Relevant bibliographies by topics / Igniters

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

Academic literature on the topic 'Igniters'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Igniters"

1

Торба, Юрий Иванович, Сергей Игоревич Планковский, Олег Валерьевич Трифонов, Евгений Владимирович Цегельник, and Дмитрий Викторович Павленко. "МОДЕЛИРОВАНИE ПРОЦЕССА ГОРЕНИЯ В ФАКЕЛЬНЫХ ВОСПЛАМЕНИТЕЛЯХ ГТД." Aerospace technic and technology, no. 7 (August 31, 2019): 39–49. http://dx.doi.org/10.32620/aktt.2019.7.05.

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The aim of the work was the development and testing of methods for modeling the combustion process in the torch igniters of gas turbine engines. To achieve it, the finite element method was used. The main results of the work are the substantiation of the need to optimize the torch igniters of gas turbine engines. The practice of operating torch igniters of various designs has shown that the stability of their work depends on the parameters of gas turbine engines and external factors (air and fuel temperature, size of fuel droplets, fuel and air consumption, as well as its pressure). At the same time, the scaling of the geometry of the igniter design does not ensure its satisfactory work in the composition of the GTE with modified parameters. In this regard, an urgent task is to develop a combustion model in a flare igniter to optimize its design. A computational model of a torch igniter for a gas turbine engine of a serial gas-turbine engine in a software package for numerical three-dimensional thermodynamic simulation of AN-SYS FLUENT has been developed. To reduce the calculation time and the size of the finite element model, recommendations on the adaptation of the geometric model of the igniter for numerical modeling are proposed. The mod-els of flow turbulence and combustion, as well as initial and boundary conditions, are selected and substantiated. Verification of the calculation results obtained by comparison of numerical simulation with the data of tests on a specialized test bench was performed. It is shown that the developed computational model makes it possible to simulate the working process in the torch igniters of the GTE combustion chambers of the investigated design with a high degree of confidence. The scientific novelty of the work consists in substantiating the choice of the combustion model, the turbulence model, as well as the initial and boundary conditions that provide adequate results to the full-scale experiment on a special test bench. The developed method of modeling the combustion process in gas turbine torch igniters can be effectively used to optimize the design of igniters based on GTE operation conditions, as well as combustion initialization devices to expand the range of stable operation of the combustion chamber.
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Ricci, Federico, Luca Petrucci, Valentino Cruccolini, Gabriele Discepoli, Carlo N. Grimaldi, and Stefano Papi. "Investigation of the Lean Stable Limit of a Barrier Discharge Igniter and of a Streamer-Type Corona Igniter at Different Engine Loads in a Single-Cylinder Research Engine." Proceedings 58, no. 1 (September 11, 2020): 11. http://dx.doi.org/10.3390/wef-06909.

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Currently, the Radio-Frequency Corona Ignition systems represent an important solution for reducing pollutant emissions and fuel consumption related to Internal Combustion Engines, while at the same time ensuring high performance. These igniters are able to extend the lean stable limit by increasing the early flame growth speed. Kinetic, thermal, and ionic effects, together with the peculiar configuration of the devices, allow the combustion process to start in a wider region than the one involved with the traditional spark. In this work two corona igniters, namely a Barrier Discharge Igniter and a Corona Streamer Igniter, were tested in a single-cylinder research engine fueled with gasoline at different engine loads in order to investigate the igniters’ performance through indicated analysis and pollutant emissions analysis. For each operating point, the devices’ control parameters were set to ensure maximum energy releasement into the medium with the aim of investigating, at the extreme operating conditions, the capability of the devices to extend the lean stable limit of the engine. The corona igniters were tested on a constant volume calorimeter as well, reproducing the engine pressure conditions at the corresponding ignition timing. The target was to give an estimation of the thermal energy released during the discharge and then to compare their capability to provide high-stability energy.
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Ma, Yanjie, Futing Bao, Weihua Hui, Yang Liu, and Yijie Gao. "A Model for Igniter Mass Flow Rate History Evaluation for Solid Rocket Motors." International Journal of Aerospace Engineering 2019 (December 31, 2019): 1–12. http://dx.doi.org/10.1155/2019/2593602.

