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Languages : en
Pages : 58
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Book Description
This report summarizes work on a research program to quantify the effect of distributed combustion of metal particles in a Rijke burner. Under a previous contract experimental data were obtained with the Rijke burner, and a mathematical model of the burner was developed. To improve the model, the McIntosh flame model, based on large activation energy asymptotics, has been coupled to the acoustic model. Results have been compared to experimental data showing that the McIntosh transfer function is an improvement over previous models. Law's model of aluminum combustion has been modified to include the effects of multiple oxidizers and their products, oxide accumulation on the surface of the burning aluminum particle, and convection. There are no adjustable parameters in the improved aluminum combustion model, and both transport and thermodynamic properties are calculated internally. Results indicate that the modified model compares more favorably to experimental data than a simple liquid droplet model. The aluminum combustion model has also been coupled to the Rijke acoustic model. Calculations show a sensitivity to the size of the region of influence surrounding a particle and to the time lag between the particle response and the acoustic pressure. The results show reasonable agreement with available data for aluminum particles burning in the Rijke burner ... Unstable combustion, Distributed combustion, Acoustic instability.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
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Book Description
This report summarizes work on a research program to quantify the effect of distributed combustion of metal particles in a Rijke burner. Under a previous contract experimental data were obtained with the Rijke burner, and a mathematical model of the burner was developed. To improve the model, the McIntosh flame model, based on large activation energy asymptotics, has been coupled to the acoustic model. Results have been compared to experimental data showing that the McIntosh transfer function is an improvement over previous models. Law's model of aluminum combustion has been modified to include the effects of multiple oxidizers and their products, oxide accumulation on the surface of the burning aluminum particle, and convection. There are no adjustable parameters in the improved aluminum combustion model, and both transport and thermodynamic properties are calculated internally. Results indicate that the modified model compares more favorably to experimental data than a simple liquid droplet model. The aluminum combustion model has also been coupled to the Rijke acoustic model. Calculations show a sensitivity to the size of the region of influence surrounding a particle and to the time lag between the particle response and the acoustic pressure. The results show reasonable agreement with available data for aluminum particles burning in the Rijke burner ... Unstable combustion, Distributed combustion, Acoustic instability.
Author: P. C. Braithwaitet
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
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Book Description
The problem of combustion instability in solid rocket propellants has been studied extensively over the past three decades. The most common way oscillatory combustion is controlled in rocket motors today is through the use of additives known as acoustic suppressants. The perfect suppressant would control all of the oscillatory modes which are present in a solid propellant rocket motor. Unfortunately suppressants that work well at one frequency, such as the product in a longitudinal mode, can be quite ineffective at other frequencies, such as tangential mode. Still, some suppressants have been relatively successful in suppressing oscillations in operational motors, the more successful suppressants include Al, ZrC and graphite.
Author: Martin Summerfield
Publisher: AIAA
ISBN: 9781600863967
Category : Solid propellants
Languages : en
Pages : 922
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Book Description
Author: Kenneth K. Kuo
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 922
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Book Description
Author: Vasily B. Novozhilov
Publisher: John Wiley & Sons
ISBN: 1119525640
Category : Technology & Engineering
Languages : en
Pages : 352
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Book Description
Despite significant developments and widespread theoretical and practical interest in the area of Solid-Propellant Nonsteady Combustion for the last fifty years, a comprehensive and authoritative text on the subject has not been available. Theory of Solid-Propellant Nonsteady Combustion fills this gap by summarizing theoretical approaches to the problem within the framework of the Zeldovich-Novozhilov (ZN-) theory. This book contains equations governing unsteady combustion and applies them systematically to a wide range of problems of practical interest. Theory conclusions are validated, as much as possible, against available experimental data. Theory of Solid-Propellant Nonsteady Combustion provides an accurate up-to-date account and perspectives on the subject and is also accompanied by a website hosting solutions to problems in the book.
Author: Haridwar Singh
Publisher: Royal Society of Chemistry
ISBN: 1782620966
Category : Science
Languages : en
Pages : 240
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Book Description
Propellants contain considerable chemical energy that can be used in rocket propulsion. Bringing together information on both the theoretical and practical aspects of solid rocket propellants for the first time, this book will find a unique place on the readers' shelf providing the overall picture of solid rocket propulsion technology. Aimed at students, engineers and researchers in the area, the authors have applied their wealth of knowledge regarding formulation, processing and evaluation to provide an up to date and clear text on the subject.
Author:
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ISBN:
Category :
Languages : en
Pages : 17
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Book Description
This final scientific report reviews the progress from May 1979 to December 1982 on a program to study various aspects of solid propellant combustion phenomena. The original program included three specific areas of study: Diffusion flame analysis; Kinetic mechanisms of double base propellants; Interaction effects of distributed particle combustion in acoustic environments. The diffusion flame is the controlling mechanism in the combustion of composite propellants. Therefore, a thorough understanding of diffusion flames is prerequisite to understanding solid propellant combustion, and was the objective of one task of the program. The second task of the program was motivated by the desire to better understand transient combustion such as occurs in DDT and combustion instability. Double base propellant combustion is dominated by the flame kinetics which appear to be more easily studied than those of composite propellants. The final task of the program was aimed at understanding the effect of stability additives on combustion instability. During the final year of the contract, work on the first two tasks was discontinued and all work was concentrated on the third task. Interim reports covering the initial work have been published in December 1980 and February 1982. This report summarizes the work performed during the final phase of the contract covering the time from October 1981 through December 1982. Keywords: Solid rocket propellants.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 77
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Book Description
The model of uniformly distributed combustion in the gas phase is used as the basis for examining several features of unsteady burning. As a zeroth approximation the flame zone begins at the solid-gas interface and responds linearly and quasi-statistically to changes of pressure only. Three deviations from this behavior are then examined: the combustion zone is displaced from the surface, the energy release responds to fluctuations of temperature and the response is not quasi-static. It appears that the assumption that the burning begins immediately at the surface can lead to significant changes, more important than the assumption that the energy release responds to changes of pressure only, especially in the interpretation of experimental data. The problem of nonquasi-static behavior, i.e., processes in the gas phase do not follow precisely impressed changes of pressure, is formulated as an expansion in frequency. Approximate results seem to be consistent with existing information.
Author: Martin Summerfield
Publisher: Elsevier
ISBN: 0323163351
Category : Science
Languages : en
Pages : 713
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Book Description
Solid Propellant Rocket Research
Author: Vigor Yang
Publisher: AIAA
ISBN: 9781600864377
Category : Ballistics, Interior
Languages : en
Pages : 1038
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Book Description
