Relevant bibliographies by topics / Fuel jets

Contents

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

Academic literature on the topic 'Fuel jets'

Author: Grafiati
Published: 4 June 2021
Last updated: 17 February 2022

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Journal articles on the topic "Fuel jets"

1

Pickett, L. M., and D. L. Siebers. "Soot Formation in Diesel Fuel Jets Near the Lift-Off Length." International Journal of Engine Research 7, no. 2 (April 1, 2006): 103–30. http://dx.doi.org/10.1243/146808705x57793.

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Soot formation in the region downstream of the lift-off length of diesel fuel jets was investigated in an optically accessible constant-volume combustion vessel under quiescent-type diesel engine conditions. Planar laser-induced incandescence and line-of-sight laser extinction were used to determine the location of the first soot formation during mixing-controlled combustion. OH chemiluminescence imaging was used to determine the location of high-heat-release reactions relative to the soot-forming region. The primary parameters varied in the experiments were the sooting propensity of the fuel and the amount of fuel-air premixing that occurs upstream of the lift-off length. The fuels considered in order of increasing sooting propensity were: an oxygenated fuel blend (T70), a blend of diesel cetane-number reference fuels (CN80), and a #2 diesel fuel (D2). Fuel-air mixing upstream of the lift-off length was varied by changing ambient gas and injector conditions, which varied either the lift-off length or the air entrainment rate into the fuel jet relative to the fuel injection rate. Results show that soot formation starts at a finite distance downstream of the lift-off length and that the spatial location of soot formation depends on the fuel type and operating conditions. The distance from the lift-off length to the location of the first soot formation increases as the fuel sooting propensity decreases (i.e. in the order D2 < CN80 < T70). At the baseline operating conditions, the most upstream soot formation occurs at the edges of the jet for D2 and CN80, while for T70 the soot formation is confined to the jet central region. When conditions are varied to produce enhanced fuel-air mixing upstream of the lift-off length in D2 fuel jets, the initial soot formation shifts towards the fuel jet centre and eventually no soot is formed. For all experimental conditions, the observed location of soot formation relative to the heat-release location (lift-off) suggests that soot formation occurs in a mixture of combustion products originating from partially premixed reactions and a diffusion flame. The results also imply that soot precursor formation rates depend strongly on fuel type in the region between the lift-off length and the first soot formation.
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Pianthong, K., A. Matthujak, K. Takayama, T. Saito, and Brian E. Milton. "VISUALIZATION OF SUPERSONIC LIQUID FUEL JETS." Journal of Flow Visualization and Image Processing 13, no. 3 (2006): 217–42. http://dx.doi.org/10.1615/jflowvisimageproc.v13.i3.20.

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

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An investigation has been conducted to develop appropriate technologies for a low-NOx, liquid-fueled combustor. The combustor incorporates an effervescent atomizer used to inject fuel into a premixing duct. Only a fraction of the combustion air is used in the premixing process. This fuel-rich mixture is introduced into the remaining combustion air by a rapid jet-shear-layer mixing process involving radial fuel–air jets impinging on axial air jets in the primary combustion zone. Computational modeling was used as a tool to facilitate a parametric analysis appropriate to the design of an optimum low-NOx combustor. A number of combustor configurations were studied to assess the key combustor technologies and to validate the three-dimensional modeling code. The results from the experimental testing and computational analysis indicate a low-NOx potential for the jet-shear-layer combustor. Key features found to affect NOx emissions are the primary combustion zone fuel–air ratio, the number of axial and radial jets, the aspect ratio and radial location of the axial air jets, and the radial jet inlet hole diameter. Each of these key parameters exhibits a low-NOx point from which an optimized combustor was developed. Also demonstrated was the feasibility of utilizing an effervescent atomizer for combustor application. Further developments in the jet-shear-layer mixing scheme and effervescent atomizer design promise even lower NOx with high combustion efficiency.
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Hill, Philip G., and Patric Ouellette. "Transient Turbulent Gaseous Fuel Jets for Diesel Engines." Journal of Fluids Engineering 121, no. 1 (March 1, 1999): 93–101. http://dx.doi.org/10.1115/1.2822018.

