Showing results 61 to 80 of 81
  Compressor and Turbine Blade Design by OptimizationLéonard, Olivier  ; ; Duysinx, Pierre in Bloebaum, C. (Ed.) Proceedings of the 3rd World Congress of Structural and Multidisciplinary Optimization WCSMO3 (1999, May) Compressor and turbine blade design involves thermodynamical, aerodynamical and mechanical aspects, resulting in an important number of iterations. Inverse methods and optimization procedures help the ... [more ▼] Compressor and turbine blade design involves thermodynamical, aerodynamical and mechanical aspects, resulting in an important number of iterations. Inverse methods and optimization procedures help the designer in this long and eventually frustrating process. In this paper an optimization procedure is presented which solves two types of two-dimensional or quasi-three-dimensional problems: the inverse problem, for which a target velocity distribution is imposed, and a more global problem, in which the aerodynamic load is maximized. [less ▲] Detailed reference viewed: 70 (2 ULg)Aerodynamic and Mechanical Design of Compressor Blades Including Static Analysis; ; Essers, Jean-André et alin Proceedings od the 3rd World Congress of Structural and Multidisciplinary Optimization (1999, May) Detailed reference viewed: 53 (4 ULg)Application of a three-dimensional inverse method to the design of a centrifugal compressor impeller; Léonard, Olivier ; in Proceedings of the ASME Turbo Expo 1998 (1998, June) ASME Paper 98-GT-127 Detailed reference viewed: 24 (1 ULg)Developpement d'une méthodologie d'optimisation aérodynamique et mécanique d'aubes de compresseurs; ; et al in RFM : Revue Française de Mécanique (1998), 4 Le projet décrit dans cet article a pour but de réaliser le dimensionnement des aubages d'un compresseur axial; pour ce faire, des codes de calcul aérodynamique et mécanique sont intégrés dans un ... [more ▼] Le projet décrit dans cet article a pour but de réaliser le dimensionnement des aubages d'un compresseur axial; pour ce faire, des codes de calcul aérodynamique et mécanique sont intégrés dans un processus d'optimisation globale. Le transfert de données entre les différents modules utilisés est pris en charge par un logiciel gestionnaire de tâches, sur lequel est axée la méthode. Les codes aérodynamiques, basés sur l'approche classique quasi-tridimensionnelle, combinent une simulation d'écoulement dans le plan méridien ainsi qu'une succession d'écoulements en grilles d'aubes. Les codes mécaniques permettent une analyse à la fois statique et dynamique des aubages ; on notera en outre la possibilité de leur adjoindre des calculs d'impact ou de vérification de la durée de vie. Dans son état actuel, le code général permet d'optimiser la masse ou le rendement d'un étage de compression sur la base d'un calcul aérodynamique dans le plan méridien et d'une vérification des marges fréquentielles. [less ▲] Detailed reference viewed: 135 (14 ULg) A Navier-Stokes Inverse Method Based on a Moving Blade Wall StrategyLéonard, Olivier ; in Proceedings of the ASME Turbo Expo 1997 (1997, June) Detailed reference viewed: 9 (0 ULg)Blade Analysis and Design Using an Implicit Flow SolverLéonard, Olivier ; ; in 2nd European Conference on Turbomachinery - Fluid Dynamics and Thermodynamics - Proceedings of the conference (1997, March) Detailed reference viewed: 19 (1 ULg)A two-dimensional Navier-Stokes inverse solver for compressor and turbine blade design; Léonard, Olivier ; in Proceedings of the Institution of Mechanical Engineers. Part A, Journal of Power and Energy (1997), 211(4), 299-307 A two-dimensional viscous inverse method for the design of compressor and turbine blades is presented. It iteratively modifies an initial geometry until a prescribed pressure distribution is reached on ... [more ▼] A two-dimensional viscous inverse method for the design of compressor and turbine blades is presented. It iteratively modifies an initial geometry until a prescribed pressure distribution is reached on the blade surface. The method solves the time-dependent Navier-Stokes equations in a numerical domain of which some boundaries (the blade walls) move during the transient part of the computation. The geometry modification algorithm is based on the transpiration principle: a normal velocity distribution is computed from the difference between the actual and prescribed pressure distributions, and is used to modify the blade shape. A time iteration is then performed on this new blade shape, taking into account the grid movement during the time stepping. A two-dimensional upwind finite-volume Navier-Stokes solver has been developed. The multiblock strategy allows for a selective concentration of the discretization points in the zones of higher gradients. Applications to turbine and compressor blade design illustrate the accuracy of the flow computation, the capabilities and efficiency of the inverse method. [less ▲] Detailed reference viewed: 62 (1 ULg)On the Existence of a Solution for Turbomachinery Blade Design; Léonard, Olivier in Proceedings of the 4th Belgian National Congress on Theoretical and Applied Mechanics (1997) Detailed reference viewed: 14 (3 ULg)Développement d’une méthodologie d’optimisation aérodynamique et mécanique d’aubes de compresseurs; ; Essers, Jean-André et alin Proceedings of the 4th Belgian