0.3 atm, then narrows with the further decrease of pressure. In contrast, the flammable regions of the hydrocarbons narrow when the pressure decreases. For hydrogen and the hydrocarbons, pressure has a much greater impact on the UFLs than on the LFLs. For binary mixtures of hydrogen and the hydrocarbons, the flammable regions of all mixtures widen when the fraction of hydrogen in the mixture increases. When the pressure decreases, the flammable regions of all mixtures narrow. The applications of Le Chatelier’s rule and the Calculated Adiabatic Flame Temperature (CAFT) model to the flammability limits of the mixtures were verified. It was found that Le Chatelier’s rule could predict the flammability limits much better than the CAFT model. The adiabatic flame temperatures (AFTs), an important parameter in the risk assessment of fire and explosion, of hydrogen and the hydrocarbons were also calculated. The influence of sub-atmospheric pressures on the AFTs was investigated. A linear relationship between the AFT and the corresponding flammability limit is derived. Furthermore, the consequence of fire relating to hydrogen and the hydrocarbons is discussed based on the AFTs of the chemicals.
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Chang, Chih-Heng, and 張智恒. "Estimating the inerting effect on combustible mixtures consisting of carbon, hydrogen, oxygen by using theoretical adiabatic flame temperature." Thesis, 2010. http://ndltd.ncl.edu.tw/handle/54019350200307077851.

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碩士
中國醫藥大學
職業安全衛生學系碩士班
98
This study proposed a model to estimate inerting effect on flammability limits for organic compounds made up of carbon, hydrogen and oxygen. The energy balance and assumption of constant adiabatic flame temperature were used to establish model. Methane, propane, isobutane, ethylene, propylene, methyl formate, dimethyl ether, methanol and acetone were selected as examples to validate the proposed model. Nitrogen, carbon dioxide, water, 1,1,1,2,2-pentafluoroethane (HFC-125) and chloroform (CHCl3) were used as inert. The mean absolute relative deviations between predictions and experiments are both less 10 % at LFL and UFL, but over estimating the LOC. Our results reveal that combustion products transfer from CO to CO2 should not be ignored in the prediction of UFL, otherwise the deviations would be considerable. Overall, the estimated results of this proposed model describe the experimental data well, except the case of adding to HFC-125 or CHCl3 flammable mixture. We suggest that at least four points and the actual compositions of products at UFL are required for precisely predicting the flammable zone. In addition to academic values, the results will be applicable in preventing the fires and explosions in real process, and can reduce the risk of fire and explosion in normal operation, storage, and transportation of materials
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Book chapters on the topic "Adiabatic Flame Temperature"

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Zhao, Ran, Hao Liu, Xiaojiao Zhong, Zijian Wang, Ziqin Jin, Yingming Chen, and Jianrong Qiu. "The Ignition Delay, Laminar Flame Speed and Adiabatic Temperature Characteristics of n-Pentane, n-Hexane and n-Heptane Under O2/CO2 Atmosphere." In Cleaner Combustion and Sustainable World, 57–63. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-30445-3_10.

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Kara, Ozan, and Arif Karabeyoglu. "Hybrid Propulsion System: Novel Propellant Design for Mars Ascent Vehicles." In Propulsion - New Perspectives and Applications [Working Title]. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.96686.

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This chapter briefly introduces hybrid rocket propulsion for general audience. Advantageous of hybrid rockets over solids and liquids are presented. This chapter also explains how to design a test setup for hybrid motor firings. Hybrid propulsion provides sustainable, safe and low cost systems for space missions. Therefore, this chapter proposes hybrid propulsion system for Mars Ascent Vehicles. Paraffin wax is the fuel of the rocket. Propulsion system uses CO2/N2O mixture as the oxidizer. The goal is to understand the ignition capability of the CO2 as an in-situ oxidizer on Mars. CO2 is known as major combustion product in the nature. However, it can only burn with metallic powders. Thus, metallic additives are added in the fuel grain. Results show that CO2 increase slows down the chemical kinetics thus reduces the adiabatic flame temperature. Maximum flammability limit is achieved at 75% CO2 by mass in the oxidizer mixture. Flame temperature is 1700 K at 75% CO2. Ignition quenches below the 1700 K.
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"Adiabatic Flame Temperatures of Hydrocarbons." In Combustion, 653–57. Elsevier, 2008. http://dx.doi.org/10.1016/b978-0-12-088573-2.00015-4.