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Existing data on transient turbulent jet injection in to large chambers demonstrates self-similar behavior under a wide range of conditions including compressibility, thermal and species diffusion, and nozzle under expansion. The Jet penetration distance well downstream of the virtual origin is proportional to the square root of the time and the fourth root of the ratio of nozzle exit momentum flow rate to chamber density. The constant of proportionality has been evaluated by invoking the concept of Turner that the flow can be modeled as a steady jet headed by a spherical vortex. Using incompressible transient jet observations to determine the asymptotically constant ratio of maximum jet width to penetration distance, and the steady jet entrainment results of Ricou and Spalding, it is shown that the penetration constant is 3 ± 0.1. This value is shown to hold for compressible flows also, with substantial thermal and species diffusion, and even with transient jets from highly under-expanded in which, as in diesel engine chambers with gaseous fuel injection, the jet is directed at a small angle to one wall of the chamber. In these tests, with under expanded nozzles. Observations of transient jet injection have been made in a chamber in which, as in diesel engine chambers with gaseous fuel injection, the jet is directed at a small angle to one wall of the chamber. In these tests, with under-expanded nozzles it was found that at high nozzle pressure ratios, depending on the jet injection angle, the jet penetration can be consistent with a penetration constant of 3. At low pressure ratios the presence of the wall noticeably retards the penetration of the jet.
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Peleowo, Adedamola Najeem. "The Effect of Nozzle Breakaway Pressure on the Spray Pattern Formed." Applied Mechanics and Materials 248 (December 2012): 173–78. http://dx.doi.org/10.4028/www.scientific.net/amm.248.173.

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The main function of a fuel injector nozzle is to break fuels into droplets, form the spray pattern, and propel the droplets into a combustion chamber. The amount of spray volume at a given operating pressure, the travel speed, and spacing between the jets of fuel can also be determined by the nozzle. In fuel injection, the smallest possible droplet size is desired for the most flow. This work presents an opportunity to use the Schlieren arrangement as a visualization method to view the flow of fuel from a three-hole fuel injector nozzle which cannot be seen by the naked eye. The jet flow of diesel Fuel was investigated by Schlieren photography. A test rig was designed and constructed to accommodate the nozzle; optical mirrors were arranged according to Schlieren specifications in order to allow the jet to be photographed. The breakaway pressure of the nozzle was varied between 60bar to 80bar. Each hole of the nozzle is 0.26mm in diameter and 120° apart; the third jet could not be seen from the images because the camera took x-y dimension images. The spray pattern observed from the two dimensional images of the jets developed were seen to be well dispersed. Su et al [3] found that emissions could be reduced in diesel engines if the injector nozzle produces smaller and more dispersed droplets.
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Neal, Nicholas, and David Rothamer. "Evolving one-dimensional transient jet modeling by integrating jet breakup physics." International Journal of Engine Research 18, no. 9 (February 1, 2017): 909–29. http://dx.doi.org/10.1177/1468087416688119.

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High-speed optical measurements of unsteady liquid fuel jets under engine-like conditions have shown that the initial penetration of the jets does not follow the behavior predicted by previously introduced one-dimensional jet models based on gas-jet principles. The experimental data indicate that the transient jet penetration velocity is initially controlled by the jet exit velocity, transitioning to gas-jet like mixing-dominated penetration further downstream. This behavior is consistent with the common description of high-pressure fuel jets as containing a liquid core surrounded by entrained gas and fuel droplets. In this paper, a new one-dimensional modeling methodology is introduced that couples the transport equations for the evolution of the liquid core of the jet and the surrounding sheath of droplets resulting from breakup. This allows for the penetration of the jet to be initially governed by the liquid core, which is relatively unaffected by the ambient gas, transitioning to spray penetration dominated by the entrained ambient gas. The model also provides a defined jet centerline velocity, which allows for the shape of the radial profiles of fuel velocity and fuel volume fraction to be solved for directly, without the need for a steady-jet assumption, as was used in previous one-dimensional models. This change removes the need for a constant momentum flux assumption, improving the transient nature of the model. The results of the model are validated against the aforementioned optical transient jet measurements. The model and all associated experimental data have been made available for use at rothamer.erc.wisc.edu/dlp .
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Crocker, D. S., and C. E. Smith. "Numerical Investigation of Enhanced Dilution Zone Mixing in a Reverse Flow Gas Turbine Combustor." Journal of Engineering for Gas Turbines and Power 117, no. 2 (April 1, 1995): 272–81. http://dx.doi.org/10.1115/1.2814091.

