Thrust Chamber Dynamics of Multi-tubepulse Detonation Engines PDF Download
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Author: Fuhua Ma
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Fuhua Ma
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 510
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Book Description
Author: Gabriel Roy
Publisher: Butterworth-Heinemann
ISBN: 0123693942
Category : Business & Economics
Languages : en
Pages : 505
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Book Description
Chemical propulsion comprises the science and technology of using chemical reactions of any kind to create thrust and thereby propel a vehicle or object to a desired acceleration and speed. Cumbustion Processes in Propulsion focuses on recent advances in the design of very highly efficient, low-pollution-emitting propulsion systems, as well as advances in testing, diagnostics and analysis. It offers unique coverage of Pulse Detonation Engines, which add tremendous power to jet thrust by combining high pressure with ignition of the air/fuel mixture. Readers will learn about the advances in the reduction of jet noise and toxic fuel emissions-something that is being heavily regulated by relevant government agencies. Lead editor is one of the world's foremost combustion researchers, with contributions from some of the world's leading researchers in combustion engineering Covers all major areas of chemical propulsion-from combustion measurement, analysis and simulation, to advanced control of combustion processes, to noise and emission control Includes important information on advanced technologies for reducing jet engine noise and hazardous fuel combustion emissions
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 548
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Author: Jiun-Ming Li
Publisher: Springer
ISBN: 3319689061
Category : Technology & Engineering
Languages : en
Pages : 246
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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:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 672
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720484080
Category :
Languages : en
Pages : 72
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Book Description
A pulse detonation engine (PDE) uses a series of high frequency intermittent detonation tubes to generate thrust. The process of filling the detonation tube with fuel and air for each cycle may yield non-uniform mixtures. Lack of mixture uniformity is commonly ignored when calculating detonation tube thrust performance. In this study, detonation cycles featuring idealized non-uniform H2/air mixtures were analyzed using the SPARK two-dimensional Navier-Stokes CFD code with 7-step H2/air reaction mechanism. Mixture non-uniformities examined included axial equivalence ratio gradients, transverse equivalence ratio gradients, and partially fueled tubes. Three different average test section equivalence ratios (phi), stoichiometric (phi = 1.00), fuel lean (phi = 0.90), and fuel rich (phi = 1.10), were studied. All mixtures were detonable throughout the detonation tube. It was found that various mixtures representing the same test section equivalence ratio had specific impulses within 1 percent of each other, indicating that good fuel/air mixing is not a prerequisite for optimal detonation tube performance.Perkins, Hugh DouglasGlenn Research CenterNAVIER-STOKES EQUATION; PULSE DETONATION ENGINES; FUEL COMBUSTION; FUEL-AIR RATIO; DETONATION; DETONABLE GAS MIXTURES; DETONATION WAVES; TEST CHAMBERS; SPECIFIC IMPULSE; THRUST; NONUNIFORMITY; COMPUTATIONAL FLUID DYNAMICS
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 666
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Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 570
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 466
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