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"Adiabatic flame temperatures of hydrocarbons." In Combustion, 651–53. Elsevier, 2015. http://dx.doi.org/10.1016/b978-0-12-407913-7.15003-0.

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Martinho Simões, José A., and Manuel Minas da Piedade. "Overview of Condensed Phase Methods." In Molecular Energetics. Oxford University Press, 2008. http://dx.doi.org/10.1093/oso/9780195133196.003.0010.

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This part includes a discussion of the main experimental methods that have been used to study the energetics of chemical reactions and the thermodynamic stability of compounds in the condensed phase (solid, liquid, and solution). The only exception is the reference to flame combustion calorimetry in section 7.3. Although this method was designed to measure the enthalpies of combustion of substances in the gaseous phase, it has very strong affinities with the other combustion calorimetric methods presented in the same chapter. Most published enthalpies of formation and reaction in the condensed phase were determined by calorimetry (see databases indicated in appendix B). It is therefore not surprising that the discussion of calorimetric methods occupies a large fraction of part II. The heart of a calorimeter is the calorimeter proper (also called measuring system or sample cell), which contains the reaction vessel, where the chemical reaction or phase transition under study occurs. Sometimes the calorimeter proper coincides with the reaction vessel. For example, in the setup shown in figure 6.1a, which is typical of many combustion calorimeters, the reaction vessel is placed inside the calorimeter proper. In the arrangement of figure 6.1b, used in many reaction-solution calorimeters, the calorimeter proper is also the reaction vessel. Normally, a controlled-temperature jacket surrounds the calorimeter proper. Other parts besides thermometers, commonly found in calorimeters, are stirring, heating, cooling, and ignition devices. Some of these devices are placed inside the calorimeter proper or cross its boundaries and are also considered to be part of it. In modern instruments, the data acquisition and many steps of the calorimetric experiments are usually computer-controlled. Calorimeters of many different designs have been constructed and operated. However, these are all variations of a few basic categories. For example, based on the heat exchange mode between the calorimeter proper and the surrounding jacket, it is convenient to distinguish three main classes of calorimeters: adiabatic, heat conduction, and isoperibol. In a perfectly adiabatic calorimeter no heat is transferred between the calorimeter proper and the jacket (the corresponding heat flow rate Φ = dQ/dt = 0, where Q represents the heat exchanged and t is time).
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Conference papers on the topic "Adiabatic Flame Temperature"

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Lilley, David. "Adiabatic Flame Temperature Calculation." In 1st International Energy Conversion Engineering Conference (IECEC). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-5979.

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Lilley, David. "Adiabatic Flame Temperature Calculation: A Simple Approach for General CHONS Fuels." In 42nd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-817.

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Dülger, Zafer. "Adiabatic Flame Temperature and Product Composition for Lean Combustion of Hydrogen-Methane Combination." In ASME 1994 International Computers in Engineering Conference and Exhibition and the ASME 1994 8th Annual Database Symposium collocated with the ASME 1994 Design Technical Conferences. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/cie1994-0460.

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Abstract Adiabatic combustion of methane (natural gas)-hydrogen mixtures is analyzed The adiabatic flame temperature and products composition (especially NOx and CO2 concentrations) variation with excess air (fuel-air equivalence ratio), hydrogen enrichment of methane, and reactant temperature is determined It is shown that reductions in NOx and CO2 emissions are possible with the extended lean limit of combustion of methane associated with hydrogen enrichment CO2 concentrations are also reduced with hydrogen enrichment, reductions being dependent upon the degree of enrichment.
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Boyde, Jan Michael, Andreas Fiolitakis, Massimiliano Di Domenico, and Manfred Aigner. "Correlations for the Laminar Flame Speed, Adiabatic Flame Temperature and Ignition Delay Time for Methane, Ethanol and n-Decane." In 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-510.

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Tourlidakis, A., and A. Malkogianni. "Influence of the Air Preheat Temperature and the Fuel Preheat Temperature in the Adiabatic Flame Temperature for Gaseous Fuels of Low Heating Value." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-69977.