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This paper describes a zero-dimensional model for evaluating the mass flow rate history of a solid rocket motor igniter. Based on the results of an igniter-firing experiment, in which the igniter is the only source of combustion gas and no propellant is ignited, the proposed model can be used to compute the mass flow rate of the igniter. Different species and temperature-dependent properties, such as the specific heat for each species, are considered. The coupling between the flow field variables in the combustion chamber and the heat transfer at the gas-solid interface is computed in a segment way. Calculations are performed for different species and properties, and the errors are discussed. Using the computed igniter mass flow rate as a boundary condition, a two-dimensional calculation is performed for validation purposes. The results are in good agreement with experimental data. The proposed model can be used to provide reasonable boundary conditions for solid rocket motor simulations and to evaluate the performance of igniters. Although derived on the basis of a small-scale solid rocket motor, the model has the potential to be used in large-scale systems.
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Pochrybniak, Cezary, Andrzej Horodeński, Kamil Namyślak, Zbigniew Leciejewski, Zbigniew Surma, and Jakub Michalski. "CONCEPT OF MAGNETO-HYDRODYNAMIC PLASMA IGNITER FOR IGNITION OF LOW VULNERABILITY GUN PROPELLANTS." PROBLEMY TECHNIKI UZBROJENIA, no. 3 (November 29, 2017): 17–28. http://dx.doi.org/10.5604/01.3001.0010.6150.

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A concept of plasma coaxial magneto-hydrodynamic igniter for low sensitivity propelling materials is presented with initial experimental results. The concept is an interesting alternative for igniters generating the plasma by a blasting wire such as CPG (Capillary Plasma Generator) systems which have been recently investigated in many worldwide laboratories.
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McCourt, James, Ian Buist, and Joseph V. Mullin. "Operational Parameters for In Situ Burning of Six U.S. Outer Continental Shelf Crude Oils." International Oil Spill Conference Proceedings 1999, no. 1 (March 1, 1999): 1261–63. http://dx.doi.org/10.7901/2169-3358-1999-1-1261.

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ABSTRACT A laboratory test program was conducted with six crude oils to determine the following parameters with respect to in situ burning:The limits to ignition using gelled-gasoline igniters imposed by evaporation and emulsion-formationThe ability of commercially-available emulsion breakers and alternative fuel igniters to extend the window-of-opportunity for ignition of stable emulsionsThe effects of wave action on the combustion of emulsion slicks,The likelihood of the residues sinking after efficient burns of thick slicks of the crude oils As well as providing valuable spill-response oriented data, the study has shown that in situ burning may not be an appropriate response option for all oils. Some oils were easily ignited and burned efficiently, even when emulsified to high water contents. One oil could not be ignited even when fresh. The ability of emulsion breakers to promote emulsion ignition and burning was found to be oil-dependent.
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Pelikán, Vojtěch, Richard Kuracina, and Zuzana Szabová. "Timing Parameters of Pyrotechnic Igniter Based on Magnesium Powder." Research Papers Faculty of Materials Science and Technology Slovak University of Technology 27, no. 44 (June 1, 2019): 97–103. http://dx.doi.org/10.2478/rput-2019-0011.

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Abstract Chemical igniters are used in the study of dispersed dusts. Energy released during their use is defined by EN 14034 at 2 x 5 kJ. The Standard does not define the exact composition of the pyrotechnic mixture. The condition of using the igniter is to release energy according to the Standard. This article is focused on pyrotechnic composition with magnesium powder. It deals with various ways of activating, preparing and sealing the pyrotechnic mixture in the igniter. These values are important for setting up a device for studying the explosive properties of dispersed dusts.
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Knoetze, J. H. "Kritiese evaluering van termodinamiese ontwerpsprosedures vir vuurpylontstekers." Suid-Afrikaanse Tydskrif vir Natuurwetenskap en Tegnologie 13, no. 4 (July 10, 1994): 129–34. http://dx.doi.org/10.4102/satnt.v13i4.595.

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There are different methods that can be used for the thermodynamic design of igniters for solid rocket motors. These methods are mostly empirically based and can easily lead to an under-designed or over-designed igniter. The best-known methods are the free volume method, the surface area method, the critical pressure, the Bryan-Lawrence equation, the ignition delay-free volume method, the mass discharge coefficient method and the heat flux method.
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Murray, Allison K., Whitney A. Novotny, Nikhil Bajaj, I. Emre Gunduz, Steven F. Son, George T. C. Chiu, and Jeffrey F. Rhoads. "Piezoelectric Inkjet-Printed Metallic Igniters." NIP & Digital Fabrication Conference 2018, no. 1 (September 23, 2018): 76–81. http://dx.doi.org/10.2352/j.imagingsci.technol.2018.62.4.040406.

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Dawe, J. R., P. R. Smy, R. F. Haley, J. D. Dale, M. F. Bardon, and D. P. Gardiner. "Plasma Jet Ignition of Methanol at Sub-Zero Temperatures." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 208, no. 3 (July 1994): 153–59. http://dx.doi.org/10.1243/pime_proc_1994_208_178_02.

