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Author : Daniel Rahn
Publisher :
ISBN 13 : 9783843950190
Total Pages : pages
Book Rating : 4.9/5 (51 download)
Download or read book Modeling of Combustion, Flow and Heat Transfer in Methane-Oxygen Liquid Rocket Engines written by Daniel Rahn and published by . This book was released on 2022 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Zhen-Guo Wang
Publisher : John Wiley & Sons
ISBN 13 : 1118890027
Total Pages : 392 pages
Book Rating : 4.1/5 (188 download)
Download or read book Internal Combustion Processes of Liquid Rocket Engines written by Zhen-Guo Wang and published by John Wiley & Sons. This book was released on 2016-08-29 with total page 392 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 : Rene Nardi Rezende
Publisher : SAE International
ISBN 13 : 0768093325
Total Pages : 158 pages
Book Rating : 4.7/5 (68 download)
Download or read book Liquid Rocket Engine written by Rene Nardi Rezende and published by SAE International. This book was released on 2018-11-15 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt: The great engineering achievement required to overcome most of the challenges and obstacles that prevented turning rocket design from art into science took place in Europe and the United States between the 1930s and the 1950s. With the vast majority of the engines currently in operation developed in the “pre-computer” age, there are new opportunities to update the design methodologies using technology that can now handle highly complex calculations fast. The space sector with an intense focus on efficiency is driving the need for updating, adapting or replacing the old modeling practices with new tools capable of reducing the volume of resources and the time required to complete simulations and analysis. This book presents an innovative parametric model applicable to the project of some elements of the liquid rocket thrust chamber with the level of detail and accuracy appropriate to the preliminary design phase. It addresses the operating characteristics and dimensioning of some thrust chamber elements through a set of equations and parameters, which include thrust or propellant characteristics. The model degree of sophistication was adjusted to the requirements of the Project Life Cycle Phase B, while also enabling quick analysis of new configurations from changes in initial project parameters.
Author : Matthieu M. Masquelet
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (798 download)
Download or read book Simulations of a Sub-scale Liquid Rocket Engine written by Matthieu M. Masquelet and published by . This book was released on 2006 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The prediction of transient phenomena inside Liquid Rocket Engines (LREs) has not been feasible until now because of the many challenges posed by the operating conditions inside the combustion chamber. Especially, the departure from ideal gas because of the cryogenic injection in a high-pressure chamber is one of the ma jor hurdle for such simula- tions. In order to begin addressing these issue, a real-gas model has been implemented in a massively parallel flow solver. This solver is capable of performing Large-Eddy Simula- tions (LES) in geometrical configurations ranging from an axisymmetric slice to a 3D slice up to a full 3D combustor. We present here the results from an investigation of unsteady combustion inside a small-scale, multi-injectors LRE. Both thermally perfect gas (TPG) and real gas (RG) approaches are evaluated for this LOX-GH2 system. The Peng-Robinson cubic equation of state (PR EoS) is used to account for real gas effects associated with the injection of cryogenic oxygen. Realistic transport properties are computed but simplified chemistry is used in order to achieve a reasonable turnaround time. Results show the impor- tance of the unsteady dynamics of the flow, especially the interaction between the different injectors. The role of the equation of state is assessed and the real gas model, despite a limited zone of application, seems to have a strong influence on the overall chamber behav- ior. Although several features in the simulated results agree well with past experimental observations, the prediction of heat flux using a simplified flux boundary condition is not completely satisfactory. This work also reviews in details the state of our knowledge on supercritical combustion in a coaxial injector configuration, stressing issues where numeri- cal modeling could provide new insights. However, many developments and improvements are required before an LES modeling of such a flow is both feasible and valid. We finally propose a comprehensive roadmap towards the completion of this goal and the possible use of CFD as a design tool for a modern liquid rocket engine.
Author : H. Ziebland
Publisher :
ISBN 13 :
Total Pages : 172 pages
Book Rating : 4.:/5 (318 download)
Download or read book Heat Transfer in Rocket Engines written by H. Ziebland and published by . This book was released on 1971 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the first part of this book the various basic heat transfer processes are considered, -- simple convective heat transfer from hot gases to the engine walls under various conditions, radiation heat transfer, and coolant heat transfer processes. This part is followed by one describing the various methods of cooling used in liquid propellant rocket engines, such as regenerative, film, ablation and radiation cooling. The final part concerns the properties of materials that will have to be known by the engine designer, from the transport properties of the hot combustion gases to those of the materials from which the engine will be constructed. Emphasis was placed on presenting simple methods for calculating the magnitude of heat transfer rather than providing the most modern and rigorous theories, particularly in the field of developing boundary layers. (Author).