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Adiabatic flame temperature is of significant importance for the design of a GT combustor, as it is the temperature under the condition of no heat loss takes place from the combustion system. This importance arises from the fact that it plays an important role in the pollutants emitted from the system, such as carbon oxides and nitrogen oxides. Additionally, the temperature also affect the thermal stresses set up in the combustion system, such stress may lead to the deterioration of the chamber if not well controlled. Consequently, it is essential before the construction of the combustion chamber, a simulation process for the temperature distribution within the combustion system to be carried out, in order to avoid local thermal stresses and to minimize nitrogen oxides and carbon dioxides emissions, pollutants of great concern, that are very dependent on the flame temperature. The factors that predominantly affect the adiabatic flame temperature are the fuel heating value, the type of oxidant, FAR, the temperature of the reactants, the amount of oxygen in the air, as well as the dissociation phenomena. In this study, a code in FORTRAN programming language is developed for the calculation of the adiabatic flame temperature. The simulation is performed for different gaseous fuels of low calorific value, for air preheat, for fuel preheat, as well as for various Φ. From the simulation resulted that Tad and Φ for each fuel are totally dependent on the fuel’s calorific value. Both for the case of the air preheat, and the fuel preheat temperature it was observed increase of the Tad. Preheating of combustible mixture by recycling heat from flue gases has been considered an effective technology not only for combustion of low calorific fuels but also for fuel conservation.
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Kim, H. S., V. K. Arghode, and A. K. Gupta. "Hydrogen Addition Effects on Swirl Stabilized Methane Flame." In ASME 2007 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/detc2007-34133.

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Effect of hydrogen addition in methane-air premixed flames has been examined from a swirl stabilized combustor under confined flame conditions. Different swirlers have been examined to investigate the effect of swirl intensity on enriching methane-air flame with hydrogen in a laboratory-scale pre-mixed combustor operated at 5.81 kW. The flame stability was examined at same head load (5.81 kW) for various parameters such as amount of hydrogen addition, combustion air flow rates and swirl strengths. This was done by comparing adiabatic flame temperatures at the lean flame limit. The combustion characteristics of hydrogen enriched methane flames at constant heat load but different swirl strength were examined using particle image velocimetry (PIV), OH chemiluminescence, micro-thermocouples diagnostics to provide information on velocity and temperature field, and combustion generated OH concentration in the flame. Gas analyzer was used to obtain NOx and CO concentration at the exit. The results show that the the lean stability limit is mostly extended by hydrogen addition, but it can reduce in case of higher swirl intensity operating at lower adiabatic flame temperatures. The addition of hydrogen increases the NOx emission; however, this effect can be reduced by increasing either the excess air or swirl intensity. The results of NOx and CO emissions were also compared with a diffusion flame type combustor. The NOx emissions of hydrogen enriched methane premixed flame was found to be lower than the corresponding diffusion flame under the fuel lean condition.
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Prakash, Shaurya, and Yin Fee Phang. "High Temperature Microsystems: Recent Advances in Microcombustion." In ASME 2009 7th International Conference on Nanochannels, Microchannels, and Minichannels. ASMEDC, 2009. http://dx.doi.org/10.1115/icnmm2009-82146.

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Recent times have seen a growing interest in developing next generation energy systems and devices for building very small engines, power plants, and high temperature microchemical reactors, all running on the combustion of hydrocarbon fuels due to their inherently high energy densities. In particular, much interest lies in creating small-scale fuel reformers to produce hydrogen and/or syngas for fuel cells. Over the past decade, most microscale combustion systems that have been developed employ catalytic and heterogeneous combustion processes. In this paper, discussion towards the development of sub-millimeter or microscale homogeneous combustion systems operating at high temperatures, which can approach adiabatic flame temperatures, to achieve potentially high power densities (∼ 103 W/cm3) will be presented. Results from previous work are summarized to discuss the role and importance of surfaces in creating and sustaining homogeneous flames in narrow, confined structures with channel dimensions as small as 100 μm. At these length scales, some unusual flame structures and flame dynamics have been observed that vary strongly with changes in boundary conditions. This paper reviews recent experimental and computational data, observations of flame structure and dynamics, and discusses several open questions that remain to be answered.
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Zhang, Qingguo, David R. Noble, Andrew Meyers, Kunning Xu, and Tim Lieuwen. "Characterization of Fuel Composition Effects in H2/CO/CH4 Mixtures Upon Lean Blowout." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68907.