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An advanced method for dilution zone mixing in a reverse flow gas turbine combustor was numerically investigated. For long mixing lengths associated with reverse flow combustors (X/H > 2.0), pattern factor was found to be mainly driven by nozzle-to-nozzle fuel flow and/or circumferential airflow variations; conventional radially injected dilution jets could not effectively mix out circumferential nonuniformities. To enhance circumferential mixing, dilution jets were angled to produce a high circumferential (swirl) velocity component. The jets on the outer liner were angled in one direction while the jets on the inner liner were angled in the opposite direction, thus enhancing turbulent shear at the expense of jet penetration. Three-dimensional CFD calculations were performed on a three-nozzle (90 deg) sector, with different fuel flow from each nozzle (90, 100, and 110 percent of design fuel flow). The computations showed that the optimum configuration of angled jets reduced the pattern factor by 60 percent compared to an existing conventional dilution hole configuration. The radial average temperature profile was adequately controlled by the inner-to-outer liner dilution flow split.
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Hesman, Tina. "Coal: The Cool Fuel for Future Jets." Science News 157, no. 15 (April 8, 2000): 230. http://dx.doi.org/10.2307/4012523.

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Ni, T. Q., and L. A. Melton. "Fuel Equivalence Ratio Imaging for Methane Jets." Applied Spectroscopy 47, no. 6 (June 1993): 773–81. http://dx.doi.org/10.1366/0003702934066910.

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A 2-D fuel/oxygen equivalence ratio imaging system has been developed. The technique exploits the efficient quenching of the fluorescence of organic molecules by molecular oxygen in order to determine the fuel and oxygen partial pressures simultaneously. Following pulsed planar laser excitation of fluoranthene—a specially selected fluorescent dopant—two images of the fluorescence were recorded, with the second image being delayed by several nanoseconds. Use of a rapid lifetime determination algorithm yielded first a fluorescence lifetime image, and subsequently, with the assumption of Stern-Volmer quenching, an intensity image corrected for quenching. Images of the air pressure, fuel pressure, and the equivalence ratio were obtained. The technique, which uses dual gated intensifiers coupled to a sensitive CCD camera, requires only two integrated fluorescence intensities to calculate the fluorescence lifetime accurately. In the current work, images of the turbulence-induced mixing of a methane jet into quiescent air are displayed. Images can also be obtained in flames, but the analysis of the data is uncertain because the fluorescence lifetime of fluoranthene is temperature dependent.
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Seitz, Franziska, Robert Schießl, and Detlev Markus. "Ignition by Hot Free Jets." Zeitschrift für Physikalische Chemie 231, no. 10 (October 26, 2017): 1737–71. http://dx.doi.org/10.1515/zpch-2016-0914.

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Abstract This paper describes some of our experimental studies on the re-ignition caused by jets of hot gas that interact with unburned fuel/air mixtures. The problem is approached from two complementary sides: On the one hand, phenomenological studies are conducted, which ask for the conditions under which a hot jet may cause ignition. A dedicated experiment is described which allows to create well-controlled exhaust gas jets and ambient conditions. In this experiment, parameters influencing the ignition process are varied, and the dependence of jet behavior on these parameters (i.e. pressure ratio, diameter and length of the gap through which the exhaust gas has to pass before getting into contact with ambient fuel/air) is studied. In particular, the frequency of a jet causing re-ignition in the ambient gas is studied. On the other hand, we also perform studies which are more “analytical” in nature. These attempt a more in-depth understanding, by first decomposing the hot jet ignition phenomenon into the underlying physical processes, and then studying these processes in isolation. This approach is applied to measurements of mixture fraction fields. First, non reacting isothermal variable density jets are studied. Here, the density of the gas mixture varies as to mimic the density of hot exhaust gas at varying temperatures. A laser-based non-intrusive method is introduced that allows to determine quantitative mixture fraction fields; although applied here to cold jets only, the method is also applicable to hot jets. The results show the effect of turbulence on the mixing field in and at the free jet, and allow to derive quantities that describe the statistics of the turbulent jet, like probability density functions (PDFs) and geometrical size of fluctuations.
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Dissertations / Theses on the topic "Fuel jets"