Author : Daniel I. Drain
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (31 download)
Download or read book Relations of Combustion Dead Time to Engine Variables for a 20,000-pound-thrust Gaseous-hydrogen written by Daniel I. Drain and published by . This book was released on 1961 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments were conducted on an uncooled 20,000lb-thrust gaseous-H and LOX rocket engine over a range of chamber pressure from 45 to 300 psia and oxidant-fuel ratio from 2 to 7. Combustion dead times were measured and compared with dead times calculated from frequency data for two assumed combustion models. Measured combustion dead time decreased with increasing chamber pressure at constant oxidant-fuel ratio or LOX injection velocity. This dead time also decreased with oxidant-fuel ratio at constant chamber pressure or O injection velocity. For the engine model where combustion dead time was considered to be the inverse of twice the measured chamberpressure frequency, only a fair agreement with the measured dead time was obtained. When the measured chamber-pressure frequencies were corrected for gas-dynamics effects in terms of the gas residence time, close agreement with the measured dead times was obtained. (Author).
Author : Richard F. Neu
Publisher :
ISBN 13 :
Total Pages : 48 pages
Book Rating : 4.:/5 (317 download)
Download or read book Comparison of Localized Heat-transfer Rates in a Liquid-oxygen - Heptane Rocket Engine Employing Several Injection Methods and Oxidant-fuel Ratios written by Richard F. Neu and published by . This book was released on 1960 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Jens Metzger
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781977919007
Total Pages : 388 pages
Book Rating : 4.9/5 (19 download)
Download or read book Internal Combustion Processes of Liquid Rocket Engines written by Jens Metzger and published by Createspace Independent Publishing Platform. This book was released on 2017-07-31 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Author : Curt H. Liebert
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (31 download)
Download or read book Determination of Local Experimental Heat-transfer Coefficients on Combustion Side of an Ammonia-oxygen Rocket written by Curt H. Liebert and published by . This book was released on 1961 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Dieter K. Huzel
Publisher : AIAA
ISBN 13 : 9781600864001
Total Pages : 452 pages
Book Rating : 4.8/5 (64 download)
Download or read book Modern Engineering for Design of Liquid-Propellant Rocket Engines written by Dieter K. Huzel and published by AIAA. This book was released on 1992 with total page 452 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 16 pages
Book Rating : 4.:/5 (317 download)
Download or read book Performance and Heat Transfer Characteristics of a Carbon Monoxide/oxygen Rocket Engine written by and published by . This book was released on 1993 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Vigor Yang
Publisher : AIAA (American Institute of Aeronautics & Astronautics)
ISBN 13 :
Total Pages : 776 pages
Book Rating : 4.3/5 (91 download)
Download or read book Liquid Rocket Thrust Chambers written by Vigor Yang and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 2004 with total page 776 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is the first major publication on liquid-rocket combustion devices since 1960, and includes 20 chapters prepared by world-renowned experts. Each chapter focuses on a specific aspect of liquid-propellant combustion and thrust chamber dynamics, and is incorporated into the volume in a well-organized, cohesive manner. There are contributions from nine different countriesChina, France, Germany, Italy, Japan, the Netherlands, Russia, Sweden, and the United States.
Author : Jonathan VanNoord
Publisher : BiblioGov
ISBN 13 : 9781289172268
Total Pages : 22 pages
Book Rating : 4.1/5 (722 download)
Download or read book A Heat Transfer Investigation of Liquid and Two-Phase Methane written by Jonathan VanNoord and published by BiblioGov. This book was released on 2013-07 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: A heat transfer investigation was conducted for liquid and two-phase methane. The tests were conducted at the NASA Glenn Research Center Heated Tube Facility (HTF) using resistively heated tube sections to simulate conditions encountered in regeneratively cooled rocket engines. This testing is part of NASA s Propulsion and Cryogenics Advanced Development (PCAD) project. Nontoxic propellants, such as liquid oxygen/liquid methane (LO2/LCH4), offer potential benefits in both performance and safety over equivalently sized hypergolic propulsion systems in spacecraft applications. Regeneratively cooled thrust chambers are one solution for high performance, robust LO2/LCH4 engines, but cooling data on methane is limited. Several test runs were conducted using three different diameter Inconel 600 tubes, with nominal inner diameters of 0.0225-, 0.054-, and 0.075-in. The mass flow rate was varied from 0.005 to 0.07 lbm/sec. As the current focus of the PCAD project is on pressure fed engines for LO2/LCH4, the average test section outlet pressures were targeted to be 200 psia or 500 psia. The heat flux was incrementally increased for each test condition while the test section wall temperatures were monitored. A maximum average heat flux of 6.2 Btu/in.2 sec was achieved and, at times, the temperatures of the test sections reached in excess of 1800 R. The primary objective of the tests was to produce heat transfer correlations for methane in the liquid and two-phase regime. For two-phase flow testing, the critical heat flux values were determined where the fluid transitions from nucleate boiling to film boiling. A secondary goal of the testing was to measure system pressure drops in the two-phase regime.
