Experimental Efforts for Supersonic Combustion Utilizing Hydrocarbon Fuels with Plasma Ignition PDF Download
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Author: Paul David Rudolph
Publisher:
ISBN:
Category :
Languages : en
Pages : 306
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Book Description
Author: Paul David Rudolph
Publisher:
ISBN:
Category :
Languages : en
Pages : 306
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 27
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Book Description
The Air Force plasma ignition program is assessing the prospect of main-fuel ignition with plasma generating devices in a supersonic flow. As the study progresses baseline conditions of operation are being established such as the required operational time of the device to initiate a combustion shock train. The two plasma torches currently under investigation consist of a DC constricted-arc design from the Virginia Polytechnic Institute and State University and an AC unconstricted-arc design based on a modified spark-plug from Polytechnic University. The plasma torches are realistic in size and operate within current power constraints while differing substantially in orifice geometry. In order to compare the potential of each concept the flow physics of each part of the igniter/fuel-injector/combustor system are being studied. In each step of the program, we utilize CFD and experiments to help define and advance the ignition process. To understand the constraints involved with ignition process of a hydrocarbon fuel jet an experimental effort to study gaseous and liquid hydrocarbons is underway, involving the testing of ethylene and JP-7 fuels with nitrogen and air plasmas. Results from the individual igniter studies have shown the plasma igniters to produce hot pockets of highly excited gas with peak temperatures up to (and in some cases above) 5000 K at only 2-kW total input power. In addition ethylene and JP-7 flames with a significant level of OH as determined by OH PLIF were also produced in a Mach-2 supersonic flow with a total temperature and pressure of 590 K and 5.4 atm respectively.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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This report results from a contract tasking TsAGl as follows: The contractor will investigate combustion of kerosene using barbotage by hydrogen and air in the aeroramp configuration at M=2.5 as described in his proposal dated 1 Jun 98.
Author: Simon Slutsky
Publisher:
ISBN:
Category :
Languages : en
Pages : 73
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Book Description
An experimental study was carried out to investigate the combustion of a liquid hydrocarbon (hexane) injected into a supersonic stream. Injection modes included wall and central injection configurations. Extremely rapid and intense heat release phenomena were obtained. It was concluded that this mode of combustion could be made to compete with that of pure gas phase combustion for many technological applications. A preliminary theoretical model of the combustion mechanism was constructed which accounts for many of the observed phenomena, and which explains the very rapid combustion characteristics.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 150
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This report results from a contract tasking Institute of High Temperatures RAS as follows: The contractor will investigate the phenomena of plasma-induced ignition of high speed, low temperature air-fuel mixtures using a recirculation zone created by a rearward facing wall step and wall cavity. The plasma will be generated using a multi-electrode, quasi direct-current electrical discharge. Fuel injectors will be located in the recirculation zone. The effects of plasma induced ignition, mixing intensification, flame-stabilization, and combustion completeness will be evaluated. Investigations will be carried out using both gaseous and liquid hydrocarbon fuels. Diagnostics include high speed video, Schlieren photography, pressure distribution measurements, electrical measurements, optical spectroscopy and infrared absorption spectroscopy. The research is mainly experimental, but will include several analytical and computational efforts for better understanding and verification of the results.
Author: Mingbo Sun
Publisher: Springer Nature
ISBN: 9811535957
Category : Technology & Engineering
Languages : en
Pages : 380
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Book Description
This book describes the unsteady phenomena needed to understand supersonic combustion. Following an initial chapter that introduces readers to the basic concepts in and classical studies on unsteady supersonic combustion, the book highlights recent studies on unsteady phenomena, which offer insights on e.g. interactions between acoustic waves and flames, flow dominating instability, ignition instability, flame flashback, and near-blowout-limit combustion. In turn, the book discusses in detail the fundamental mechanisms of these phenomena, and puts forward practical suggestions for future scramjet design.
Author: Steven William Vavrik
Publisher:
ISBN:
Category :
Languages : en
Pages : 274
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Book Description
Author: Sangchul Lee
Publisher: Springer Nature
ISBN: 9811926352
Category : Technology & Engineering
Languages : en
Pages : 1396
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Book Description
This proceeding comprises peer-reviewed papers of the 2021 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2021), held from 15-17 November 2021 in Jeju, South Korea. This book deals with various themes on computational fluid dynamics, wind tunnel testing, flow visualization, UAV design, flight simulation, satellite attitude control, aeroelasticity and control, combustion analysis, fuel injection, cooling systems, spacecraft propulsion and so forth. So, this book can be very helpful not only for the researchers of universities and academic institutes, but also for the industry engineers who are interested in the current and future advanced topics in aerospace technology.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
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Book Description
Recent progress on the authors' efforts to develop a detailed kinetic mechanism for C(sub 8)H(sub m) hydrocarbons and practical plasma igniters for plasma-assisted combustion are discussed. Shock tube validation experiments made in argon using a fixed stoichiometry (PHI = 1.0), pressures of approximately 0.95 and 1.05 atm, and temperatures ranging from 850 to 1200 K (post-reflected shock) are presented. The mechanism is being expanded to include electron kinetics and to allow for a degree of nonequilibrium modeled with separate electron and gas temperatures. Quantum calculations used to derive needed electron impact ionization/dissociation cross-sections for hydrocarbons are discussed. In addition, ignition of ethylene fuel in a Mach 2 supersonic flow with a total temperature of 590 K and pressure of 5.4 atm is demonstrated using a low frequency discharge with peak and average powers reaching 8 kW and 2.8 kW, respectively. (7 figures, 28 refs.).
Author: S. G. Chianese
Publisher:
ISBN:
Category :
Languages : en
Pages :
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