High Temperature Shock Tube Ignition Studies of CO2́2 Diluted Mixtures PDF Download
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Author: Owen Marcus Pryor
Publisher:
ISBN:
Category :
Languages : en
Pages : 66
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Book Description
Experimental data for ignition delay times and species time-histories (CH4) were obtained in mixtures diluted with CO2. Experiments were performed behind reflected shockwaves from temperatures of 1200 to 2000 K for pressures ranging from 1 to 11 atm. Ignition times were obtained from emission and laser absorption measurements. Current experimental data were compared with the predictions of detailed chemical kinetic models (available from literature) that will allow for accurate design and modeling of combustion systems.
Author: Owen Marcus Pryor
Publisher:
ISBN:
Category :
Languages : en
Pages : 66
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Book Description
Experimental data for ignition delay times and species time-histories (CH4) were obtained in mixtures diluted with CO2. Experiments were performed behind reflected shockwaves from temperatures of 1200 to 2000 K for pressures ranging from 1 to 11 atm. Ignition times were obtained from emission and laser absorption measurements. Current experimental data were compared with the predictions of detailed chemical kinetic models (available from literature) that will allow for accurate design and modeling of combustion systems.
Author: Samuel Evan Barak
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Book Description
In this study, syngas combustion was investigated behind reflected shock waves in order to gain insight into the behavior of ignition delay times and effects of the CO2 dilution. Pressure and light emissions time-histories measurements were taken at a 2 cm axial location away from the end wall. High-speed visualization of the experiments from the end wall was also conducted. Oxy-syngas mixtures that were tested in the shock tube were diluted with CO2 fractions ranging from 60% - 85% by volume. A 10% fuel concentration was consistently used throughout the experiments. This study looked at the effects of changing the equivalence ratios ([phi]), between 0.33, 0.5, and 1.0 as well as changing the fuel ratio ([theta]), hydrogen to carbon monoxide, from 0.25, 1.0 and 4.0. The study was performed at 1.61-1.77 atm and a temperature range of 1006-1162K. The high-speed imaging was performed through a quartz end wall with a Phantom V710 camera operated at 67,065 frames per second. From the experiments, when increasing the equivalence ratio, it resulted in a longer ignition delay time. In addition, when increasing the fuel ratio, a lower ignition delay time was observed. These trends are generally expected with this combustion reaction system. The high-speed imaging showed non-homogeneous combustion in the system, however, most of the light emissions were outside the visible light range where the camera is designed for. The results were compared to predictions of two combustion chemical kinetic mechanisms: GRI v3.0 and AramcoMech v2.0 mechanisms. In general, both mechanisms did not accurately predict the experimental data. The results showed that current models are inaccurate in predicting CO2 diluted environments for syngas combustion.
Author: Bijan Vakilzadeh
Publisher:
ISBN:
Category :
Languages : en
Pages : 610
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Book Description
Author: Robert E. Case
Publisher:
ISBN:
Category :
Languages : en
Pages : 66
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Book Description
A shock tube was employed to determine the ignition limit curves of three mixtures of N2O, CO, and N2. The ignition limit curve, which separates the ignition and no-ignition zones, is an experimentally determined curve plotted on temperature-pressure coordinates. The test gas mixtures of N2O, CO, N2 were ignited by the temperature rise behind the reflected shock wave for pressures in the range of 5 to 65 atmospheres. A 2-inch inside diameter constant area shock tube employing a helium driver was used to generate this reflected shock wave. Limited results were obtained on ignition delay time for each of the three gas mixtures. (Modified author abstract).
Author: Karl Scheller
Publisher:
ISBN:
Category :
Languages : en
Pages : 31
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Book Description
The ignition of propane-oxygen mixtures highly diluted with argon has been examined in the region behind a reflected shock wave in a single pulse shock tube. The measurements covered a temperature range of 1250-1600K at pressures varying from 2 to 10 atmospheres for mixture equivalence ratios of 0.125 to 2.0. For these conditions, observed induction times ranged from 12 to 600 microseconds. In one series of tests on a stoichiometric mixture, analyses were made of the shocked gas just prior to and immediately after ignition. These revealed that extensive pyrolysis of the propane preceded ignition. Mixture compositions and test conditions in this investigation were selected in such a manner that the influence of significant parameters on the ignition delay times could be clearly delineated. It was found that the experimental results of more than 150 tests were well correlated. (Author).
Author: Robert Edward Case (CAPT, USAF.)
Publisher:
ISBN:
Category : Carbon monoxide
Languages : en
Pages :
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Book Description
Author: Roger Ronald Craig
Publisher:
ISBN:
Category : Shock tubes
Languages : en
Pages : 62
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Author: R.K. Hanson
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Alfred Gordon Gaydon
Publisher:
ISBN: 9781258637460
Category :
Languages : en
Pages : 326
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Book Description
We report results of high-temperature shock tube research aimed at improving knowledge of the combustion behavior of diesel, jet and related fuels. Research was conducted in four Stanford shock tube facilities and focused on the following topics: (1) development of the aerosol shock tube; (2) ignition delay time measurements of gaseous jet fuels (JP-8 and Jet-A) and surrogate components at high pressures and low temperatures; (3) laser absorption measurements of species time-histories for OH radicals and alkanes; (4) ignition delay times of n-dodecane, jet fuel and diesel using the aerosol shock tube technique; and (5) improving shock tube performance and modeling.
