Numerical Simulation of Gas-particle Two-phase Turbulent Flows on the Combustion Chamber of Spinning Solid Rocket Motor PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Numerical Simulation of Gas-particle Two-phase Turbulent Flows on the Combustion Chamber of Spinning Solid Rocket Motor PDF full book. Access full book title Numerical Simulation of Gas-particle Two-phase Turbulent Flows on the Combustion Chamber of Spinning Solid Rocket Motor by Gao Bo. Download full books in PDF and EPUB format.
Author: Gao Bo
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Gao Bo
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Zhen-Guo Wang
Publisher: John Wiley & Sons
ISBN: 1118890051
Category : Technology & Engineering
Languages : en
Pages : 509
Get Book Here
Book Description
This book concentrates on modeling and numerical simulations of combustion in liquid rocket engines, covering liquid propellant atomization, evaporation of liquid droplets, turbulent flows, turbulent combustion, heat transfer, and combustion instability. It presents some state of the art models and numerical methodologies in this area. The book can be categorized into two parts. Part 1 describes the modeling for each subtopic of the combustion process in the liquid rocket engines. Part 2 presents detailed numerical methodology and several representative applications in simulations of rocket engine combustion.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1032
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 994
Get Book Here
Book Description
Author: Kan Xie
Publisher: Springer
ISBN: 9811364397
Category : Technology & Engineering
Languages : en
Pages : 237
Get Book Here
Book Description
This book focuses on the performance and application of fluidic nozzle throats for solid rocket motors, discussing their flow details and characterization performance, as well as the influence of the particle phase on their performance. It comprehensively covers a range of fluidic nozzle throats in solid rocket motors and is richly illustrated with impressive figures and full-color photographs. It is a valuable resource for students and researchers in the fields of aeronautics, astronautics and related industries wishing to understand the fundamentals and theories of fluidic nozzle throats and engage in fluidic nozzle throat analysis and design.
Author: Bart Merci
Publisher: Springer Science & Business Media
ISBN: 3319046780
Category : Technology & Engineering
Languages : en
Pages : 167
Get Book Here
Book Description
This book reflects the results of the 2nd and 3rd International Workshops on Turbulent Spray Combustion. The focus is on progress in experiments and numerical simulations for two-phase flows, with emphasis on spray combustion. Knowledge of the dominant phenomena and their interactions allows development of predictive models and their use in combustor and gas turbine design. Experts and young researchers present the state-of-the-art results, report on the latest developments and exchange ideas in the areas of experiments, modelling and simulation of reactive multiphase flows. The first chapter reflects on flame structure, auto-ignition and atomization with reference to well-characterized burners, to be implemented by modellers with relative ease. The second chapter presents an overview of first simulation results on target test cases, developed at the occasion of the 1st International Workshop on Turbulent Spray Combustion. In the third chapter, evaporation rate modelling aspects are covered, while the fourth chapter deals with evaporation effects in the context of flamelet models. In chapter five, LES simulation results are discussed for variable fuel and mass loading. The final chapter discusses PDF modelling of turbulent spray combustion. In short, the contributions in this book are highly valuable for the research community in this field, providing in-depth insight into some of the many aspects of dilute turbulent spray combustion.
Author: Masaya Yamamoto
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 15
Get Book Here
Book Description
Author: Murat Yaldizli
Publisher:
ISBN:
Category : Combustion engineering
Languages : en
Pages : 442
Get Book Here
Book Description
Author: Mathias Ross
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Get Book Here
Book Description
With efficiencies in conventional rocket designs reaching the limit of theoretical possibility,there has been renewed interest in technologies which may be able to shift the boundaries of efficiency. One such technology is the rotating detonation rocket engine, which has the potential to create highly efficient engines in a small form factor. However, the detonation dynamics and complex flowfields inside the combustion chamber are greatly dependent on geometry; in particular, the downstream nozzle design affects dynamics inside the combustion chamber. In this work, high fidelity large eddy simulations of gaseous methane-oxygen rotating detonation rocket engines are presented for five engine configurations. The first simulation discussed is a validation case from the AIAA model validation in propulsion workshop. A laser model based on the Beer-Lambert law was developed for com- paring simulations with experimental laser absorbance measurements, and used to directly relate the simulation with experimental measurements of temperature, pressure, and CO column density in the exhaust of the engine. The analysis found that the simulation over- predicted pressure and thrust in the engine, as has been the case in other simulations of the engine, but that features in the exhaust flowfield closely matched experimental measurements. Close agreement between simulation and experiment was also seen in the measured CO mole fraction of the exhaust. The effect of adding a converging-diverging nozzle to a rotating detonation rocket engine was explored in the other four simulations, which consider an engine of two different lengths, with and without a constriction. The geometries matched experimental tests previously conducted at the Air Force Research Laboratory, and the operational modes attained in the simulations were found in all cases to directly relate to experimental observations. In the unconstricted geometries, flow in the chamber exceeded Mach 1 in pockets up- stream of the chamber exit. However, geometries with a diverging-converging nozzle directly followed the Mach-area relationship, with supersonic flow existing only in the diverging regions of the nozzle. This suggests a fundamental difference between the flowfield present in RDRE geometries with and without an area constriction, even though the constriction studied was gradual enough that no reflected shocks were observed traveling upstream. The formation enthalpy of the flow was measured inside the chamber for all configurations, and demonstrated that the difference in pressures and detonation structures associated with the chamber area constriction did not result in a significant change in the amount of energy released through combustion. Adding a constriction increased the average pressure of the combustion chamber, which would typically result in increased combustive energy release, but no associated release through combustion was observed. As such, although the use of a converging-diverging nozzle increased overall performance, the induced change in operating mode was detrimental to the extraction of energy from the flow. Changing chamber length was found to have little impact on the operation of an unconstricted rotating detonation rocket engine. However, changing the length of a chamber with a constriction resulted in a change in operating mode, and decrease in the strength of the counter-propagating waves. This suggests that, although unconstricted chamber geometries are likely optimized at short lengths, the length of the chamber is an important parameter to be considered when the engine utilizes a chamber area constriction.
Author: DP Mishra
Publisher: CRC Press
ISBN: 1351708414
Category : Technology & Engineering
Languages : en
Pages : 364
Get Book Here
Book Description
The book follows a unified approach to present the basic principles of rocket propulsion in concise and lucid form. This textbook comprises of ten chapters ranging from brief introduction and elements of rocket propulsion, aerothermodynamics to solid, liquid and hybrid propellant rocket engines with chapter on electrical propulsion. Worked out examples are also provided at the end of chapter for understanding uncertainty analysis. This book is designed and developed as an introductory text on the fundamental aspects of rocket propulsion for both undergraduate and graduate students. It is also aimed towards practicing engineers in the field of space engineering. This comprehensive guide also provides adequate problems for audience to understand intricate aspects of rocket propulsion enabling them to design and develop rocket engines for peaceful purposes.
