3 edition of Structure of a swirl-stabilized combusting spray found in the catalog.
Structure of a swirl-stabilized combusting spray
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va
Written in English
|Other titles||Structure of a swirl stabilized combusting spray.|
|Statement||Daniel L. Bulzan.|
|Series||NASA technical memorandum -- 106724.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
A comparison of chemical propulsion, nuclear thermal propulsion, andmultimegawatt electric propulsion for Mars missions ROBERT FRISBEE, JOHN BLANDINO and. Detailed Analysis of the Velocity Fields from 60 kW Swirl-Stabilized Coal Flames in CO2/O2- and N2/O2-Atmospheres by Means of Laser Doppler Velocimetry and Particle Image Velocimetry. In: Combustion Science and Technology, (10), S. , ISSN
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Diesel Spray Structure by Laser Tomography and Diffraction”, Combustion Institute / Canadian Section, Spring Technical Meeting, Paper No. 38, p, May , , Ottawa, Ontario. O Gülder, Ö. L., “A Turbulent Premixed Flame Propagation Model for the Wrinkled FlameFile Size: KB. Issuu is a digital publishing platform that makes it simple to publish magazines, catalogs, newspapers, books, and more online. Easily share your publications and get them in front of Issuu’s.
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Get this from a library. Structure of a swirl-stabilized combusting spray. [Daniel L Bulzan; United States. National Aeronautics and Space Administration.]. VELOCITY AND DROP SIZE MEASUREMENTS IN A CONFINED, SWIRL-STABILIZED, COMBUSTING SPRAY Daniel L. Bulzan National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio Abs_act Drop size and velocity measurements in a confined, swirl-stabilized, reacting spray are presented.
The configur. To investigate the structure of a hollow-cone spray flame similar to those occurring in the primary zone of gas-turbine combustors or within furnaces, a swirl-stabilized combustor was used. The spray structure is, however, drastically changed inside the flame reaction zone, as shown by changes in both the magnitude and shape of the radial distributions of drop number density, liquid.
Important observation is that the turbulent spray flame structure is significantly different, both quantitatively and qualitatively, from that of the corresponding gaseous diffusion flame. In addition, the spray flame exhibits a strong sensitively to the transient liquid-phase : S.
Aggarwal, S. Chitre. Recent developments in industrial dry-low-emission (DLE) swirl-stabilized combustors are first summarized. Various swirl injector configurations and related flow characteristics, including vortex breakdown, precessing vortex core, large-scale coherent structures, and liquid fuel atomization and spray formation, are by: A hollow-cone spray with a nominal cone angle of 30 degrees from a pressure-swirl fuel atomizer was used in a swirl-stabilized combustor.
The combustor is circular in cross section, with a swirl plate and fuel nozzle axis coinciding with the axes of the chamber. kerosene is injected upward inside the chamber from the fuel : B. Chehroudi, M. Ghaffarpour. CONFERENCE PROCEEDINGS Papers Presentations Journals. Advanced Photonics Journal of Applied Remote Sensing.
Abstract. Confined short turbulent swirling premixed and non-premixed methane and heptane spray flames stabilized on an axisymmetric bluff body in a square enclosure have been examined close to the blow-off limit and during the extinction transient with OH* chemiluminescence and OH-PLIF operated at 5 by: To isolate the impact of high combustion temperature on spray evaporation, two cases were investigated and compared.
In the first case the spray evaporation is studied in a non-combusting environment. In the second it is investigated how the premixed combustion conditions affect Cited by: 1. A combustor is a component or area of a gas turbine, ramjet, or scramjet engine where combustion takes place.
It is also known as a burner, combustion chamber or flame a gas turbine engine, the combustor or combustion chamber is fed high pressure air by the compression system. The combustor then heats this air at constant pressure.
After heating, air passes from the combustor through. Experimental and numerical investigations of single droplet burning modes in a lean, partially prevaporized swirl-stabilized spray flame are reported.
In the experiment single droplet flames have been visualized by CH-PLIF and simultaneous recording of the Mie signal. This book offers gas turbine users and manufacturers a valuable resource to help them sort through issues associated with combustion instabilities.
International Journal of Spray and Combustion Dynamics, Vol. 7, No. 3 Passive Control of Noise and Instability in a Swirl-Stabilized Combustor With the Use of High-Strength Porous Insert. The spray structure of an AlliedSignal high-pressure swirl injector which utilizes a fuel injection pressure of MPa was characterized by Evers.
This injector design is shown schematically in Fig. Four regions denoted as leading-edge, cone, trailing-edge, and vortex-cloud, were identified for the hollow-cone spray that is by: "A study of the effects of chemical mechanisms on the computed structure of a radiation sensitive opposed flow partially premixed flame," Combustion and Flame, () 25 X.
Zhu, J. Gore, A. Karpetis, and R. Barlow, The effects of self-absorption of radiation on an. In many continuous combustion processes, such as those found in aeroengines or gas turbines, the flame is stabilized by a swirling flow formed by aerodynamic swirlers.
The dynamics of such swirling flames is of technical and fundamental interest. This article reviews progress in this field and begins with a discussion of the swirl number, a parameter that plays a central role in the definition Cited by: This book focuses on recent advances in the design of very highly efficient, low-pollution-emitting propulsion systems, as well as advances in testing, diagnostics and analysis.
It offers unique coverage of Pulse Detonation Engines, which add tremendous power to jet thrust by combining high pressure with ignition of the air/fuel mixture. Daniel L. Bulzan. Structure of a swirl-stabilized combusting spray. Journal of Propulsion and Power[Citation] [PDF] [PDF Plus] CHENG-TUNG CHOU, RU-GUN LIU, JEN-KUN TSAI, ANTHONY S.
CHIANG. CONFINED COAXIAL JET FLOWS INTO A COLD MODEL OF CVD CHAMBER. Chemical Engineering Communications Swirl stabilized premixed flame analysis using of LES and POD Iudiciani, Piero LU Mark; Abstract For environmental and human health reasons, the regulations on the emissions from combustion devices are getting more and more strict.
In particular, it is important to abate the emission of pollutants deriving from combustion in gas : The compatibility of spray characteristics of alternative fuel blends, in relation to currently used Jet A-1 fuel, has been assessed experimentally. Tested blends were selected based on a narrow cut of paraffins, mixed with appropriately selected aromatics and naphthenes.
Relevant physical properties including the density, viscosity, and surface tension were estimated : Andreas P. Vouros, Alexandros P.
Vouros, Thrassos Panidis. DESCRIPTION: The structure of the density field in a turbulent air flow directly affects the optical properties of the associated air volume, an effect which can degrade the ability to acquire imagery or propagate a laser through that volume.The successful development of the coal-based integrated gasification combined cycle (IGCC) with carbon capture and storage (CCS) requires gas turbines capable of achieving dry low nitrogen oxide (NOx) combustion of hydrogen-rich syngas fuels for low emissions and high plant efficiency.
This chapter describes the development of a “multi-cluster combustor” as a state-of-the-art dry low NOx Author: Tomohiro Asai, Yasuhiro Akiyama, Satoschi Dodo.Combustor Explained.
A combustor is a component or area of a gas turbine, ramjet, or scramjet engine where combustion takes place. It is also known as a burner, combustion chamber or flame a gas turbine engine, the combustor or combustion chamber is fed high pressure air by the compression system.
The combustor then heats this air at constant pressure.