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Rodriguez, Juan Ignacio. "Acoustic excitation of liquid fuel droplets and coaxial jets." Diss., Restricted to subscribing institutions, 2009. http://proquest.umi.com/pqdweb?did=1835606741&sid=1&Fmt=2&clientId=1564&RQT=309&VName=PQD.

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Wilson, Michael. "Integral modelling of jets of variable composition in generalised crossflows." Thesis, University of Bath, 1986. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.382563.

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Pianthong, Kulachate Mechanical &amp Manufacturing Engineering Faculty of Engineering UNSW. "Supersonic liquid diesel fuel jets : generation, shock wave characteristics, auto-ignition feasibilities." Awarded by:University of New South Wales. School of Mechanical and Manufacturing Engineering, 2002. http://handle.unsw.edu.au/1959.4/20325.

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It is well known that high-speed liquid jetting is one of the most powerful techniques available to cut or penetrate material. Recently, it has been conjectured that high-speed liquid jets may be beneficial in improving combustion in such applications as SCRAM jets and direct injection diesel engines. Although there are practical limitations on maximum jet velocity, a fundamental study of the characteristics of high-speed liquid fuel jets and their auto-ignition feasibility is necessary. Important benefits could be increased combustion efficiency and enhanced emission control from improved atomisation. The generation of high-speed liquid jets (water and diesel fuel) in the supersonic to hypersonic ranges by use of a vertical single stage powder gun is described. The effect of the projectile velocity and projectile mass on the jet velocity is found experimentally. Jet exit velocities from a range of different nozzle inner profiles and nozzle hardness are thoroughly examined. The characteristics and behaviour of the high-speed liquid jet and its leading bow shock wave have been studied with the aid of a shadowgraph technique. This provides a clearer picture of each stage of the generation of hypersonic liquid jets. It makes possible the study of hypersonic diesel fuel jet characteristics and their potential for auto-ignition. The fundamental processes by which a supersonic liquid jet is generated by projectile impact have been investigated. The momentum transfer from the projectile to the liquid and the shock wave reflection within the nozzle cavity are the key items of interest. A new one-dimensional analysis has been used in order to simplify this complex and difficult problem. The impact pressure obtained from the projectile was firstly derived. Then, an investigation of the intermittent pressure increase in a closed end cavity and a simple stepped, cross-sectional nozzle were carried out. The nozzle pressure and final jet velocity were estimated and compared to a previous method and to experimental results. Some interesting characteristics found in the experiments relate well to those anticipated by the analysis. The characteristics of a hypersonic diesel fuel jet and its leading edge shock wave were assessed for their potential for auto-ignition using fuel with cetane numbers from 50-100. The investigations were performed at normal ambient air and at elevated air (110 ???C) temperature. So far, there is no sign of auto-ignition that may occur because of the temperature rise of the induced shock.
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Garcia, Fermin N. (Fermin Noel). "A nonlinear control algorithm for fuel optimal attitude control using reaction jets." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/46267.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1998.
Includes bibliographical references (p. 159-161).
We present the analysis and design of a weighted nonlinear time-fuel optimal control algorithm for spacecraft attitude dynamics using on-off gas jets. In the development of a controller, we explore four control algorithms within a single-step control framework where the step is the fundamental update time of the digital controller. The benchmark controller is a basic pulse-width modulator (PWM) with a proportional derivative controller driving the feedback loop. The second is a standard rate-ledge controller (RLC) with full-on or full-off pulse commands, while the third varies the duration of the RLC pulse commands based on the location of the states in the phase plane. The RLC algorithm is shown to well-approximate a continuous-time weighted time-fuel optimal controller. The fourth control algorithm consists of a combination of the variable-pulse RLC algorithm and a tracking-fuel optimal controller that reduces the residual error relative to the latter algorithm. Experimental data from a dynamic air-bearing testbed at Lawrence Livermore National Laboratory are used to compare the four control algorithms. The PWM scheme proves to be robust to disturbances and unmodeled dynamics and quite fast, but yields excessive fuel consumption from frequent switching. The standard RLC algorithm gives poor closed-loop performance in the presence of unmodeled dynamics and ends up being equally as fuel costly as the PWM scheme. The third algorithm, the RLC with variable pulses, significantly improves the transient and steady-state responses of the first two controllers. Via parameter tuning, we observe that this modified RLC gives excellent steady-state fuel consumption as well as reasonably fast settling times. The fourth algorithm, although more fuel efficient than the PWM and standard RLC controllers, is less efficient than the variable RLC algorithm. Matlab simulations of the four control algorithms studied are corroborated by these test results.
by Fermín Noel García.
S.M.
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Wang, Hongjuan. "Simulation of fuel injectors excited by synthetic microjets." Thesis, Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/11862.

