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Author: J. TAMAGNO Publisher: ISBN: Category : Languages : en Pages : 1
Book Description
Experiments on spontaneous combustion characteristics of hydrogen injected into a supersonic stream of hot air are described in detail. The results are presented and compared with a theory developed for premixed reactants. The experimental data show that if the initial static temperature and the static pressure of the air stream are high enough then diffusion will be rate controlling and a mixing theory using equilibrium chemistry could be used in analyzing the combustion process. If the chemical reactions are slow, the behavior of the combustion process can be studied as a system where mixing and diffusive effects are absent. The ignition delay times inferred from the initiation of the pressure rise along the burner are in good agreement with those predicted by the empirical correlation. The static temperature exerts a greater influence on the ignition delay time than the static pressure. The static pressure level is an important parameter in determining the time for complete combustion. (Author).
Author: J. TAMAGNO Publisher: ISBN: Category : Languages : en Pages : 1
Book Description
Experiments on spontaneous combustion characteristics of hydrogen injected into a supersonic stream of hot air are described in detail. The results are presented and compared with a theory developed for premixed reactants. The experimental data show that if the initial static temperature and the static pressure of the air stream are high enough then diffusion will be rate controlling and a mixing theory using equilibrium chemistry could be used in analyzing the combustion process. If the chemical reactions are slow, the behavior of the combustion process can be studied as a system where mixing and diffusive effects are absent. The ignition delay times inferred from the initiation of the pressure rise along the burner are in good agreement with those predicted by the empirical correlation. The static temperature exerts a greater influence on the ignition delay time than the static pressure. The static pressure level is an important parameter in determining the time for complete combustion. (Author).
Author: Antonio Ferri Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 136
Book Description
A theoretical and experimental investigation of mixing and supersonic combustion is presented. A review of the problem under investigation is given. Then an analysis of inviscid flow fields with a finite rate chemistry for a hydrogen-air reaction is presented, an an analysis of a turbulent mixing for flows with large density gradients with no chemical reaction is presented. The analysis is compared wit the experimental results. Results of the experiments in upersonic combustion are presented. (Author).
Author: William H. Heiser Publisher: AIAA ISBN: 9781563470356 Category : Science Languages : en Pages : 632
Book Description
An almost entirely self-contained engineering textbook primarily for use in undergraduate and graduate courses in airbreathing propulsion. It provides a broad and basic introduction to the elements needed to work in the field as it develops and grows. Homework problems are provided for almost every individual subject. An extensive array of PC-based user-friendly computer programs is provided in order to facilitate repetitious and/or complex calculations. Annotation copyright by Book News, Inc., Portland, OR
Author: Corin Segal Publisher: Cambridge University Press ISBN: 0521838150 Category : Technology & Engineering Languages : en Pages : 271
Book Description
Demand for high-speed propulsion has renewed development of the supersonic combustion ramjet engine (Scramjet engine) for hypersonic flight applications.
Author: Central aerodynamic inst moscow (Russia) Publisher: ISBN: Category : Languages : en Pages : 57
Book Description
Final report summarizes shortly main results of the quarterly reports and presents experimental results on self-ignition and combustion stabilization in supersonic flow using free recirculation zone. Tests are conducted at hypersonic facility TsAGI T-131B. Measurements are performed in a nearly matched supersonic jet at the exit of two-dimensional channel over Mach number range M=2.O-2.8 at stagnation temperature range Tt=1200-1400K. initial thickness of jet was equal 67 mm. Self-ignition and stabilization are obtained at Tt=1400K. Self-ignition was absent at Tt=1200K, 1300K. Thickness of free recirculation zone was about 25-30 mm.
Author: Mingbo Sun Publisher: Springer Nature ISBN: 9811535957 Category : Technology & Engineering Languages : en Pages : 380
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: Corin Segal Publisher: Cambridge University Press ISBN: 1139478192 Category : Technology & Engineering Languages : en Pages : 271
Book Description
The renewed interest in high-speed propulsion has led to increased activity in the development of the supersonic combustion ramjet engine for hypersonic flight applications. In the hypersonic regime the scramjet engine's specific thrust exceeds that of other propulsion systems. This book, written by a leading researcher, describes the processes and characteristics of the scramjet engine in a unified manner, reviewing both theoretical and experimental research. The focus is on the phenomena that dictate the thermo-aerodynamic processes encountered in the scramjet engine, including component analyses and flowpath considerations; fundamental theoretical topics related to internal flow with chemical reactions and non-equilibrium effects, high-temperature gas dynamics, and hypersonic effects are included. Cycle and component analyses are further described, followed by flowpath examination. Finally, the book reviews experimental and theoretical capabilities and describes ground testing facilities and computational fluid dynamics facilities developed for the study of time-accurate, high-temperature aerodynamics.
Author: James E. Drewry Publisher: ISBN: Category : Airplanes Languages : en Pages : 17
Book Description
An investigation of supersonic combustion as related to propulsive systems for high Mach number, high altitude flight is described. A method of laboratory simulation is employed which is considered to be suitable for fundamental studies of diffusional-controlled supersonic combustion under conditions approaching those of actual flight. A numerical analysis of the mixing and combustion processes for an axisymmetric hydrogen-air ducted flow system was carried out, using a computer code based upon boundary layer concepts and including the effects of finite-rate chemistry. A limited parametric study of the combustor flow field was made for a Mach number range of 1.5 to 2.5 for the injected air stream. Hydrogen injection is central and parallel to the air stream and is assumed to occur sonically. A matched pressure condition between the fuel and air streams is assumed to exist at the combustor inlet. Inlet static pressures in the range of 0.1 to 0.2 atmospheres were considered. Results of the parametric study indicated the inlet conditions required to achieve auto-ignition within a reasonable combustor length. Based on the numerical data obtained, a mixing and combustion chamber was designed and fabricated for the performance of experimental tests under conditions closely matching those of the numerical study. Experimental data from a number of laboratory tests in which supersonic combustion was obtained are presented and discussed. (Author).
Author: J. TAMAGNO
Author: J. TAMAGNO
Author: Antonio Ferri
Author: C. L. Yates
Author: William H. Heiser
Author: Corin Segal
Author: Central aerodynamic inst moscow (Russia)
Author: E. T. Curran
Author: Mingbo Sun
Author: Corin Segal
Author: James E. Drewry