mixing iodine supersonic
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- mixing iodine supersonic
A variant of an ejector-mixing nozzle for a chemical oxygen–iodine laser was experimentally tested with notched starlet ejectors. Cold-flow planar laser-induced fluorescence measurements ...
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For low hypersonic conditions, combustion occurs mainly in the diffusive mode in which the gas/liquid fuels are injected into supersonic freestreams for simultaneous fuel-air mixing and chemical reaction. Flame stability is generally enhanced by improved mixing, physical flameholding, and external energy addition.
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Masamori Endo. A computational model of the cross-flow type singlet oxygen generator (SOG) for chemical oxygen-iodine laser (COIL) is developed. The reaction zone, in which basic hydrogen peroxide ...
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The injection and mixing of iodine vapor into a duct flow has been investigated experimentally and numerically. Laser-induced fluorescence has been used to visualize the progress of spreading of the iodine and its distribution homogeneity along the duct. Several injection methods, typical flow pressures for oxygen-iodine lasers, and various molar flux …
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Injecting the iodine in the subsonic region promotes mixing between the injected iodine and the primary oxygen flows, whereas diffusive mixing is difficult in the …
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Supersonic mixing is of great practical importance in engineering applications such as the scramjet engine combustor (Seiner et al. 2001) and chemical oxygen iodine laser (COIL) (Noren et al. 2011).In these applications, it is essential for the injectant to be mixed rapidly into the primary flow.
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Optimization Of A Highly Efficient Supersonic COIL With Supersonic Mixing Of Iodine And Oxygen 5c. PROGRAM ELEMENT NUMBER 5d. PROJECT NUMBER 5d. TASK NUMBER 6. AUTHOR(S) Professor Salman Rosenwaks 5e.
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The oxygen flows through the exit to an iodine–oxygen mixing system and expanded to supersonic velocity in a slit supersonic nozzle. As shown in Ref. 9, for …
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A supersonic expansion nozzle has allowed us to achieve highly efficient operation of the supersonic mixing chemical oxygen–iodine laser (COIL). The nozzle's shape produced a rapid mixing of ...
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A numerical method using AUSMDV scheme and k-ω SST turbulence model with an explicit compressibility correction was developed, and a 3-D numerical simulation of a supersonic flow field with a vertical sonic jet of hydrogen was performed. Good agreement between numerical results and experimental data validated the reliability of …
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The measurements were made for different positions of the iodine injection plane with respect to the critical cross-section (both in the subsonic part of the nozzle and in the supersonic flow). The gas pressure at the nozzle unit entry was varied from 50 to 250 Torr. The total pressure loss have been found for different mixing designs.
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Spray and mixing characteristics of liquid jet in a tubular gas–liquid atomization mixer. ... hydrodynamics and absorption of iodine vapour in a venturi scrubber operating in self-priming mode. Nuclear Engineering and Design, Vol. 341 ... Numerical simulations of spray jet in supersonic crossflows using an Eulerian approach with an …
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To enhance the mixing between the flows, trip jets are placed in the wake of the single jet. The sonic trip jets, significantly smaller than the primary supersonic iodine jet, are intended to ...
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the supersonic nozzle and the iodine injectors must be designed to provide both adequate penetration of the iodine stream into the oxygen flow and adequate mixing between the oxygen and iodine flows (Madden et al. 1999). The two mixing schemes (subsonic vs. supersonic region injection) have their respective advantages, but the former has been
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Experimental investigations of supersonic flow over a 25° compression ramp were carried out in a Mach 3.0 wind tunnel; the upstream boundary layer was laminar flow. Wall pressure was measured; fine structures of holistic flow field and local regions were visualized by nanoparticle-tracer-based planar laser scattering (NPLS) technique. The …
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A preliminary design optimization of a revolutionary concept involving integrated airbreathing propulsive assist is presented. The conceptual design for the proposed airbreathing thrust augmenter is an annular ramjet/scramjet integrated into a liquid-oxygen-rocket propellant rocket core. The airbreathing engine makes use of the …
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$40.00. The dissociation of I2 molecules at the optical axis of a supersonic chemical oxygen-iodine laser (COIL) was studied via detailed measurements and three …
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We report on an efficient supersonic chemical oxygen-iodine laser, energized by a jet-type singlet oxygen generator, operating without primary buffer gas and applying simple nozzle geometry and transonic mixing of iodine and oxygen.