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Asay, Rich. "A Five-Zone Model for Direct Injection Diesel Combustion." BYU ScholarsArchive, 2003. https://scholarsarchive.byu.edu/etd/100.

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Recent imaging studies have provided a new conceptual model of the internal structure of direct injection diesel fuel jets as well as empirical correlations predicting jet development and structure. This information was used to create a diesel cycle simulation model using C language including compression, fuel injection and combustion, and expansion processes. Empirical relationships were used to create a new mixing-limited zero-dimensional model of the diesel combustion process. During fuel injection five zones were created to model the reacting fuel jet: 1) liquid phase fuel 2) vapor phase fuel 3) rich premixed products 4) diffusion flame sheath 5) surrounding bulk gas. Temperature and composition in each zone is calculated. Composition in combusting zones was calculated using an equilibrium model that includes 21 species. Sub models for ignition delay, premixed burn duration, heat release rate, and heat transfer were also included. Apparent heat release rate results of the model were compared with data from a constant volume combustion vessel and two single-cylinder direct injection diesel engines. The modeled heat release results included all basic features of diesel combustion. Expected trends were seen in the ignition delay and premixed burn model studies, but the model is not predictive. The rise in heat release rate due to the diffusion burn is over-predicted in all cases. The shape of the heat release rate for the constant volume chamber is well characterized by the model, as is the peak heat release rate. The shape produced for the diffusion burn in the engine cases is not correct. The injector in the combustion vessel has a single nozzle and greater distance to the wall reducing or eliminating wall effects and jet interaction effects. Interactions between jets and the use of a spray penetration correlation developed for non-reacting jets contribute to inaccuracies in the model.
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Rees, Simon John. "Hydrodynamic instability of confined jets & wakes & implications for gas turbine fuel injectors." Thesis, University of Cambridge, 2010. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.609152.

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Stotz, Ingo [Verfasser]. "Shock Tube Study on the Disintegration of Fuel Jets at Elevated Pressures and Temperatures / Ingo Stotz." München : Verlag Dr. Hut, 2011. http://d-nb.info/1018982434/34.

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Tautschnig, Georg [Verfasser]. "Auto-Ignition and Combustion of Fuel Jets in Vitiated Co-Flow at Elevated Pressure / Georg Tautschnig." München : Verlag Dr. Hut, 2016. http://d-nb.info/1113335971/34.

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Al-Hasnawi, Adnan Ghareeb Tuaamah [Verfasser], and Eckehard [Akademischer Betreuer] Specht. "Mixing behaviour of side injection of air jets and gaseous fuel jets into the axial flow of tunnel kilns / Adnan Ghareeb Tuaamah Al-Hasnawi ; Betreuer: Eckehard Specht." Magdeburg : Universitätsbibliothek, 2016. http://d-nb.info/1117085953/34.