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This paper describes measurements of the dependence of lean blowout limits upon fuel composition for H2/CO/CH4 mixtures. Blowout limits were obtained at fixed approach flow velocity, reactant temperature, and combustor pressure at several conditions up to 4.4 atm and 470 K inlet reactants temperature. Consistent with prior studies, these results indicate that the percentage of H2 in the fuel dominates the mixture blowoff characteristics. That is, flames can be stabilized at lower equivalence ratios, adiabatic flame temperatures, and laminar flame speeds with increasing H2 percentage. Various methods of correlating these data were evaluated, using combinations of Lewis number (Lemix), adiabatic flame temperature (Tad), flame speed (SL), and chemical time (τchem). These correlations clearly indicate the significance of the mixture diffusivity, heat content, and flame propagation speed upon blowout characteristics across a wide fuel spectrum. Two basic models of flame stabilization discussed in the literature were evaluated — a well-stirred reactor based approach that considers the ratio of chemical and flow times, and a propagative mechanism that considers the ratio of flame and flow speed. Both mechanisms were able to correlate some, but not all segments of the data set.
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9

Dong, Mingchun, and David G. Lilley. "Impinging Flame Prediction for CVD Diamond Synthesis." In ASME 1993 International Computers in Engineering Conference and Exposition. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/cie1993-0056.

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Abstract High-temperature flames impinging normally onto adiabatic surfaces are considered. These are important in the CVD (chemical vapor deposition) diamond synthesis method for diamond growth on surfaces. Problems of complex chemistry and the mechanism of diamond growth are discussed. The present paper has illustrated the effects of several key parameters on the substrate surface temperature and flowfield for CVD diamond synthesis by impinging oxy-acetylene jet flames. The studies were concerned with combustion flowfield predictions, oxy-acetylene flames, axisymmetric-vertical impingement on an adiabatic surface, and the effects of varying the nozzle-substrate separation distance, nozzle size, overall equivalence ratio and flow rate on the substrate surface temperature and flowfield. This investigation provides a key to linking the flame with diamond growth rate on the substrate surface, complements the other facets of the project, and shows that the parametric influences can be predicted with relative ease, thereby extending the range of previously found experimental data.
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10

Watanabe, Hirotatsu, Santosh J. Shanbhogue, and Ahmed F. Ghoniem. "Impact of Equivalence Ratio on the Macrostructure of Premixed Swirling CH4/Air and CH4/O2/CO2 Flames." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43224.

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Premixed CH4/O2/CO2 flames (oxy-flames) and CH4/air flames (air-flames) were experimentally studied in a swirl-stabilized combustor. For comparing oxy and air flames, the same equivalence ratio and adiabatic flame temperature were used. CO2 dilution was adjusted to attain the same adiabatic temperature for the oxy-flame and the corresponding air-flame while keeping the equivalence ratio and Reynolds number (=20,000) the same. For high equivalence ratios, we observed flames stabilized along the inner and outer shear layers of the swirling flow and sudden expansion, respectively, in both flames. However, one notable difference between the two flames appears as the equivalence ratio reaches 0.60. At this point, the outer shear layer flame disappears in the air-flame while it persists in the oxy-flame, despite the lower burning velocity of the oxy-flame. Prior PIV measurements (Ref. 9) showed that the strains along the outer shear layer are higher than along the inner shear layer. Therefore, the extinction strain rates in both flames were calculated using a counter-flow premixed twin flame configuration. Calculations at the equivalence ratio of 0.60 show that the extinction strain rate is higher in the oxy than in the air flame, which help explain why it persists on the outer shear layer with higher strain rate. It is likely that extinction strain rates contribute to the oxy-flame stabilization when air flame extinguish in the outer shear layer. However, the trend reverses at higher equivalence ratio, and the cross point of the extinction strain rate appears at equivalence ratio of 0.64.
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