Reproduction de : Thèse de doctorat : Mathématiques appliquées : Lille 1 : 2005. / N° d'ordre (Lille 1) : 3608. Résumé. Titre provenant de la page de titre du document numérisé. Bibliogr. p. 245-250.

Reproduction de : Thèse de doctorat : Mécanique des fluides et Aérodynamique : Lille 1 : 2006. / N° d'ordre (Lille 1) : 3945. Titre provenant de la page de titre du document numérisé. Bibliogr. p. 255-258. Liste des publications et rapports.

Thèse de doctorat : Sciences physique et de l'ingénieur. Mécanique des fluides et mathématiques appliquées : Bordeaux 1 : 2009. Thèse de doctorat : Sciences physique et de l'ingénieur. Mécanique des fluides et mathématiques appliquées : Politecnico di Torino : 2009. / Titre provenant de l'écran-titre.

Thèse de doctorat : Mécanique : Lille 1 : 2002. / N° d'ordre (Lille) : 3246. Résumé en français et en anglais. Bibliogr. p. 185-188.

Thesis (M.S.)--Worcester Polytechnic Institute. / Keywords: CFD; computational fluid dynamics; plume; nozzle; DSMC; numerical modelling. Includes bibliographical references (p. 83-86).

Thèse de doctorat : PHYSIQUE : Nice : 1998. / 1998NICE5198. 95 REF.

Thesis (Ph. D.)--Institute of Paper Chemistry, 1943. / Bibliography: leaf 79.

Inter-turbine burners are useful devices for increasing engine power. To reduce the size of these combustion devices, ultra-compact combustor (UCC) concepts are necessary. One such UCC concept is the centrifugal-force based high-g combustor design. Here, a model ultra-compact combustor (UCC) with fuel spray injection is simulated using large eddy simulation (LES) and Reynolds-Averaged Navier-Stokes (RANS) methodologies to understand mixing and spray dispersion inside centrifugal-based combustion systems. Both non-evaporating and evaporating droplet simulations were carried, as well as the tracking of a passive scalar, to explore this multiphase system. Simulation results show that mixing of fuel and oxidizer is based on a jet-in-crossflow system, with the fuel jet issuing into a circulating oxidizer flow stream. It is seen that a a high velocity vortex-like ring develops in the inner core of the combustor, which has enough momentum to obstruct the path of combustion products. There is minimal fuel droplet and vapor segregation inside the combustor and enhanced turbulent mixing is seen at mid-radius. / text

A panel method derived from inviscid irrotational flow theory and utilizing hyperboloid panels is developed and applied to the simulation of steady fully wetted flows inside water-jet pumps and rocket engine inducers. The source and dipole influence coefficients of the hyperboloid panels are computed using Gauss quadrature. The present method solves the boundary value problem subject to a uniform inflow directly by discretizing the blade, casing/shroud and hub geometries with panels. The Green's integral equation and the influence coefficients for the water-jet/inducer problem are defined and solved by allocating constant strength sources and dipoles on the blade, hub and casing surfaces and constant strength dipoles on the shed wake sheets from the rotor/ stator blades. The rotor- stator interaction is accomplished using an iterative procedure which considers the effects between the rotor and the stator, via circumferentially averaged induced velocities. Finally, the hydrodynamic performance predictions for the water-jet pump and the inducer from the present method are validated against existing experimental data and numerical results from Reynolds Averaged Navier- Stokes (RANS) solvers. / text

In this thesis, we consider soltions to the two-dimensional Euler equations with uniformly continuous initial vorticity in a critical or subcritical Besov space. We use paradifferential calculus to show that the solution will lose an arbitrarily small amount of smoothness over any fixed finite time interval. This result is motivated by a theorem of Bahouri and Chemin which states that the Sobolev exponent of a solution to the two-dimensional Euler equations in a critical or subcritical Sobolev space may decay exponentially with time. To prove our result, one can use methods similar to those used by Bahouri and Chemin for initial vorticity in a Besov space with Besov exponent between 0 and 1; however, we use different methods to prove a result which applies for any Sobolev exponent between 0 and 2. The remainder of this thesis is based on joint work with J. Kelliher. We study the vanishing viscosity limit of solutions of the Navier-Stokes equations to solutions of the Euler equations in the plane assuming initial vorticity is in a variant Besov space introduced by Vishik. Our methods allow us to extend a global in time uniqueness result established by Vishik for the two-dimensional Euler equations in this space. / text