Proceedings of the Gas Dynamics Symposium on Aerothermochemistry PDF Download
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Author: Northwestern University (Evanston, Ill.)
Publisher:
ISBN:
Category : Combustion
Languages : en
Pages : 296
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Book Description
Author:
Publisher:
ISBN:
Category : Rocketry
Languages : en
Pages : 456
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Book Description
Author: Boris E. Gelfand
Publisher: Springer Science & Business Media
ISBN: 3642253512
Category : Science
Languages : en
Pages : 339
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Book Description
The potential of hydrogen as an important future energy source has generated fresh interest in the study of hydrogenous gas mixtures. Indeed, both its high caloricity and reactivity are unique properties, the latter underscoring safety considerations when handling such mixtures. The present monograph is devoted to the various aspects of hydrogen combustion and explosion processes. In addition to theoretical and phenomenological considerations, this work also collates the results of many experiments from less well known sources. The text reviews the literature in this respect, thereby providing valuable information about the thermo-gas-dynamical parameters of combustion processes for selected experimental settings in a range of scientific and industrial applications.
Author: Irvin Glassman
Publisher: Academic Press
ISBN: 0080568815
Category : Technology & Engineering
Languages : en
Pages : 794
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Book Description
Combustion Engineering, a topic generally taught at the upper undergraduate and graduate level in most mechanical engineering programs, and many chemical engineering programs, is the study of rapid energy and mass transfer usually through the common physical phenomena of flame oxidation. It covers the physics and chemistry of this process and the engineering applications - from the generation of power such as the internal combustion automobile engine to the gas turbine engine. Renewed concerns about energy efficiency and fuel costs, along with continued concerns over toxic and particulate emissions have kept the interest in this vital area of engineering high and brought about new developments in both fundamental knowledge of flame and combustion physics as well as new technologies for flame and fuel control. - New chapter on new combustion concepts and technologies, including discussion on nanotechnology as related to combustion, as well as microgravity combustion, microcombustion, and catalytic combustion - all interrelated and discussed by considering scaling issues (e.g., length and time scales) - New information on sensitivity analysis of reaction mechanisms and generation and application of reduced mechanisms - Expanded coverage of turbulent reactive flows to better illustrate real-world applications - Important new sections on stabilization of diffusion flames. For the first time, the concept of triple flames will be introduced and discussed in the context of diffusion flame stabilization
Author: Jet Propulsion Laboratory (U.S.)
Publisher:
ISBN:
Category : Jet propulsion
Languages : en
Pages : 100
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Book Description
Author: Mostafa Barzegar Gerdroodbary
Publisher: Butterworth-Heinemann
ISBN: 0128211407
Category : Technology & Engineering
Languages : en
Pages : 230
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Book Description
Scramjet engines are a type of jet engine and rely on the combustion of fuel and an oxidizer to produce thrust. While scramjets are conceptually simple, actual implementation is limited by extreme technical challenges. Hypersonic flight within the atmosphere generates immense drag, and temperatures found on the aircraft and within the engine can be much greater than that of the surrounding air. Maintaining combustion in the supersonic flow presents additional challenges, as the fuel must be injected, mixed, ignited, and burned within milliseconds. Fuel mixing, along with the configuration and positioning of the injectors and the boundary conditions, play a key role in combustion efficiency. Scramjets: Fuel Mixing and Injection Systems discusses how fuel mixing efficiency and the advantage of injection systems can enhance the performance of the scramjets. The book begins with the introduction of the supersonic combustion chamber and explains the main parameters on the mixing rate. The configuration of scramjets is then introduced with special emphasis on the main effective parameters on the mixing of fuel inside the scramjets. In addition, basic concepts and principles on the mixing rate and fuel distribution within scramjets are presented. Main effective parameters such as range of fuel concentration for the efficient combustion, pressure of fuel jet and various arrangement of jet injections are also explained. This book is for aeronautical and mechanical engineers as well as those working in supersonic combustion who need to know the effects of compressibility on combustion, of shocks on mixing and on chemical reactions, and vorticity on the flame anchoring. - Explains the main applicable approaches for enhancement of supersonic combustion engines and the new techniques of fuel injection - Shows how the interaction of main air stream with fuel injections can develop the mixing inside the scramjets - Presents results of numerical simulations and how they can be used for the development of the combustion engines
Author: Gordon C. Oates
Publisher: AIAA
ISBN: 9781600860058
Category : Aerothermodynamics
Languages : en
Pages : 568
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Book Description
Annotation Design and R & D engineers and students will value the comprehensive, meticulous coverage in this volume. Beginning with the basic principles and concepts of aeropropulsion combustion, chapters explore specific processes, limitations, and analytical methods as they bear on component design.
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 630
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Book Description
Author: S Penner
Publisher: Elsevier
ISBN: 0323153186
Category : Technology & Engineering
Languages : en
Pages : 381
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Book Description
Progress in Astronautics and Rocketry, Volume 6: Detonation and Two-Phase Flow compiles technical papers presented at the ARS Propellants, Combustion, and Liquid Rockets Conference held in Palm Beach, Florida on April 26-28, 1961. This book provides an excellent illustration of research and development on a selected group of problems relating to detonations, two-phase nozzle flow, and combustion in liquid fuel rocket engines. This volume is divided into two parts. Part 1 covers the entire range of physical conditions under which detonation may be initiated or sustained, such as high explosives, solid propellants, liquid sprays, and gases. Experimental and theoretical studies are also discussed, including the significant progress of the basic phenomena involved in transition from deflagration to detonation, and nature of stable detonations in dilute sprays and other systems. The perennial problems associated with high frequency instabilities in liquid fuel rocket engines are considered in Part 2. This publication is valuable to students and investigators working in the field of propulsion research and development.
Author:
Publisher:
ISBN:
Category : Periodicals
Languages : en
Pages : 1768
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Book Description
Author: Richard Frank Hoglund
Publisher:
ISBN:
Category : Boundary layer. 650
Languages : en
Pages : 282
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Book Description
The boundary layer approximation is applied to the equations governing the mixing zone between two parallel semi-infinite streams. The two streams differ in composition and temperature, but they are not necessarily in chemical equilibrium. Closed form solutions are obtained for the approach to equilibrium in the mixing zone in the case of equal velocitiesof the two streams. Frozen flow and equilibrium flow appear as limiting cases of the general solution. A linearized reaction rate law is used for the no-equilibrium stituations. These solutions indicate that the major factor contributing to non-equilibrium conditions outside of the mixing zone is the presence of non-equilibrium conditions outside of the mixing zone. An approximate solution to the case of unequal free stream velocities is obtained using an equilibrium condition found to be applicable in the constant velocity case. The results of these studies are used to provide a qualitative indication of the effects of dissociation and ionization reactions on the flow field immediately behind a hypersonic body. It is found that the presence of reactions in various regions of this flow field causes individual and discernible changes in the wake expansion angle and in the base pressure.