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Books on the topic "Fuel jets"

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Drummond, J. Philip. Mixing enhancement of reacting parallel fuel jets in a supersonic combustor. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

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John, D. St. Effect of jet injection angle and number of jets on mixing and emissions from a reacting crossflow at atmospheric pressure. [Washington, D.C.]: National Aeronautics and Space Administration STI Preogram Office, 2000.

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Jet fuel toxicology. Boca Raton: Taylor & Francis, 2011.

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Jet Fuel Toxicology. Hoboken: CRC Press, 2010.

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Miller, Bruno, Charles M. Murphy, Donovan Johnson, Michael Johnson, Frank Rosenberg, Sandy Webb, John Shideler, et al. Tracking Alternative Jet Fuel. Washington, D.C.: Transportation Research Board, 2016. http://dx.doi.org/10.17226/23696.

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Goodger, E. M. Transport fuels technology: From well to wheels, wings, and water. Norwich: Landfall Press, 2000.

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Frank, Berardino, National Research Council (U.S.). Transportation Research Board, Airport Cooperative Research Program, and United States. Federal Aviation Administration, eds. Impact of jet fuel price uncertainty on airport planning and development. Washington, D.C: Transportation Research Board, 2011.

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Abadie, Olivier. Jet fuel: How high a flyer? : demand, supply, and the endless quest for efficiency. Cambridge, MA: CERA, 2007.

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Bennett, J. S. Gas turbine combustor and engine augmentor tube sooting characteristics. Monterey, Calif: Naval Postgraduate School, 1986.

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Bartis, James T. Constraints on JP-900 jet fuel production concepts. Sant Monica, CA: RAND, 2007.

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Book chapters on the topic "Fuel jets"

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Siebers, Dennis L. "Recent Developments on Diesel Fuel Jets Under Quiescent Conditions." In Flow and Combustion in Reciprocating Engines, 257–308. Berlin, Heidelberg: Springer Berlin Heidelberg, 2008. http://dx.doi.org/10.1007/978-3-540-68901-0_5.

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Milton, B. E., and K. Pianthong. "Prediction of the driving conditions for hypersonic liquid fuel jets." In Shock Waves, 1291–96. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-27009-6_200.

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Murayama, T., N. Miyamoto, and T. Chikahisa. "Photographic Measurement of Air Entrainment in Two-Dimensional Fuel Jets." In Laser Diagnostics and Modeling of Combustion, 259–66. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-45635-0_33.

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Siebers, D. L., and L. M. Pickett. "Injection Pressure and Orifice Diameter Effects on Soot in DI Diesel Fuel Jets." In Thermo- and Fluid Dynamic Processes in Diesel Engines 2, 109–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-662-10502-3_7.

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Adhikari, Dilip Kumar. "Bio-jet Fuel." In Biofuel and Biorefinery Technologies, 187–201. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-67678-4_8.

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Hazlett, Robert N., and James M. Hall. "Jet Aircraft Fuel System Deposits." In Chemistry of Engine Combustion Deposits, 245–61. Boston, MA: Springer US, 1985. http://dx.doi.org/10.1007/978-1-4613-2469-0_13.

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Filburn, Thomas. "Fuel Systems." In Commercial Aviation in the Jet Era and the Systems that Make it Possible, 71–82. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-20111-1_6.

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Platzer, Max F., and Nesrin Sarigul-Klijn. "Production of Jet Fuel from Seawater." In The Green Energy Ship Concept, 103–4. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-58244-9_25.

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Shah, Virang G., Donald J. Hayes, and David B. Wallace. "Ink-Jet as Direct-Write Technology for Fuel Cell Packaging and Manufacturing." In Fuel Cell Electronics Packaging, 205–37. Boston, MA: Springer US, 2007. http://dx.doi.org/10.1007/978-0-387-47324-6_11.

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Filburn, Thomas. "Fuel System Failure." In Commercial Aviation in the Jet Era and the Systems that Make it Possible, 157–67. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-20111-1_13.

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Conference papers on the topic "Fuel jets"

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Pickett, Lyle M., and Dennis L. Siebers. "Fuel Effects on Soot Processes of Fuel Jets at DI Diesel Conditions." In SAE Powertrain & Fluid Systems Conference & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2003. http://dx.doi.org/10.4271/2003-01-3080.

