Author: A. A. TahaPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Numerical Simulation of Ignition/combustion Characteristics of Ethylene in Supersonic Air Streams
Author: A. A. TahaUnsteady Supersonic Combustion
Author: Mingbo SunPublisher: 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.
Towards a Numerical Simulation of Supersonic Mixing & Combustion
Author: Mohammed KamelPublisher: LAP Lambert Academic Publishing
ISBN: 9783659387043
Category :
Languages : en
Pages : 208
Book Description
The design and off-design studies of the hypersonic air-breathing engines face many challenges, due to the complexity of their internal flows. The mixing and combustion processes in Supersonic-Combustion Ramjet (scramjet) engines involve complicated aerothermochemical features, such as: the interactions between shock-waves and boundary-layer, the shock induced-combustion and the recirculation zones. In this study, a numerical solver is developed and validated to be an efficient design tool capable of simulating these complicated flow features of the supersonic combustors. For the code validation, several test cases are considered to monitor the code ability to solve for the diffusive and turbulent fluxes, and the chemical source term. In addition, the code is validated by resolving the transverse sonic injection into supersonic air flow in the case of Helium injection from a flat plate, and in the case of Hydrogen injection in a single-strut scramjet engine. The effectiveness of this injection technique in mixing and flame-holding is demonstrated. The results show good agreement with the previous numerical and experimental investigations, and prove the simulator's accuracy.
On the Numerical Simulation of Supersonic Combustion
Author: Fenggan ZhuangNumerical Simulation of Supersonic Combustion
Author: A. NeophytouAIAA Aerospace Sciences Meeting and Exhibit, 42nd
Author: Chemical Abstracts
Author: Effects of Supersonic Vitiated/clean Air on Ignition/combustion Characteristics of Hydrogen Fuel
Author: S. N. TiwariExperimental Results on Supersonic Combustion
Author: J. TAMAGNOPublisher:
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).
Supersonic Combustion Studies at Low Density Conditions
Author: James E. DrewryPublisher:
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).