Propellant Spray Combustion Processes During Stable And Unstable Liquid Rocket Combustion
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Author | : |
Publisher | : |
Total Pages | : 371 |
Release | : 1970 |
Genre | : |
ISBN | : |
The purpose of this program is the acquisition of detailed analytical and experimental information concerning the mechanisms of energy addition from propellant spray combustion to steady flow fields and propagating pressure disturbances. Data are to be obtained and used to evaluate present or formulate new expressions describing the dynamics that contribute to the coupling processes between the spray and gas flow fields. These expressions appear in steady-state and transient propellant combustion models and bear directly on the prediction of performance and onset of high frequency combustion instability in liquid propellant rocket engines. To overcome past difficulties in comparing analytical and experimental results, an experimental apparatus which produces a monodisperse propellant spray uniformly distributed throughout the combustor has been built. The motor, to be operated as a rocket engine combustor under either stable or transient conditions, provides for optical observation and is extensively instrumented to record pressure wave amplification or decay as a function of parameter variation. Test data (drop diameters, velocity and pressure wave growth or decay as functions of chamber length and initial conditions) can be input to the newly-developed combustion models and the validity of the coupling term expressions evaluated by directly comparing the resulting predictions to experimental data. These newly-developed combustion models are described in detail.
Author | : David T. Harrje |
Publisher | : |
Total Pages | : 674 |
Release | : 1972 |
Genre | : Liquid propellant rockets |
ISBN | : |
The solution of problems of combustion instability for more effective communication between the various workers in this field is considered. The extent of combustion instability problems in liquid propellant rocket engines and recommendations for their solution are discussed. The most significant developments, both theoretical and experimental, are presented, with emphasis on fundamental principles and relationships between alternative approaches.
Author | : Vigor Young |
Publisher | : AIAA |
Total Pages | : 606 |
Release | : 1995 |
Genre | : Liquid propellant rockets |
ISBN | : 9781600864186 |
Annotation Since the invention of the V-2 rocket during World War II, combustion instabilities have been recognized as one of the most difficult problems in the development of liquid propellant rocket engines. This book is the first published in the United States on the subject since NASA's Liquid Rocket Combustion Instability (NASA SP-194) in 1972. In this book, experts cover four major subject areas: engine phenomenology and case studies, fundamental mechanisms of combustion instability, combustion instability analysis, and engine and component testing. Especially noteworthy is the inclusion of technical information from Russia and China--a first.
Author | : |
Publisher | : |
Total Pages | : 668 |
Release | : 1972 |
Genre | : Space vehicles |
ISBN | : |
Author | : David T. Harrje |
Publisher | : |
Total Pages | : 668 |
Release | : 1972 |
Genre | : Liquid propellant rockets |
ISBN | : |
The solution of problems of combustion instability for more effective communication between the various workers in this field is considered. The extent of combustion instability problems in liquid propellant rocket engines and recommendations for their solution are discussed. The most significant developments, both theoretical and experimental, are presented, with emphasis on fundamental principles and relationships between alternative approaches.
Author | : S. LAMBIRIS |
Publisher | : |
Total Pages | : 1 |
Release | : 1962 |
Genre | : |
ISBN | : |
Information is presented on the combustion processes necessary for successful analytical modeling of liquid-propellant rocket engine combustion during stable operation. Theoretical and experimental results of single-propellant droplet combustion and their application in spray-combustion analyses are reviewed. Propellant-spray formation and droplet-size distributions from particular rocket injector types are considered. Several assumptions concerning the propellant combustion processes are examined and the experimental evidence necessary for confirming the model predictions is discussed. Recent experimental data, found sufficient for approximate model verification, are shown to be useful for guiding the development of an analytical bipropellant combustion model without the necessity of making simplifying and restrictive assumptions. A description of a new combustion model is given, which is based on detailed spatial accounting of the combustion field for each particular injector-chamber configuration and propellant combination. (Author).
Author | : R. D. Sutton |
Publisher | : |
Total Pages | : 60 |
Release | : 1973 |
Genre | : |
ISBN | : |
The purpose of this program was to define, through analysis and experiment, the mechanisms of energy addition from propellant-spray combustion to steady-flow fields and propagating pressure disturbances. Such information is important because it forms the basis of steady-state and transient propellant combustion models to accurately predict performance and combustion instability characteristics in liquid-propellant rocket and air-breathing engines and, thus, minimize the probability of encountering problems with these factors during engine development. A specialized model rocket engine was constructed to permit detailed observation of the spray-combustion processes occurring under well-defined conditions. The apparatus was designed to produce a monodisperse propellant spray uniformly distributed throughout the combustor. The motor could be operated under either stable or transient conditions and contained quartz windows on two sides to permit optical observation of the vaporizing droplets. (Author).
Author | : Leon M. Wenzel |
Publisher | : |
Total Pages | : 20 |
Release | : 1965 |
Genre | : Liquid oxygen |
ISBN | : |
Author | : David Altman |
Publisher | : Princeton University Press |
Total Pages | : 197 |
Release | : 2015-12-08 |
Genre | : Science |
ISBN | : 1400879957 |
David Altman, James M. Carter, S. S. Penner, Martin Summerfield. High Temperature Equilibrium, Expansion Processes, Combustion of Liquid Propellants, The Liquid Propellants Rocket Engine. Originally published in 1960. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.
Author | : |
Publisher | : |
Total Pages | : 0 |
Release | : 2004 |
Genre | : |
ISBN | : |
This research was directed towards developing new knowledge of combustion processes in liquid-propellant rocket engines. Attention was given to the combustion of different fuels, beginning with hydrogen-oxygen but ultimately including multicomponent hydrocarbon mixtures representative of RP fuels, and to nonlinear processes of importance in combustion instability. Effects of detailed chemical kinetics on performance and stability were addressed by introducing systematically reduced chemistry that enables theoretical analysis to be completed thoroughly and accurately. The interactions between chemistry and turbulence were addressed, including the effects of the heat release on the turbulence. The orientation of the work was fundamental and aimed at predicting not only performance and acoustic response but also intrinsic instability. The results were intended to help to improve understanding of combustion mechanisms and combustion instabilities in liquid-propellant rocket motors. The most recent specific results concern induction times in hydrogen-oxygen mixtures and heal-release effects on turbulent missing.