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Stenzler, Jacob N., Jong G. Lee, J. Matthew Deepe, Domenic A. Santavicca, and Wonnam Lee. "Fuel Transfer Function Measurements in Modulated Liquid Jets." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-60673.

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Results are presented from an experimental study of the effect of operating conditions on the fuel transfer function of a modulated liquid jet injected into a high velocity crossflow. This injection configuration is commonly used in a variety of liquid-fueled gas turbine combustion systems. The transfer function relates the rate at which fuel is injected into the crossflow to the Mie scattering intensity of droplets at a given downstream location. The time-varying rate of liquid injection into the test section is measured using a high speed rotating patternator. From a spectral analysis of the input and output functions, correlations are developed to predict the phase and gain of the fuel transfer function. Experiments are conducted over a range of jet and crossflow conditions in order to determine the effect of operating conditions on the fuel transfer function.
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Davis, Staci, and Ari Glezer. "Mixing control of fuel jets using synthetic jet technology - Velocity field measurements." In 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-447.

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Ritchie, B., and J. Seitzman. "Mixing control of fuel jets using synthetic jet technology - Scalar field measurements." In 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-448.

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Mohammad, Bassam, San-Mou Jeng, and M. Gurhan Andac. "Influence of the Primary Jets and Fuel Injection on the Aerodynamics of a Prototype Annular Gas Turbine Combustor Sector." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23083.

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Transverse dilution jets are widely used in combustion systems. The current research provides a detailed study of the primary jets of a realistic annular combustion chamber sector. The combustor sector comprises an aerodynamic diffuser, inlet cowl, combustion dome, primary dilution jets, secondary dilution jets and cooling strips to provide convective cooling to the liner. The chamber contracts toward the end to fit the turbine nozzle ring. 2D PIV is employed at an atmospheric pressure drop of 4% (isothermal) to delineate the flow field characteristics. The laser is introduced to the sector through the exit flange. The interaction between the primary jets and the swirling flow as well as the sensitivity of the primary jets to perturbations is discussed. The perturbation study includes: effect of partially blocking the jets, one at a time, the effect of blocking the convective cooling holes, placed underneath the primary jets and shooting perpendicular to it. In addition, the effect of reducing the size of the primary jets as well as off-centering the primary jets is explained. Moreover, PIV is employed to study the flow field with and without fuel injection at four different fuel flow rates. The results show that the flow field is very sensitive to perturbations. The cooling air interacts with the primary jet and influences the flow field although the momentum ratio has a 100:1 order of magnitude. The results also show that the big primary jets dictate the flow field in the primary zone as well as the secondary zone. However, relatively smaller jets mainly influence the primary combustion zone because most of the jet is recirculated back to the CRZ. Also, the jet penetration is reduced with 25% and 11.5% corresponding to a 77% and 62% reduction of the jet’s area respectively. The study indicates the presence of a critical jet diameter beyond which the dilution jets have minimum impact on the secondary region. The jet off-centering shows significant effect on the flow field though it is in the order of 0.4 mm. The fuel injection is also shown to influence the flow field as well as the primary jets angle. High fuel flow rate is shown to have very strong impact on the flow field and thus results in a strong distortion of both the primary and secondary zones. The results provide useful methods to be used in the flow field structure control. Most of the effects shown are attributed to the difference in jet opposition. Hence, the results are applicable to reacting flow.
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Ishii, Eiji, Yoshihiro Sukegawa, and Hiroshi Yamada. "Fuel Spray Simulation With Collision Jets for Automobile Engines." In ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting collocated with 8th International Conference on Nanochannels, Microchannels, and Minichannels. ASMEDC, 2010. http://dx.doi.org/10.1115/fedsm-icnmm2010-30098.

