Fundamental Studies of Inkjet Based Fuel Injection Technology for Pulsed Detonation Engines PDF Download
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Author:
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ISBN:
Category :
Languages : en
Pages : 14
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Book Description
The University of Colorado, in collaboration with TDA Research Inc., worked on using inkjet type concepts to develop MEMS technology for fuel injection for pulsed detonation engines (PDE). We considered this approach because of the requirements of periodic injection, small droplet size and distributed injection. We demonstrated the potential for injectors based on inkjet technology to meet PDE needs. We evaluated commercially available inkjet technologies, developed a large array atomizer conceptual design, and reviewed and compared current atomization techniques to military specifications. The results of our study showed that new injection technology would be required and that inkjet-type MEMS technology does have the potential to meet PDE needs. During the first year of the AFOSR program we explored issues such as material compatibility, flow throughput, and actuation design. We carried out finite element stress analysis simulations for various pump configurations and volume of fluid (VOF) analysis of jet breakup. During the second year our work focused on developing comprehensive simulations of real pump designs. We successfully modeled a passive valve pump and showed that the simulation correctly predicts behavior observed in the literature. During the final year of funding we focused on design optimization using multi-physics simulations and assisting in prototype testing.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Book Description
The University of Colorado, in collaboration with TDA Research Inc., worked on using inkjet type concepts to develop MEMS technology for fuel injection for pulsed detonation engines (PDE). We considered this approach because of the requirements of periodic injection, small droplet size and distributed injection. We demonstrated the potential for injectors based on inkjet technology to meet PDE needs. We evaluated commercially available inkjet technologies, developed a large array atomizer conceptual design, and reviewed and compared current atomization techniques to military specifications. The results of our study showed that new injection technology would be required and that inkjet-type MEMS technology does have the potential to meet PDE needs. During the first year of the AFOSR program we explored issues such as material compatibility, flow throughput, and actuation design. We carried out finite element stress analysis simulations for various pump configurations and volume of fluid (VOF) analysis of jet breakup. During the second year our work focused on developing comprehensive simulations of real pump designs. We successfully modeled a passive valve pump and showed that the simulation correctly predicts behavior observed in the literature. During the final year of funding we focused on design optimization using multi-physics simulations and assisting in prototype testing.
Author: Eric M. Braun
Publisher:
ISBN:
Category : Combustion engineering
Languages : en
Pages :
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Book Description
A series of related analytical and experimental studies are focused on utilizing detonations for emerging propulsion and power generation devices. An understanding of the physical and thermodynamic processes for this unsteady thermodynamic cycle has taken over 100 years to develop. An overview of the thermodynamic processes and development history is provided. Thermodynamic cycle analysis of detonation-based systems has often been studied using surrogate models. A real gas model is used for a thermal e ciency prediction of a detonation wave based on the work and heat speci ed by process path diagrams and a control volume analysis. A combined rst and second law analysis aids in understanding performance trends for di erent initial conditions. A cycle analysis model for an airbreathing, rotating detonation wave engine (RDE) is presented. The engine consists of a steady inlet system with an isolator which delivers air into an annular combustor. A detonation wave continuously rotates around the combustor with side relief as the ow expands towards the nozzle. Air and fuel enter the combustor when the rarefaction wave pressure behind the detonation front drops to the inlet supply pressure. To create a stable RDE, the inlet pressure is matched in a convergence process with the average combustor pressure by increasing the annulus channel width with respect to the isolator channel. Performance of this engine is considered using several parametric studies. RDEs require a fuel injection system that can cycle beyond the limits of mechanical valves. Fuel injectors composed of an ori ce connected to a small plenum cavity were mounted on a detonation tube. These fuel injectors, termed uidic valves, utilize their geometry and a supply pressure to deliver fuel and contain no moving parts. Their behavior is characterized in order to determine their feasibility for integration with high-frequency RDEs. Parametric studies have been conducted with the type of fuel injected, the ori ce diameter, and the plenum cavity pressure. Results indicate that the detonation wave pressure temporarily interrupts the uidic valve supply, but the wave products can be quickly expelled by the fresh fuel supply to allow for refueling. The interruption time of the valve scales with injection and detonation wave pressure ratios as well as a characteristic time. The feasibility of using a detonation wave as a source for producing power in conjunction with a linear generator is considered. Such a facility can be constructed by placing a piston{spring system at the end of a pulsed detonation engine (PDE). Once the detonation wave re ects o the piston, oscillations of the system drive the linear generator. An experimental facility was developed to explore the interaction of a gaseous detonation wave with the piston. Experimental results were then used to develop a model for the interaction. Governing equations for two engine designs are developed and trends are established to indicate a feasible design space for future development.