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Employing chemical fluorescence method (CFM),the effects of trip tabs on the process of supersonic mixing of parallel oxygen-iodine flows in COIL was studied. The experimental results indicated ...
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The aerothermodynamic processes in the supersonic combustion chamber are complex and closely related. The comparable time scales lead to a closely coupled turbulent mixing and chemical reaction rates. Combustion cannot be initiated until mixing has been achieved at a molecular level, and, in turn, in regions where combustion has taken place ...
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Comparing the measurements and the calculations enabled critical examination of previously proposed dissociation mechanisms and suggestion of a mechanism consistent with the experimental and theoretical results obtained in a supersonic COIL for the gain, temperature, I 2 dissociation fraction, and N at the optical …
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The oxygen flows through the exit to an iodine-oxygen mixing system and expanded to supersonic velocity in a slit supersonic nozzle. As shown in Ref. 9, for supersonic mixing the output power and ...
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The Variable Mach Number Supersonic Wind Tunnel is capable of providing a test flow with a continuously variable Mach number in the range of 1.3 to 3.1. The facility (see left image) consists of a 300 psi compressed air source, settling chamber, variable nozzle block (see right image detail), test section, and diffuser.
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In this work, supersonic hydrogen combustion in the Hyshot II scramjet engine is investigated. In particular, fundamental physics of mixing, combustion and vorticity generation as well as the interaction between shock waves, boundary layer and heat release are analyzed by means of 3D Large Eddy Simulations (LES) using detailed …
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A simple one-dimensional (1D) computational fluid dynamics (CFD) model of the chemical oxygen iodine laser (COIL) with supersonic mixing is compared with three-dimensional (3D) CFD models and with ...
به خواندن ادامه دهیدA supersonic scheme was employed for mixing working gases viz., energy carrying [singlet oxygen (SO) with buffer nitrogen] and emitting (vapour mixture of iodine and nitrogen) [3, 4]. Iodine vapour mixed with the carrier gas (nitrogen) was supplied into the subsonic part of the nozzle. The supersonic nozzle with an exit size of 100 6:7 cm
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A significant amount of high-speed combustion research has been directed towards the design of the scramjet combustor due to emerging interest in hypersonic flights. The combustion and mixing timescales in a supersonic combustion are of the order of few milliseconds [1], [2], [3]. Hence, the duration available for complete combustion is very short.
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The most widely used approach for laser medium generation has been the use of subsonic mixing and dissociation of molecular iodine in an O2(1 ) medium with high dilution by …
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A schematic diagram of a typical supersonic COIL device is shown in Fig. 9. The main components are (1) a gas–liquid reactor producing singlet oxygen, (2) the iodine supersonic mixing nozzles, (3) the gain region and optical resonator, and (4) the pressure recovery system.
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The mixing efficiency for supersonic injection of iodine (∼0.85) is much larger than for transonic injection (∼0.5), the maximum values of the gain being ∼0.65%/cm for both injection schemes.
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that the mixing characteristics are strongly related to jet to cross flow momentum ratio. In case of higher values of momentum ratio, slower mixing rates, higher penetration, and more losses of stagnation pressure are observed. Sriram and Mathews 18 simulated transverse sonic injection in supersonic flow using Roe™s approximate Riemann solver
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A "swallowtail" cavity for the supersonic combustor was proposed to serve as an efficient flame holder for scramjets by enhancing the mass exchange between the cavity and the main flow. A numerical study on the "swallowtail" cavity was conducted by solving the three-dimensional Reynolds-averaged Navier–Stokes equations implemented …
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