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Use of a pulsed plasma jet igniter to improve low-temperature starting of 100 per cent methanol (M100) fuelled engines is explored. A simple theoretical model of heat transfer from plasma to liquid methanol shows that sufficient energy is transferred for fuel vaporization in cold starting. Two laboratory experiments test liquid plane surface and droplet modes of ignition. An ordinary four cylinder auto engine fitted with plasma jet igniters is tested for cold starting in a Canadian winter, and cold starting is improved from +10°C (conventional ignition) to −16°C.
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Whittaker, Harry. "LASER IGNITION OF OIL SPILLS." International Oil Spill Conference Proceedings 1987, no. 1 (April 1, 1987): 389–94. http://dx.doi.org/10.7901/2169-3358-1987-1-389.

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ABSTRACT A major oil spill in the Arctic, whether from a tanker or an oil rig, could result in large concentrations of oil among broken ice and/or thousands of oiled melt pools. The remoteness of the area and the inadequacy of other countermeasures make in-situ burning the only possible response. Helicopter-deployable igniters have been developed to ignite the oil, but studies have shown that use of these devices has severe logistical constraints. The use of a helicopter-borne laser system as an alternative to, or in conjunction with, the igniters has been pursued from conceptual development to completion of the engineering design phase. The concept was examined by theoretical analysis combined with laboratory studies. This work indicated that a dual-laser system would ignite both fresh and weathered crude oils at temperatures representative of an arctic spring or fall day. A series of outdoor experiments was carried out in Kanata, Ontario, Canada, in March 1985. These experiments, under climatic conditions very similar to those in the Canadian Arctic in June, demonstrated that a two-laser system would ignite both fresh and weathered crudes. An engineering feasibility and design study was undertaken. The study confirmed that a system having the required performance can be assembled from existing, proven hardware and operated effectively from a helicopter. The development of the laser ignition of oil spills from concept through engineering design is described.
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Dissertations / Theses on the topic "Igniters"

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Benito, Parejo Carlos Javier. "Experimental Characterization of Electrical Discharges and Formation of the Ignition Kernel. Application to the Study of Performances of Aeronautical Igniters." Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2019. http://www.theses.fr/2019ESMA0021.