National Congress on Theoretical and Applied Mechanics (1997) Detailed reference viewed: 17 (2 ULg)Application of a High-Order Upwind Finite-Volume Scheme to 2D Cascade Flows Using a Multi-Block Approach; Léonard, Olivier ; Essers, Jean-André in Proceedings of the 12th ISABE Conference (1995) Detailed reference viewed: 12 (2 ULg)Permeable Wall Concept for Transonic Blade DesignLéonard, Olivier ; ; in Proceedings of the 3rd Belgian National Congress on Theoretical and Applied Mechanics (1994) Detailed reference viewed: 5 (1 ULg)Design Method for Subsonic and Transonic Cascade with Prescribed Mach Number DistributionLéonard, Olivier ; in Journal of Turbomachinery (1992), 114(3), 553-560 An iterative procedure for blade design, using a time marching procedure to solve the unsteady Euler equations in the blade-to-blade plane, is presented. A flow solver, which performs the analysis of the ... [more ▼] An iterative procedure for blade design, using a time marching procedure to solve the unsteady Euler equations in the blade-to-blade plane, is presented. A flow solver, which performs the analysis of the flow field for a given geometry, is transformed into a design method. This is done by replacing the classical slip condition (no normal velocity component) by other boundary conditions, in such a way that the required pressure or Mach number distribution may be imposed directly on the blade. The unknowns are calculated on the blade wall using the so-called compatibility relations. Since the blade shape is not compatible with the required pressure distribution, a nonzero velocity component normal to the blade wall evolves from the new flow calculation. The blade geometry is then modified by resetting the wall parallel to the new flow field, using a transpiration technique, and the procedure is repeated until the calculated pressure distribution has converged to the required one. Examples for both subsonic and transonic flows are presented and show a rapid convergence to the geometry required for the desired Mach number distribution. An important advantage of the present method is the possibility to use the same code for the design and the analysis of a blade. [less ▲] Detailed reference viewed: 34 (4 ULg)Inverse Design of Compressor and Turbine Blades at Transonic Flow ConditionsLéonard, Olivier ; in Proceedings of the ASME Turbo Expo 1992 (1992, June) Detailed reference viewed: 25 (1 ULg)Conception et développement d'une méthode inverse de type Euler et application à la génération de grilles d'aubes transsoniquesLéonard, Olivier Doctoral thesis (1992) Detailed reference viewed: 20 (3 ULg)Permeable Wall Boundary Conditions For Transonic Airfoil DesignLéonard, Olivier ; in Proceedings od the First European Computational Fluid Dynamics Conference (1992) Detailed reference viewed: 5 (1 ULg)Design Method for Subsonic and Transonic Cascade with Prescribed Mach Number DistributionLéonard, Olivier ; in Proceedings of the ASME Turbo Expo 1991 (1991, June) A iterative procedure for blade design, using a time marching procedure to solve the unsteady Euler equations in the blade-to-blade plane, is presented. A flow solver, which performs the analysis of the ... [more ▼] A iterative procedure for blade design, using a time marching procedure to solve the unsteady Euler equations in the blade-to-blade plane, is presented. A flow solver, which performs the analysis of the flow field for a given geometry, is transformed into a design method. This is done by replacing the classical slip condition (no normal velocity component) by other boundary conditions, in such a way that the required pressure or Mach number distribution may be imposed directly on the blade. The unknowns are calculated on the blade wall using the so-called compatibility relations. Since the blade shape is not compatible with the required pressure distribution, a nonzero velocity component normal to the blade wall evolves from the new flow calculation. The blade geometry is then modified by resetting the wall parallel to the new flow field, using a transpiration technique, and the procedure is repeated until the calculated pressure distribution has converged to the required one. Examples for both subsonic and transonic flows are presented and show a rapid convergence to the geometry required for the desired Mach number distribution. An important advantage of the present method is the possibility to use the same code for the design and the analysis of a blade. [less ▲] Detailed reference viewed: 28 (1 ULg)Blade Design and Analysis Using a Modified Euler SolverLéonard, Olivier ; in Proceedings of ICIDES-3 (1991) Detailed reference viewed: 7 (1 ULg)Subsonic and Transonic Cascade DesignLéonard, Olivier in Van den Braembussche, René (Ed.) Inverse Methods for Airfoil Design for Aeronautical and Turbomachinery Applications (1990) Detailed reference viewed: 20 (3 ULg)Subsonic and Transonic Blade Design by Means of Analysis Codes; Léonard, Olivier ; in Computational Methofs for Aerodynamic Design (Inverse) and Optimization (1990, March) Detailed reference viewed: 34 (2 ULg)Subsonic and Transonic Blade DesignLéonard, Olivier ; in Proceedings od the 2nd Belgian National Congress on Theoretical and Applied Mechanics (1990) Detailed reference viewed: 12 (2 ULg) |
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