Numerical Simulation of Pulse Detonation Engine Phenomena PDF Download
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Author: Xing He
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Xing He
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Prashaanth Ravindran
Publisher:
ISBN: 9780542467868
Category : Aerospace engineering
Languages : en
Pages :
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Book Description
The objective of this work was to develop a parallel algorithm that would be used in the simulation of the detonation process in the chamber of a pulse detonation engine. The emphasis is laid on reducing computation time while maintaining the accuracy of the solution and subsequently developing a numerical solution to be in agreement with real-world physical characteristics of a detonation wave initiation, build-up and progression. The flow is assumed to be unsteady, inviscid and non heat conducting. To adhere to real time effects, the flow equations are coupled with finite rate chemistry and the vibrational energy equation are based on a two-temperature model, to account for possible vibrational non-equilibrium. Finite Volume formulation is employed to ensure conservation and to allow proper handling of discontinuities. Runge-Kutta integration scheme has been utilized to obtain a time-accurate solution, with Roes flux difference splitting scheme applied to cell face fluxes. For higher-order spatial accuracy, MUSCL technique is employed. Equation stiffness has been taken care of by observing point implicit treatment of the source terms and detonation is initiated with the application of a localized hot-spot. The parallel algorithm has been developed using Message Passing Interface standard developed by the Argonne National Laboratory for the purposes of solving equations in a distributed environment. A proto-cluster of Beowulf type consisting of 8-nodes has been assembled and made operational, and an algorithm which performs space-time calculations simultaneously on the nodes has been successfully developed. A two-step global model for Hydrogen-Air mixture has been selected for validating the parallel algorithm with existing results, to establish veracity and accuracy while reducing computation time to almost a fourth. Excellent agreement has been found on comparison of the results with the same code when solved in a single processor.
Author: Jiun-Ming Li
Publisher: Springer
ISBN: 3319689061
Category : Technology & Engineering
Languages : en
Pages : 246
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Book Description
This book focuses on the latest developments in detonation engines for aerospace propulsion, with a focus on the rotating detonation engine (RDE). State-of-the-art research contributions are collected from international leading researchers devoted to the pursuit of controllable detonations for practical detonation propulsion. A system-level design of novel detonation engines, performance analysis, and advanced experimental and numerical methods are covered. In addition, the world’s first successful sled demonstration of a rocket rotating detonation engine system and innovations in the development of a kilohertz pulse detonation engine (PDE) system are reported. Readers will obtain, in a straightforward manner, an understanding of the RDE & PDE design, operation and testing approaches, and further specific integration schemes for diverse applications such as rockets for space propulsion and turbojet/ramjet engines for air-breathing propulsion. Detonation Control for Propulsion: Pulse Detonation and Rotating Detonation Engines provides, with its comprehensive coverage from fundamental detonation science to practical research engineering techniques, a wealth of information for scientists in the field of combustion and propulsion. The volume can also serve as a reference text for faculty and graduate students and interested in shock waves, combustion and propulsion.
Author: Hyungwon Kim
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Ajjay Omprakas
Publisher:
ISBN:
Category :
Languages : en
Pages : 79
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Book Description
The objective of this research is to simulate normal detonation combustion which is a mode of operation for a Pulsed Detonation Engine (PDE). A supersonic flow with stoichiometric hydrogen-air mixture is made to impinge on a wedge, thus resulting in increasing the temperature and pressure across a shock wave leading to the formation of detonation wave. Different modes of the operations can be simulated by varying the incoming Mach number, pressure, temperature and equivalence ratio. For the case of normal detonation wave mode which is an unsteady process, after the detonation being initiated due to the shock induced by the wedge, the detonation wave propagates upstream in the flow as the combustion chamber Mach number is lower than the C-J Mach number. The concept of detonation wave moving upstream and downstream is controlled by changing the incoming flow field properties. By this method the unsteady normal detonation wave is made to oscillate in the combustion chamber leading to a continuous detonation combustion. The intention of this research is to simulate two cycles of detonation combustion in order to determine the frequency and to obtain the variation of flow properties at the exit plain with respect to time.
Author: A. A. Boni
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Author: Weipeng Hu
Publisher: Springer Nature
ISBN: 9811974357
Category : Technology & Engineering
Languages : en
Pages : 540
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Book Description
To make the content of the book more systematic, this book mainly briefs some related basic knowledge reported by other monographs and papers about geometric mechanics. The main content of this book is based on the last 20 years’ jobs of the authors. All physical processes can be formulated as the Hamiltonian form with the energy conservation law as well as the symplectic structure if all dissipative effects are ignored. On the one hand, the important status of the Hamiltonian mechanics is emphasized. On the other hand, a higher requirement is proposed for the numerical analysis on the Hamiltonian system, namely the results of the numerical analysis on the Hamiltonian system should reproduce the geometric properties of which, including the first integral, the symplectic structure as well as the energy conservation law.
Author: John H. S. Lee
Publisher: Cambridge University Press
ISBN: 9780521897235
Category : Technology & Engineering
Languages : en
Pages : 400
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Book Description
This book introduces the detonation phenomenon in explosives. It is ideal for engineers and graduate students with a background in thermodynamics and fluid mechanics. The material is mostly qualitative, aiming to illustrate the physical aspects of the phenomenon. Classical idealized theories of detonation waves are presented first. These permit detonation speed, gas properties ahead and behind the detonation wave, and the distribution of fluid properties within the detonation wave itself to be determined. Subsequent chapters describe in detail the real unstable structure of a detonation wave. One-, two-, and three-dimensional computer simulations are presented along with experimental results using various experimental techniques. The important effects of confinement and boundary conditions and their influence on the propagation of a detonation are also discussed. The final chapters cover the various ways detonation waves can be formed and provide a review of the outstanding problems and future directions in detonation research.
Author: Matthew John Grismer
Publisher:
ISBN:
Category :
Languages : en
Pages : 450
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Author: Anthony Scott Hasler
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
The performance of a hybrid mixed flow turbofan (with detonation tubes installed in the bypass duct) is investigated in this study and compared with a baseline model of a mixed flow turbofan with a standard combustion chamber as a duct burner. Previous studies have shown that pulsed detonation combustors have the potential to be more efficient than standard combustors, but they also present new challenges that must be overcome before they can be utilized. The Numerical Propulsion System Simulation (NPSS) will be used to perform the analysis with a pulsed detonation combustor model based on a numerical simulation done by Endo, Fujiwara, et. al. Three different cases will be run using both models representing a take-off situation, a subsonic cruise and a supersonic cruise situation. Since this study investigates a transient analysis, the pulse detonation combustor is run in a rig setup first and then its pressure and temperature are averaged for the cycle to obtain quasi-steady results.