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Les systèmes d'allumage par étincelle sont généralement définis par l'énergie électrique utilisée pour leur fonctionnement. Cependant, la caractéristique physique qui affecte directement le processus d'allumage est l'énergie déposée dans le fluide par le système. Ce travail porte sur le développement de deux méthodologies proposées pour la caractérisation du dépôt d’énergie thermique de décharges électriques produites par différents systèmes d'allumage et de leur mise en œuvre au travers d’une étude paramétrique.Un dispositif expérimental est mis au point afin de développer et mettre en œuvre simultanément les deux techniques: une technique non optique, la calorimétrie à volume constant, et une technique optique, la SBOS (Speckle-based Background-Oriented Schlieren). L’étape de validation de ces méthodes est réalisée dans une configuration de référence d’un allumeur inductif alimentant une paire d'électrodes pointe-pointe.La calorimétrie à volume constant permet de mesurer un dépôt d'énergie thermique fournie au fluide par l’analyse de la montée en pression à l'intérieur d'une chambre de petit volume. Un suivi temporel du dépôt d’énergie pendant la décharge est ainsi obtenu. La mesure globale dans un volume de contrôle rend cette technique adaptable à tous types de décharges et d’électrodes. Le rapport entre le dépôt d'énergie thermique et l'apport d'énergie électrique représente l'efficacité du transfert d'énergie. Cette dernière est comprise entre 15 et 40 % pour la configuration de référence. Le dépôt d'énergie et l'efficacité du transfert d’énergie sont plus élevés à mesure que la pression et l'écart inter-électrode augmentent. Des essais avec un mélange inerte azote-propane montrent que le dépôt d'énergie est plus important en présence de carburant que dans l'air pur.La SBOS est une méthode optique permettant de quantifier les variations d’indice optique générés par le phénomène étudié. Le principe consiste à comparer des images d’un motif visualisé au travers du phénomène avec ce même motif en l’absence de phénomène. Cette technique est ici adaptée aux contraintes d’échelles spatiale et temporelle d’une décharge électrique. Une procédure de traitement a été développée afin d’obtenir les champs de masse volumique, de température et enfin l'énergie locale au moment de l'acquisition de l'image. Le volume du noyau chaud produit par le plasma et le dépôt d'énergie en sont déduits. Ces propriétés sont mesurées à différents instants de l'évolution du noyau. Dans la configuration de référence, il est montré que les températures dans le noyau chaud atteignent des valeurs plus élevées pour des distances inter-électrodes et des pressions plus élevées ou encore en présence de carburant. Le volume du noyau chaud est en revanche réduit lorsque la pression ou la distance inter-électrode augmente. Des mesures simultanées de dépôt d’énergie par les deux techniques montrent un très bon accord entre la SBOS et la calorimétrie.Enfin, les deux méthodologies sont adaptées à l'étude de différents systèmes d'allumage. Ainsi, deux allumeurs ont été testés, un allumeur à décharge radiofréquence multi filamentaires innovant et un allumeur capacitif typique d’un moteur d’hélicoptère. Pour ce dernier, le dépôt d'énergie est mesuré pour différentes pressions initiales et mélanges gazeux afin de simuler les conditions réelles du moteur. La technique SBOS est utilisée pour estimer la température dans le noyau chaud aux premiers instants de la décharge (jusqu'à 3500 K) et le dépôt d’énergie thermique qui est en bon accord avec la mesure calorimétrique. Le rendement ce cette décharge spécifique semble peu dépendant des conditions thermodynamiques du mélange et est estimé à 14%
Spark ignition systems are generally defined by the electrical energy input used to operate them. However, the physical characteristic that directly affects the ignition process is the energy deposit supplied to the fluid by the system. This work focuses on the development of two proposed methodologies for the characterization of the thermal energy deposit of electrical discharges produced by different ignition systems, and their implementation through a parametric study. An experimental device is developed for this purpose, using simultaneously a non-optical and an optical technique. The experimental techniques are first validated in a reference configuration: a pair of pin-to-pin electrodes with an automobile-type inductive ignition system.Constant volume calorimetry measures a thermal energy deposit supplied to the fluid via the pressure rise inside a reduced volume chamber. The ratio between thermal energy deposit and electrical energy supply represents the efficiency of energy transfer, which is between 15 and 40% for the reference configuration. Energy deposit and efficiency are higher as pressure and inter-electrode gap increase. Tests with an inert propane-nitrogen mixture show that energy deposit is greater in the presence of fuel than in clean air.SBOS (Speckle-based Background-Oriented Schlieren) is an optical method that quantifies changes in the optical index generated by the phenomenon under study. This technique has been adapted to the spatial and temporal specificity of an electrical discharge. Image-processing procedure has been developed to obtain density, temperature and local energy fields at the time of image acquisition. The volume of the hot kernel produced by the plasma and the energy deposit are deduced from it. These properties are measured at different times during the evolution of the kernel. Temperatures in the hot kernel reach higher values (up to 1400 K) at longer inter-electrode gaps and higher pressures, or in the presence of gaseous fuel. Energy deposit measurements performed by SBOS are in good agreement with calorimetry results.Finally, both methodologies are adapted to the study of different ignition systems. Two igniters were tested: an innovative multi-filament radiofrequency discharge igniter and a capacitive helicopter engine igniter. For the latter, the energy deposit is measured for different initial pressures and gas mixtures to simulate the actual engine conditions. The electrical energy input is 2 J, the electrical energy measured at the electrodes is 625 mJ and finally the thermal energy deposited in the gas is about 85 mJ. The estimated efficiency of 14% is not very pressure dependent. The SBOS technique is used to estimate the temperature in the hot kernel at the first moments of discharge (around 3700 K) and the thermal energy deposit, which is in good agreement with the calorimetric measurement
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Weierbach, Florence M. "IGNITES Voices from Our Community." Digital Commons @ East Tennessee State University, 2018. https://dc.etsu.edu/etsu-works/7371.

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Andersson, Sofie. "Ignite Imagination." Thesis, KTH, Arkitektur, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-146205.

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The intention with this project is to explore and open up the imagination, through investigating how text can be transformed into architecture. The outcome of the investigation during this project is a series of 9 architectural objects. The objects are independent from the text and could be thought of as ‘short-stories’.
Intentionen med detta examensarbete var att undersöka och öppna upp fantasin, genom att utforska hur text kan transformeras till arkitektur. Resultatet av detta utforskande projekt är en serie av 9 objekt. Objekten är oberoende av texten och kan ses som ’short-stories’ i sig själva.
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4

Ha, Jung Wan Coleman Robert Emerson. "Translation of Dr. Robert E. Coleman's book The spark that ignites." Theological Research Exchange Network (TREN), 1994. http://www.tren.com.