Author: P. P. Lo
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Wadysaw Mitianiec
Publisher: Nova Science Publishers
ISBN: 9781536124729
Category : Two-stroke cycle engines
Languages : en
Pages : 0
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Book Description
The main goal of the book is the presentation of the last theoretical and experimental works concerning fuel injection systems, mainly in small power two-stroke engines as well as in marine engines. This book includes thirteen chapters devoted to the processes of fuel injection and the combustion that takes place in a stratified charge within the cylinders of two-stroke engines. In the first two chapters, the division into different injection systems in two-stroke engines and each injection system is briefly described. Various theoretical and practical solutions of fueling system designs are described. In Chapter Three, mathematical models, the spatial movement of gas in the cylinder and the combustion chamber are introduced, taking into account the turbulence of the charge. Chapter Four relates to the behavior of fuel injected into the gaseous medium, including evaporation processes, disintegration and processes occurring while the fuel drops connect with the wall. The next section describes the zero-dimensional model of fuel injection in two-stroke engines along with examples of numerical calculations. The sixth chapter is devoted to CFD multi-dimensional models of movement and evaporation of the fuel in a closed gaseous medium, occurring also in other engine types. Chapter Seven describes a two-zone model of the combustion process and the effect of the geometry of the combustion chamber on the flame propagation with a simplified verification model of combustion. Chapter Eight compares the propagation phase of gas and liquid fuels concerning direct fuel injection as well as the direct fuel injection from the cylinder head and the thermodynamic parameters of the charge. The formation of the components during the combustion process in the direct fuel injection two-stroke engine was obtained by numerical calculations and results are discussed in Chapter Nine. Chapter Ten describes the parameters of the two-stroke engine with a direct fuel injection carried out at the Cracow University of Technology. Additionally, the chapter presents CFD simulations of fuel propagation and combustion processes, taking into account the formation of toxic components and exhaust gas emission. The processes of two direct rich mixture injection systems FAST and RMIS developed in CUT are presented in Chapter Eleven. Miscellaneous problems of direct fuel injection, such as characteristics of fuel injectors, problems of direct gaseous fuel injection, and the application of fuelling systems in outboard engines and snowmobile vehicles are presented in Chapter Twelve. A comparison of working parameters in two- and four stroke engines is also mapped out. The last chapters contain the final conclusions and remarks concerning fuel injection and emission of exhaust gases in small two-stroke engines. This book is a comprehensive monograph on fuel injection. The author presents a series of theoretical and design information from his own experience and on the basis of the works of other authors. The main text intends to direct fuel injection with respect to gas motion in the combustion chamber and influence the injection parameters for exhaust emission. The book presents its own theoretical work and experimental tests concerning a two-stroke gasoline engine with electrically controlled direct fuel injection. The book describes the processes of a general nature also occurring in other types of engines and presents a comparison of different injection systems on working parameters and gas emission. The book contains 294 images, 290 equations and 16 tables obtained from the CFD simulation and experimental works.
Author: Władysław Mitianiec
Publisher:
ISBN: 9781536129410
Category : Two-stroke cycle engines
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 65
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Book Description
Practical use of the pulse detonation engine as a form of propulsion for future aircraft and missile platforms depends upon the ability to reliably detonate a fuel air mixture at high frequencies in order to produce an acceptable level of thrust, and to take advantage of the higher thermodynamic efficiency available from the pulse detonation engine combustion cycle. This research thesis focused on improving and mapping fuel fraction delivery profiles for a valveless pulse detonation engine. The gas dynamic conditions downstream of inlet manifold isolation chokes were evaluated for a number of geometries with Computational Fluid Dynamics software in an effort to reduce areas of recirculation in the inlet manifold of the engine and improve fuel delivery profiles. Based on the results from this modeling a new inlet manifold configuration was designed, installed and evaluated in laboratory experimentation. Laboratory testing was performed at multiple air and fuel mass flow rates using ethylene as the fuel. Absorption spectroscopy, using a He-Ne laser tuned to the 3.39m︡ wavelength with known spectroscopic fuel absorption cross sections, was used to measure fuel mass fraction profiles for each engine inlet geometry at various flow rates. Additionally, JP10 fuel concentration profiles were determined for several fuel injector actuation pressures and at various alignments using the same diagnostic approach.
Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 63
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Book Description
The Pulse Detonation Engine offers the Department of Defense a new low cost, light weight, and efficient solution to supersonic flight on many of its small airborne platforms. In the past, both liquid fuel and gaseous fuel designs have been partially developed and tested. Several aspects of these configurations have led to the need for the development of a new design, in particular the reduction of total pressure losses, and the removal of auxiliary oxygen system previously required to initiate a detonation wave in fuel-air mixtures within practical distances. Furthermore, higher repetition rates are required for practical thrust levels, as well as the use of liquid fuels, as these are more attractive due to their higher energy densities. A new PDE configuration was designed to operate on the liquid fuel, JP-10. The fuel injection system was characterized using laser diagnostics so that the fuel injection strategy could be optimized for the specified operating conditions. The timing parameters for the fuel-air injection profile were characterized as well in order to deliver the desired amount and duration. This was a concurrent effort with computational simulations of the internal flow paths, design/integration of a novel transient plasma ignition system, and ongoing developments of a performance measurement test rig.
Author: Swati Chandran Thirumangalath
Publisher:
ISBN:
Category :
Languages : en
Pages : 65
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The filling process of a pulsed detonation engine with fuel and oxidizer should be carried out quickly in order to maintain a high frequency of operation. The objectives of this research were to model an efficient inlet system for filling the detonation tube with fuel/air mixture in stoichiometric ratio and to evaluate various filling schemes. Numerical modeling of the filling process was done using PointwiseTM for meshing and FluentTM as the flow solver, solving the Reynolds-averaged Navier-Stokes equations with a k-[epsilon] turbulence model. Five different filling configurations were studied, including endwall, normal and angled, opposing and staggered sidewall. The fuel choices were biogas, hydrogen, methane, propane and octane all in the gaseous state. Oxidizer considered was air. The reactants were injected pre-mixed with an equivalence ratio of unity, at different velocities into a tube initially filled with ambient air at standard conditions. The benchmark was when the tube was 90 percent filled. It was found that staggered sidewall injection was the best configuration for rapidly filling the tube.
Author:
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ISBN:
Category : Airplanes
Languages : en
Pages : 514
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Book Description
Author: National Academies of Sciences, Engineering, and Medicine
Publisher: National Academies Press
ISBN: 0309664225
Category : Science
Languages : en
Pages : 137
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Book Description
Leadership in gas turbine technologies is of continuing importance as the value of gas turbine production is projected to grow substantially by 2030 and beyond. Power generation, aviation, and the oil and gas industries rely on advanced technologies for gas turbines. Market trends including world demographics, energy security and resilience, decarbonization, and customer profiles are rapidly changing and influencing the future of these industries and gas turbine technologies. Technology trends that define the technological environment in which gas turbine research and development will take place are also changing - including inexpensive, large scale computational capabilities, highly autonomous systems, additive manufacturing, and cybersecurity. It is important to evaluate how these changes influence the gas turbine industry and how to manage these changes moving forward. Advanced Technologies for Gas Turbines identifies high-priority opportunities for improving and creating advanced technologies that can be introduced into the design and manufacture of gas turbines to enhance their performance. The goals of this report are to assess the 2030 gas turbine global landscape via analysis of global leadership, market trends, and technology trends that impact gas turbine applications, develop a prioritization process, define high-priority research goals, identify high-priority research areas and topics to achieve the specified goals, and direct future research. Findings and recommendations from this report are important in guiding research within the gas turbine industry and advancing electrical power generation, commercial and military aviation, and oil and gas production.
