LDV Measurements of the Flow Field in the Nozzle Region of a Confined Double Annular Burner

[+] Author and Article Information
Francois Schmitt, Birinchi K. Hazarika, Charles Hirsch

Department of Fluid Mechanics, Vrije Universiteit Brussel, Pleinlaan 2, B-1050 Brussels, Belgium

J. Fluids Eng 123(2), 228-236 (Feb 06, 2001) (9 pages) doi:10.1115/1.1366681 History: Received November 20, 2000; Revised February 06, 2001
Copyright © 2001 by ASME
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Wilcox, D. C., 1998, Turbulence Modeling for CFD, DCW Industries.
Piquet, J., 1999, Turbulent Flows, Models and Physics, Springer-Verlag, Berlin.
Beér, J. M., and Chigier, N. A., 1983, Combustion Aerodynamics, Robert E. Krieger Publi. Comp., Malabar.
Escudier,  M. P., and Keller,  J. J., 1985, “Recirculation in Swirling Flow: A Manifestation of Vortex Breakdown,” AIAA Journal, 23, p. 111.
Frisch, U., 1995, Turbulence, The Legacy of A. N. Kolmogorov, Cambridge University Press, Cambridge.
Gnedenko, B. V. and Kolmogorov, A. N., 1954, Limit Distributions for Sums of Independent Random Variables, Addison-Wesley.
Thring, M. W., and Newby, M. P., 1953, “Combustion Length of Enclosed Turbulent Jet Flames,” Fourth Symposium on Combustion, Williams and Wilkins, pp. 789–796.
Craya, A. and Curtet, R., 1955, “Sur l’évolution d’un jet en espace confine,” C. R. Acad. Sci., Paris, 241, p. 621.
Curtet,  R., 1958, “Confined Jets and Recirculation Phenomena with Cold Air,” Combust. Flame, 2, p. 383.
Becker, H. A., 1961, “Concentration Fluctuation in Ducted Jet-Mixing,” Sc. D. thesis in Chem. Engg., MIT, Cambridge, Mass.
Becker, H. A., Hottel, H. C., and Williams, G. C., 1963, “Mixing and Flow in Ducted Turbulent Jets,” Ninth Symposium on Combustion, Academic Press, pp. 7–20.
Guruz,  A. G., , 1975, “Aerodynamics of a Confined Burning Jet,” Combust. Sci. Technol., 9, p. 103.
Hazarika, B. K., Vucinic, D., Schmitt, F., and Hirsch, Ch., 2001, “Analysis of Toroidal Vortex Unsteadiness and Turbulence in a Confined Double Annular Jet,” AIAA paper 2001-0146, 39th AIAA Aerospace Sciences Meeting & Exhibit, Reno, January 2001.
Zhu,  J., and Shih,  T.-H., 1994, “Computation of Confined Coflow Jets with Three Turbulence Models,” Int. J. Numerical Meth. Fluids, 19, p. 939.
Launder,  B. E., and Spalding,  D. B., 1974, “The Numerical Computation of Turbulent Flows,” Comput. Methods Appl. Mech. Eng., 3, pp. 269–289.
Gatski,  T. B., and Speziale,  C. G., 1993, “On Explicit Algebraic Stress Models for Complex Turbulent Flows,” J. Fluid Mech., 254, p. 59
Shih,  T.-H., and Lumley,  J. L., 1993, “Remarks on Turbulent Constitutive Relations,” Math. Comput. Modell., 18, p. 9.
Schmitt,  F., and Hirsch,  Ch., 2000, “Experimental Study of the Constitutive Equation for an Axisymmetric Complex Turbulent Flow,” Z. Angew. Math. Mech., 80, pp. 815–825.


Grahic Jump Location
Superposition of axial velocity, radial velocity, kinetic energy k and stress, for x=0.19. This traverse goes through all the vortices, big central and small lateral.
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Superposition of axial velocity, radial velocity, kinetic energy k and stress τuv, for x=0.38. This traverse goes only through the big central vortex.
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From top to bottom, left to right: evolution of the axial velocity profile, with the distance from the burner exit. Different zones are found, possessing recirculation and merging of the different streams. Zone A corresponds to primary and secondary vortices, and possesses 3 recirculation regions. Zone B corresponds to an annular jet, with 2 recirculation regions. Zone C corresponds to a central jet, with 1 recirculation region.
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(a) Picture of the entrance of the burner, showing the aluminum rings; (b) picture of the exit of the burner, showing the nozzles producing the primary and secondary flows
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The entrance of the burner: there are 3 elements in this region to facilitate smooth entry, denoted F, G, and H. The entrance of the central tube is covered with a bullet of ellipsoid shape (F). The two streams are separated by an annular boundary, whose entrance is covered with an aluminum ring (G), of elliptic cross section, with axial length of 20 mm. The exterior boundary has an entrance covered with an aluminum ring (H).
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The exit of the burner, indicating the dimensions of different diameters and showing contracting nozzle pieces I and J. Piece J and I produce area contraction ratio of 2.2:1 and 2.4:1, respectively.
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Decrease of the error in the estimate of mean values, with the number of particles considered
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Superposition of axial velocity profiles, and of radial velocity, at the exit of the nozzle, for different angles of the burner
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An overall display of the facility. Inlet arrangement, a cut on the burner, and the combustion chamber are shown. The nozzle region corresponding to the measurements is indicated. The burner is made of 5 PVC tubes: two tubes are used for the exterior boundary, two for the boundary between the two ducts, and one for the central boundary. The tubes stay together using threaded rods. Two supports (denoted 1 and 2) support the burner. Dimensions in mm.
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Experimental grid chosen for the measurements. Darker zones correspond to one measurement every 0.5-mm along the vertical.
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Streamlines of the flow. This shows the direct and recirculating flows, the central vortex and double-toroidal vortices. The different zones identified with traverse sections in Fig. 9 are indicated.
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Vector plot of the velocity field on some grid points
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Axial velocity: gray levels and isolines 0, 0.3, and 0.57. Isoline 0 surrounds 5 recirculation regions
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Isolines and display of the kinetic energy k. The values of the isolines are the following: .024, .04, .056, .072, .088, .104, .12.
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Isolines and display of the stress τuv=uv−UV. The values of the isolines are the following: −.037, −.026, −.015, −.005, 0., .005, .015, .026, .037.




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