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Thesis (M.A.)--Trinity Evangelical Divinity School, 1994.
Abstract. Title page, abstract and initial chapter in English followed by Korean translation of the English work. Includes bibliographical references (leaf 11).
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Billingsley, Matthew C. "Plasma Torch Atomizer-Igniter for Supersonic Combustion of Liquid Hydrocarbon Fuels." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/36331.

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To realize supersonic combustion of hydrocarbons, an effective atomizer-igniter combination with the capabilities of fuel preheating, atomization, penetration, mixing, ignition and flameholding is desired. An original design concept incorporating these capabilities was built and tested at Virginia Tech, and was found to provide good penetration, effective atomization, and robust ignition and flameholding. Quiescent testing with kerosene and JP-7 provided initial performance data. The atomizer-injector design was then modified for insertion into a supersonic wind tunnel, and tested with kerosene in an unheated Mach 2.4 flow with typical freestream conditions of To = 280 K and Po = 360 kPa. Water injection was utilized in both cases for comparison and to analyze atomization behavior. In the quiescent environment, the regeneratively cooled plasma torch igniter was found to significantly increase electrode life while heating, atomizing, and igniting the liquid fuel. Jet breakup length was measured and characterized, and mean droplet size was estimated using an existing correlation. Several qualitative observations regarding quiescent combustion were made, including torch power effects and the process of flame formation. In the supersonic environment, the effect of fuel injection direction was analyzed. Best results were obtained when fuel was injected with a velocity component opposite to the direction of main tunnel flow. Repeatable ignition occurred in the supersonic boundary layer at the fuel stagnation location near the plasma torch plume. Direct, filtered, shadowgraph, and schlieren photographs, temperature measurements, and visible emission spectroscopy provided evidence of combustion and the details of the flame structure. The new atomizer-igniter design provided robust and reliable ignition and flameholding of liquid hydrocarbon fuels in an unheated supersonic flow at M=2.4, with no ramp, step, or other physical penetration into the flowpath.
Master of Science
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Mozingo, Joseph Alexander. "Evaluation of a Strut-Plasma Torch Combination as a Supersonic Igniter-Flameholder." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/36461.

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As the flight speeds of aircraft are increased above Mach 5, efficient methods of propulsion are needed. Scramjets may be a solution to this problem. Supersonic combustion is one of the main challenges involved in the operation of a Scramjet engine. In general, both an igniter and a flameholder are needed to achieve and maintain supersonic combustion. The current work examines a plasma torch-strut combination as an igniter-flameholder. The plasma torch-strut combination was tested in the Virginia Tech unheated supersonic wind tunnel at Mach 2.4. Pressure and temperature sampling, filtered photography, and spectroscopic measurements were used to compare different test cases. These results provide both qualitative and quantitative results on how the combination responds to changes in the mass flow rate of fuel and the power to the plasma torch. The key conclusions of the work were the following: 1. Tests showed that an exothermic reaction takes place. 2. The amount of heat release increases with an increase in the mass flow rate of fuel. 3. The plasma torch-fuel injector interaction caused the heat release to be well above the tunnel floor and sometimes off the strut centerline 4. One change in the fuel injector pattern caused more temperature rise near the floor of the tunnel. 5. The flow penetration height of the plasma torch alone was reduced by the fuel-plasma torch interaction. 6. Moving the strut upstream reduced the measured temperature rise at a fixed downstream location, but increased the penetration height of the plasma torch. 7. The computed heat release was found to be small compared to the potential heat release from all the fuel burning. 8. The amount of temperature rise caused by the fuel is not greatly affected by the power to the plasma torch.
Master of Science
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Grant, Andrew J. "Laser diagnostics of spark-ignited combustion systems." Thesis, University of Oxford, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.343481.

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Thornhill, Michael Joseph. "Idle speed control of spark ignited engines." Thesis, Queen's University Belfast, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.286863.

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Anderson, Cody Dean. "Development and Testing of an Integrated Liquid-Fuel-Injector/Plasma-Igniter for Scramjets." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/31416.

