Turbulent combustion flow through variable cross section channel
Abstract
The object of this study is to develop a new evolutionary numerical method for solving direct task of Laval nozzle, which provides noniterative calculations of chemical reacting turbulent flows with detailed kinetic chemistry. The numerical scheme of fourth order along the normal coordinate and second order along the streamwise one is derived for calculation of differencedifferential equations of the second order and the first order. Marching method provides the possibility of computing field flow in subsonic section of nozzle and near an expansion. Critical mass consumption is calculated with controlled accuracy. After critical cross section of nozzle a combined marching method with global iterations over axial pressure (only) makes it possible to overcome ill posedness of mixed supersonic flow and calculate the whole flow field near and after critical cross section. Numerical results are demonstrated on turbulent burning hydrogenoxygen flow through Laval nozzle with curvature of wall K{sub w} = 0.5.
 Authors:
 Publication Date:
 Research Org.:
 Russian Academy of Science, Inst. for High Temperatures, Moscow (RU)
 OSTI Identifier:
 20019082
 Resource Type:
 Conference
 Resource Relation:
 Conference: 5th ASME/JSME Thermal Engineering Joint Conference, San Diego, CA (US), 03/14/199903/19/1999; Other Information: 1 CDROM. Operating Systems required: Windows i386, i486, Pentium Pro, MS Windows 3.1, 95, or NT3.51, 8MB Ram, MacIntosh and Power MacIntosh with a 68020 or greater processor, System software version 7.1, 3.5 MB RAM (5 MB for PowerMac), 6 MB available harddisk space, Unix; PBD: 1999; Related Information: In: Proceedings of the 5th ASME/JSME thermal engineering joint conference, [3600] pages.
 Country of Publication:
 United States
 Language:
 English
 Subject:
 33 ADVANCED PROPULSION SYSTEMS; 08 HYDROGEN; RAMJET ENGINES; HYDROGEN FUELS; MATHEMATICAL MODELS; COMBUSTION KINETICS; TURBULENT FLOW; NOZZLES; FLUID FLOW
Citation Formats
Rogov, B.V., and Sokolova, I.A. Turbulent combustion flow through variable cross section channel. United States: N. p., 1999.
Web.
Rogov, B.V., & Sokolova, I.A. Turbulent combustion flow through variable cross section channel. United States.
Rogov, B.V., and Sokolova, I.A. Thu .
"Turbulent combustion flow through variable cross section channel". United States.
doi:.
@article{osti_20019082,
title = {Turbulent combustion flow through variable cross section channel},
author = {Rogov, B.V. and Sokolova, I.A.},
abstractNote = {The object of this study is to develop a new evolutionary numerical method for solving direct task of Laval nozzle, which provides noniterative calculations of chemical reacting turbulent flows with detailed kinetic chemistry. The numerical scheme of fourth order along the normal coordinate and second order along the streamwise one is derived for calculation of differencedifferential equations of the second order and the first order. Marching method provides the possibility of computing field flow in subsonic section of nozzle and near an expansion. Critical mass consumption is calculated with controlled accuracy. After critical cross section of nozzle a combined marching method with global iterations over axial pressure (only) makes it possible to overcome ill posedness of mixed supersonic flow and calculate the whole flow field near and after critical cross section. Numerical results are demonstrated on turbulent burning hydrogenoxygen flow through Laval nozzle with curvature of wall K{sub w} = 0.5.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Thu Jul 01 00:00:00 EDT 1999},
month = {Thu Jul 01 00:00:00 EDT 1999}
}

This is an experimental determination of local and integral heat transfer rates for a stream of hightemperature dissociation products from the combustion of natural gas at the inital section of a rectangular channel. The results are compared with theoretically calculated data. 4 figs.

Integral combustion simulation of a turbulent reacting flow in a channel with crossstream injection
A new integral onestep reaction submodel has been developed for an Argonne combustion computer code to simulate reacting flows of an advanced combustor for magnetohydrodynamic power generation. The integral combustion code makes numerical calculations of a reacting flow more efficient and more stable while still preserving the major physical effects of the complex combustion processes. Results of the simulation indicate that (1) fluid mixing is mainly responsible for combustion performance and (2) counterflow injection with an injection angle in the range of 120[degree] to 140[degree] yields the best mixing and combustion performance. 
Magnetohydrodynamic Flow through Ducts of Variable Cross Section
BS>Equations govenning the quasionedimensional nonsteady flow of fluid of infinite electric conductivity through ducts of variable cross section are presented. The equations were obtained by assuming that only one component of the magnetic field is not equal to zero. The problem of propagation of a shock wave through a duct of variable cross section and the interaction of shock and simple waves could be solved with these equations. (M.C.G.) 
Laminar flow of two phases through a capillary tube with variable square crosssection
The angularity of the channels in a porous medium and the variation in their crosssection can be schematized by a constricted capillary tube of square crosssection. The flow of a nonwetting droplet in such a capillary, already filled with an immiscible fluid, is described by approximated equations derived from Stokes equations. The droplet flows through the constriction if the ratio of the viscosity forces to the interfacial forces is greater than a critical value which depends on the contact angle, and on the viscosity ratio. The greater the droplet viscosity, the more easily the droplet flows through the throat whatevermore »