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Fuel injectors for automobile engines atomize fuel into multi-scale free surfaces: liquid films formed at the fuel-injector outlet, ligaments generated by the liquid-film breakup, and droplets generated from the ligaments within the air/fuel mixture region. We previously developed a fuel spray simulation combining the liquid-film breakup near the injector outlet with the air/fuel mixture. The liquid-film breakup was simulated by a particle method. The fuel-droplet behavior in the air/fuel mixture region was simulated by a discrete droplet model (DDM). In this study, we applied our method to simulate fuel sprays from a fuel injector with collision jets. The simulation results were compared with the measurements—the mean diameter of droplet in spray, D32, was 35 percent larger than measured D32. We also studied the effects of DDM injection conditions on the spray distribution in the air/fuel mixture region—diameter distributions of injected DDM-droplets were given by the liquid-film breakup simulation, or by Nukiyama-Tanazawa’s theory. The diameter distribution of droplets near the injector outlet was found to affect the spray distribution within the air/fuel mixture region, mainly around the leading edge of spray.
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Lin, K. C., K. Kirkendall, P. Kennedy, and T. Jackson. "Spray structures of aerated liquid fuel jets in supersonic crossflows." In 35th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-2374.

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Wu, Pei-Kuan, Kevin Kirkendall, Raymond Fuller, and Abdollah Nejad. "Spray structures of liquid fuel jets atomized in subsonic crossflows." In 36th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-714.

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Pianthong, Kulachate, Masud Behnia, and Brian E. Milton. "Visualization of supersonic diesel fuel jets using a shadowgraph technique." In 24th International Congress on High-Speed Photography and Photonics, edited by Kazuyoshi Takayama, Tsutomo Saito, Harald Kleine, and Eugene V. Timofeev. SPIE, 2001. http://dx.doi.org/10.1117/12.424244.

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DRUMMOND, J. "Mixing enhancement of reacting parallel fuel jets in a supersonic combustor." In 27th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-1914.

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Reports on the topic "Fuel jets"

1

Yeboah, Yaw D., and Tiejun Bai. Study of the Sub- and Supercritical Behavior of Fuel Droplets and Jets. Fort Belvoir, VA: Defense Technical Information Center, September 1998. http://dx.doi.org/10.21236/ada353665.

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2

Lucht, Robert, and William Anderson. Structure and Dynamics of Fuel Jets Injected into a High-Temperature Subsonic Crossflow: High-Data-Rate Laser Diagnostic Investigation under Steady and Oscillatory Conditions. Office of Scientific and Technical Information (OSTI), January 2015. http://dx.doi.org/10.2172/1222578.

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Darrah, S. Jet Fuel Deoxygenation. Fort Belvoir, VA: Defense Technical Information Center, October 1988. http://dx.doi.org/10.21236/ada205006.

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Jeyashekar, Nigil, Patsy Muzzell, Eric Sattler, and Nichole Hubble. Lubricity and Derived Cetane Number Measurements of Jet Fuels, Alternative Fuels and Fuel Blends. Fort Belvoir, VA: Defense Technical Information Center, July 2010. http://dx.doi.org/10.21236/ada529442.

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Hadder, G., S. Das, R. Lee, N. Domingo, and R. Davis. Navy Mobility Fuels Forecasting System Phase 5 report: Jet fuel conversion by Pacific fuel suppliers and impacts on Navy fuel availability. Office of Scientific and Technical Information (OSTI), September 1989. http://dx.doi.org/10.2172/5458749.

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Eser, S., J. Perison, R. Copenhaver, and H. Schobert. Thermal stability of jet fuel. Office of Scientific and Technical Information (OSTI), January 1989. http://dx.doi.org/10.2172/5568036.

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Eser, S., J. Perison, R. Copenhaver, and H. Schobert. Thermal stability of jet fuel. Office of Scientific and Technical Information (OSTI), January 1989. http://dx.doi.org/10.2172/5454598.

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Harris, David T. Immunotoxicology of JP-8 Jet Fuel. Fort Belvoir, VA: Defense Technical Information Center, September 2004. http://dx.doi.org/10.21236/ada426816.

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Martel, Charles R. Properties of JP-8 Jet Fuel. Fort Belvoir, VA: Defense Technical Information Center, May 1988. http://dx.doi.org/10.21236/ada197270.

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J.E. Sinor Consultants Inc. Investigation of Byproduct Application to Jet Fuel. Office of Scientific and Technical Information (OSTI), October 2001. http://dx.doi.org/10.2172/788110.

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