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A newly designed liquid fuel (kerosene) aeroramp injector/plasma igniter was tested in cold flow using the Virginia Tech supersonic wind tunnel at Mach 2.4. The liquid fuel (kerosene) injector is flush wall mounted and consists of a 2 hole aeroramp array of impinging jets that are oriented in a manner to improve mixing and atomization of the liquid jets. The two jets are angled downstream at 40 degrees and have a toe-in angle of 60 degrees. The plasma torch used nitrogen and air as feedstocks and was placed downstream of the injector as an ignition aid. First, schlieren and shadowgraph photographs were taken of the injector flow to study the behavior of the jets, shape of the plume, and penetration of the liquid jet. The liquid fuel aeroramp was found to have better penetration than a single, round jet at 40 degrees. However, the liquid fuel aeroramp does not penetrate as well as an upstream/downstream impinging jet in a plane aligned with the flow. Next, the Sauter mean droplet diameter distribution was measured downstream of the injector. The droplet diameter was found to vary from 21 to 37 microns and the atomization of the injector does not appear to improve beyond 90 effective jet diameters from the liquid fuel aeroramp. These results were then used to decide on an initial location for the plasma torch. The combined liquid injector/plasma torch system was tested in an unheated (300 K) Mach 2.4 flow with a total pressure of 345 kPa. The liquid fuel (kerosene) volumetric flow rate was varied from 0.66 lpm to 1.22 lpm for the combined liquid injector/plasma torch system. During this testing the plasma torch was operated from 1000 to 5000 watts with 25 slpm of nitrogen and air as feedstocks. The interaction between the spray plume and the plasma torch was observed with direct photographs, videos, and photographs through an OH filter. It is difficult to say that any combustion is present from these photographs. Of course, it would be surprising if much combustion did occur under these cold-flow, low-pressure conditions. Differences between the interaction of the spray plume and the plasma torch with nitrogen and air as feedstocks were documented. According to the OH wavelength filtered photographs the liquid fuel flow rate does appear to have an effect on the height and width of the bright plume. As the liquid fuel flow rate increases the bright plume increases in height by 30% and increases in width slightly (2%). While, a decrease in liquid fuel flow rate resulted in an increase in height by 9% and an increase in width by 10%. Thus, as the liquid fuel flow rate varies the width and height of the bright plume appear to always increase. This can be explained by noticing that the shape of the bright plume changes as the liquid fuel flow rate varies and perhaps anode erosion during testing also plays a part in this variation of the bright plume. From the OH wavelength filtered photographs it was also shown that the bright plume appears to decrease in width by 9% and increase in height by 22% when the plasma torch is set at a lower power setting. When air is used as the torch feedstock, instead of nitrogen, the penetration of the bright plume can increase by as much as 19% in width and 17% in height. It was also found that the height and width of the bright plume decreased slightly (2%) as the fuel flow rate increased when using air as the torch feedstock. Testing in a hot-flow facility is planned.
Master of Science
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10

Rabe, Tiaan. "Determination of the effectiveness of a Hot Tube igniter for initiating HCCI combustion." Master's thesis, University of Cape Town, 2006. http://hdl.handle.net/11427/5483.

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Includes bibliographical references (leaves 61-63).
Homogeneous Charge Compression Ignition (HCCI) is a new internal combustion system that promises high efficiency and dramatically reduced nitrous oxide (NOJ and particulate matter (PM) emissions when compared to current spark ignition (SI) and compression ignition (CI) engine technologies. In its simplest form, HCCI can be described as lean autoignition of a homogeneous fuel/air mixture that occurs without a flame front. HCCI can in theory be achieved using almost any fuel, provided that it evaporates readily and has a short enough ignition delay that it can be made to autoignite under the conditions typically found in an IC engine. Basically HCCI incorporates the best features of a SI (petrol) and CI (diesel) engine. Like in a SI engine, the fuel and air in the cylinder is allowed to be well mixed before the onset of combustion which promotes cleaner burnng (Low PM) and like in a CI engine the engine is operated overall fuel-lean and therefore has no throttling losses and near zero NOx emissions. The mixture is also compression ignited in the same way as in a CI engine. This causes combustion to occur simultaneously throughout the combustion chamber and thus no flame front is present.
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Books on the topic "Igniters"

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Gelbart, Marvin. The Igniters. Bloomington, IN: AuthorHouse, 2008.

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Thorne, L. R. Platinum catalytic igniters for lean hydrogen-air mixtures. Washington, DC: Division of Engineering, Office of Nuclear Regulatory Research, U.S. Nuclear Regulatory Commission, 1988.

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Cook, M. Igniter adapter-to-igniter chamber deflection test final report. Brigham City, UT: Thiokol Corp., Space Operations, 1990.

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Ignite. Enumclaw, WA: WinePress Pub., 2010.

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Gammon, Carolyn. Lesbians ignited. Charlottetown, PEI, Canada: Gynergy Books, 1992.

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Green, James M. A premixed hydrogen/oxygen catalytic igniter. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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Abdelnour, Mark. Soundtrack ignite! Boston, MA: Course Technology, 2004.

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GarageBand ignite! Boston, MA: Course Technology, 2004.