Author : Norbert Peters
Publisher : Cambridge University Press
ISBN 13 : 1139428063
Total Pages : 322 pages
Book Rating : 4.1/5 (394 download)
Download or read book Turbulent Combustion written by Norbert Peters and published by Cambridge University Press. This book was released on 2000-08-15 with total page 322 pages. Available in PDF, EPUB and Kindle. Book excerpt: The combustion of fossil fuels remains a key technology for the foreseeable future. It is therefore important that we understand the mechanisms of combustion and, in particular, the role of turbulence within this process. Combustion always takes place within a turbulent flow field for two reasons: turbulence increases the mixing process and enhances combustion, but at the same time combustion releases heat which generates flow instability through buoyancy, thus enhancing the transition to turbulence. The four chapters of this book present a thorough introduction to the field of turbulent combustion. After an overview of modeling approaches, the three remaining chapters consider the three distinct cases of premixed, non-premixed, and partially premixed combustion, respectively. This book will be of value to researchers and students of engineering and applied mathematics by demonstrating the current theories of turbulent combustion within a unified presentation of the field.
Author : Richard J. Quentmeyer
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (317 download)
Download or read book Hot-gas-side Heat Transfer Characteristics of Subscale, Plug-nozzle Rocket Calorimeter Chamber written by Richard J. Quentmeyer and published by . This book was released on 1993 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781723149092
Total Pages : 118 pages
Book Rating : 4.1/5 (49 download)
Download or read book Hydrocarbon-Fuel/Combustion-Chamber-Liner Materials Compatibility written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-18 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of dynamic tests using methane and NASA-Z copper test specimen under conditions that simulate those expected in the cooling channels of a regeneratively cooled LOX/hydrocarbon booster engine operating at chamber pressures up to 3000 psi are presented. Methane with less than 0.5 ppm sulfur contamination has little or no effect on cooling channel performance. At higher sulfur concentrations, severe corrosion of the NASA-Z copper alloy occurs and the cuprous sulfide Cu2S, thus formed impedes mass flow rate and heat transfer efficiency. Therefore, it is recommended that the methane specification for this end use set the allowable sulfur content at 0.5 ppm (max). Bulk high purity liquid methane that meets this low sulfur requirement is currently available from only one producer. Pricing, availability, and quality assurance are discussed in detail. Additionally, it was found that dilute sodium cyanide solutions effectively refurbish sulfur corroded cooling channels in only 2 to 5 minutes by completely dissolving all the Cu2S. Sulfur corroded/sodium cyanide refurbished channels are highly roughened and the increased surface roughness leads to significant improvements in heat transfer efficiency with an attendant loss in mass flow rate. Both the sulfur corrosion and refurbishment effects are discussed in detail. Homer, G. David Glenn Research Center COOLING; COPPER ALLOYS; COPPER SULFIDES; CORROSION; DYNAMIC TESTS; ENVIRONMENT SIMULATION; METHANE; OXYGEN-HYDROCARBON ROCKET ENGINES; SULFUR; BOOSTER ROCKET ENGINES; COMBUSTION CHAMBERS; COST ESTIMATES; CYANIDES; DISSOLVING; HEAT TRANSFER; MASS FLOW RATE; QUALITY CONTROL; SODIUM; SURFACE ROUGHNESS...
Author : DP Mishra
Publisher : CRC Press
ISBN 13 : 1351708414
Total Pages : 364 pages
Book Rating : 4.3/5 (517 download)
Download or read book Fundamentals of Rocket Propulsion written by DP Mishra and published by CRC Press. This book was released on 2017-07-20 with total page 364 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