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Greatrix, D. R. Numerical models for pellet-dispersion igniter systems. New York: AIAA, 1988.

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Johnson, Deborah Joyner. Write to ignite. Fort Mill, SC: MorningStar Publications, 2008.

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Book chapters on the topic "Igniters"

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Görnig, T. "Integrated Electronics for Bus Systems Igniters." In Advanced Microsystems for Automotive Applications 2001, 221–27. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-642-18253-2_20.

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Ikeda, Yuji. "Plasma-Assisted Combustion in Automobile Engines Using Semiconductor-Oscillated Microwave Discharge Igniters." In RF Power Semiconductor Generator Application in Heating and Energy Utilization, 195–216. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3548-2_9.

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Ingenito, Antonella. "Igniter Design Guidelines." In Subsonic Combustion Ramjet Design, 91–93. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-66881-5_9.

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Brett, James. "Ignite." In Evolving Digital Leadership, 311–18. Berkeley, CA: Apress, 2018. http://dx.doi.org/10.1007/978-1-4842-3606-2_20.

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Shaw, Lisa, Luis Duno-Gottberg, Joanna Page, and Ignacio M. Sánchez Prado. "National cinemas (re)ignited." In The Routledge Companion to Latin American Cinema, 44–61. New York : Routledge, 2017.: Routledge, 2017. http://dx.doi.org/10.4324/9781315720449-4.

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Koehn, Peter H., and Milton O. Obamba. "Higher Education and Development: Knowledge as Igniter." In The Transnationally Partnered University, 27–37. New York: Palgrave Macmillan US, 2014. http://dx.doi.org/10.1057/9781137481757_2.

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Ricart, Glenn, and Rick McGeer. "US Ignite and Smarter Communities." In The GENI Book, 479–510. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-33769-2_20.

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Pegoraro, Francesco. "Ignition Physics and the Ignitor Project." In Current Trends in International Fusion Research, 125–34. Boston, MA: Springer US, 1997. http://dx.doi.org/10.1007/978-1-4615-5867-5_9.

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Rollet, S., and M. Rapisarda. "Neutronics and Shielding Analysis of an Ignitor." In Advanced Monte Carlo for Radiation Physics, Particle Transport Simulation and Applications, 911–17. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-642-18211-2_146.

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Shakya, Rikesh, and Nathan Ida. "Flame Temperature Sensor Based on a Silicon Nitride Hot Surface Igniter." In Lecture Notes in Electrical Engineering, 163–76. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-91659-0_12.

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Conference papers on the topic "Igniters"

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LA FERLA, R., R. TUFFIAS, and Q. JANG. "Monolithic catalytic igniters." In 29th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1905.

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Murray, Richard, and Jahangir Rastegar. "A Review of Three Patents Relating to the Development of Novel Inertia-Driven Mechanisms for Igniters On-Board Gun-Fired Munitions." In ASME 2010 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/detc2010-28468.

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This is a review of a series of three patents issued for inertia igniters: devices which are generally used on-board gun-fired munitions to provide pyrotechnic initiation of a thermal battery. The igniters use the overwhelming firing acceleration to drive various mechanism components which provide event-sensing and a time time-delay in addition to the mechanical striking which ignites the pyrotechnic element of the igniter. The embodiments in the three patents progresses from a novel approach to achieve greater axial compactness while maintaining equivalent performance to a benchmark design, to a two-stage design which expands the range of performance of the event-sensing and time-delay characteristics of the devices, and finally to several novel approaches for producing arbitrarily long delays and the sensing of large impulses in highly compact multi-stage inertia-driven devices. The expansion of the range of operation of such devices is particularly important because prior to these innovative approaches, long delays or the practical measurement of large impulses required electronic methods and an additional tier of electrical power in addition to the thermal battery which is to be initiated.
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DE VALK, G., F. ZEE, and G. GADIOT. "HM-60 pyrotechnic igniters ignition improvement." In 26th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2084.

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Kuo, Spencer, Daniel Bivolaru, S. Popovic, Henry Lai, and Wilson Lai. "Plasma Torch Igniters for a Scramjet Combustor." In 42nd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-839.

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Brauers, Bernd, Marcello Angelone, Bart Goorden, Eric Gautronneau, and Gandolfo di Vita. "Qualification and Production of the VEGA SRM Igniters." In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-5322.

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Pulido, Julio, Mark Mc Bride, and Miguel Fonseca. "Reliability analysis of igniters under thermal mechanical loadings." In 2017 Annual Reliability and Maintainability Symposium (RAMS). IEEE, 2017. http://dx.doi.org/10.1109/ram.2017.7889744.

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Reese, David, Darren Wright, and Steven Son. "CuO/Al Igniters For Solid Rocket Motor Ignition." In 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-5987.

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Zheng, Lei. "Abstract IA26: Vaccines: The igniters of antitumor immunity." In Abstracts: AACR Special Conference: Tumor Immunology and Immunotherapy: A New Chapter; December 1-4, 2014; Orlando, FL. American Association for Cancer Research, 2015. http://dx.doi.org/10.1158/2326-6074.tumimm14-ia26.

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Gupta, Sreenath B. "Fouling Mitigation for Laser Igniters in Natural Gas Engines." In ASME 2020 Internal Combustion Engine Division Fall Technical Conference. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/icef2020-2963.

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Abstract Due to several recent developments in lasers and optics, laser igniters can now be designed to be (i) compact so as to have the same footprint as a standard spark plug, (ii) have low power draw, usually less than 50 Watts, and (iii) have vibration and temperature resistance at levels typical of reciprocating engines. Primary advantages of these laser igniters remain (i) extension of lean or dilution limits for ignition of combustible mixtures, and (ii) improved ignition at higher pressures. Recently, tests performed in a 350 kW 6-cylinder stationary natural gas reciprocating engine retrofitted with these igniters showed an extension of the operational envelope to yield efficiency improvements of the order of 2.6% points while being compliant with the mandated emission regulations. Even though laser igniters offer promise, fouling of the final optical element that introduces the laser into the combustion chamber is of concern. After performing a thorough literature search, a test plan was devised to evaluate various fouling mitigation strategies. The final approach that was used is a combination of three strategies and helped sustain an optical transmissivity exceeding 98% even after 1500 hrs. of continuous engine operation at 2400 rpm. Based on the observed trend in transmissivity, it now appears that laser igniters can last up to 6000 hrs. of continuous engine operation in a stationary engine running at 1800 rpm.
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Matveev, Igor, Svetlana Matveeva, and Alexander Gutsol. "Non-Equilibrium Plasma Igniters and Pilots for Aerospace Application." In 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-1191.

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Reports on the topic "Igniters"

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Stobie, I. C., John D. Knapton, and J. DeSpirito. Characterization of Solid and Liquid Propellant Igniters for Use in Medium Caliber Regenerative Liquid Propellant Guns. Fort Belvoir, VA: Defense Technical Information Center, May 1988. http://dx.doi.org/10.21236/ada196741.

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Homentowski, Eugene, Neha Mehta, Gartung Cheng, and Emily Cordaro. M228 Fuze Igniter Pressure Measurement. Fort Belvoir, VA: Defense Technical Information Center, July 2010. http://dx.doi.org/10.21236/ada526418.

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Guo, Shuyue, and Marcia A. Cooper. Multivariate Regression of Pyrotechnic Igniter Output. Office of Scientific and Technical Information (OSTI), January 2020. http://dx.doi.org/10.2172/1595549.

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Knapton, John D., Avi Birk, James DeSpirito, and Cris Watson. Regenerative Liquid Propellant Gun Igniter Concepts. Fort Belvoir, VA: Defense Technical Information Center, October 1987. http://dx.doi.org/10.21236/ada190595.

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Homentowski, Eugene, Neha Mehta, Gartung Cheng, and Emily Cordaro. M228 Fuze Igniter Pressure Measurement, Part 2. Fort Belvoir, VA: Defense Technical Information Center, March 2011. http://dx.doi.org/10.21236/ada538007.

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Bromberg, L., P. Titus, D. Cohn, and C. Bolton. IGNITOR scale-up studies (DIGNITOR). Office of Scientific and Technical Information (OSTI), April 1990. http://dx.doi.org/10.2172/7185023.

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Santavicca, D. A. Spark Ignited Turbulent Flame Kernel Growth. Office of Scientific and Technical Information (OSTI), June 1995. http://dx.doi.org/10.2172/6605.

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Xiao, H., R. D. Hazeltine, and R. Carrera. Self-consistent radial sheath in ignited plasmas. Office of Scientific and Technical Information (OSTI), November 1991. http://dx.doi.org/10.2172/10107814.

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Chen, J. C., and V. Kabadi. Ignition Rate Measurement of Laser-Ignited Coals. Office of Scientific and Technical Information (OSTI), May 1997. http://dx.doi.org/10.2172/644601.

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Cheng, C. Z., G. Y. Fu, and J. W. Van Dam. Toroidal Alfven wave stability in ignited tokamaks. Office of Scientific and Technical Information (OSTI), January 1989. http://dx.doi.org/10.2172/6386067.

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