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  • Optimisation techniques applied to the design of gas turbine blades cooling systems

    This study is part of an AVIO project concerning the development of High Pressure Turbine blades with advanced cooling systems. Due to the high gas temperatures entering the turbine of the most recent aero-engines (in general up to 2000 K at the turbine inlet), a very efficient cooling system is required in order to maintain the metal temperatures below the allowable limits.

    paper 2005
  • MultiObjective Optimization in Engine Design Using Genetic Algorithms to Improve Engine Performance

    The use of genetic algorithms (GAs) is enjoying ever-increasing popularity among engineers and designers as a way of optimizing their products and processes. One of the major advantages of such techniques is that they allow true multiobjective optimization (where the objectives are kept separate throughout the optimization process, rather than being collapsed into a single, weighted objective function from the beginning).

    paper 2005
  • Coupled modeFRONTIER - FIRE Approach for ICEngine Intake Port Optimization

    Internal Combustion Engine (IC-Engine) efficiency and emission characteristics are at great extent, governed by the details of the intake port-combustion chamber arrangement. In this context, the discharge coefficient and swirl/tumble numbers, are commonly used to characterize the intake port with respect to the volumetric efficiency and, at least partly, to the combustion of both diesel and gasoline engines.

    paper 2005
  • Optimization of a Two Loop Pipe Network

    Here we describe how the problem was solved using genetic algorithms available in the commercial optimization software, modeFRONTIER, coupled with Epanet 2, a hydraulics program developed by the U.S. Environmental Protection Agency (EPA).

    paper 2004
  • Reduced Basis Methods with modeFrontier

    In this proceeding we present some results obtained with modeFrontier coupled with some reduced basis methods that allow fast and reliable approximation of certain scalar quantities derived from partial differential 
    equations solutions.
     

    paper 2004
  • Transonic 3D Wing Multi-Objective Optimization

    The purpose of this work is the optimization of the ONERA M6 wing that should be optimized at a fixed Mach number and at a fixed angle of attack, in order to reduce the inviscid drag with constraints on the lift coefficient and on the maximum thickness of spanwise wing cuts.

    paper 2003
  • Two Dimensional Axial Compressor Optimization

    The purpose of this work is to optimize the stator shape of an axial compressor, in order to maximize the global efficiency of the machine, fixing the rotor shape. We have used a 3-D parametric mesh and the CFX Tascflow code for the flow simulation. To find out the most important variables in this problem, we have run a preliminary DOE series of designs, whose results have been analyzed by a statistic tool.

    paper 2003
  • Blood Pressure Measurement device design

    The objective of this optimisation is to find The best compromise between pressure losses and pressure uniformity on a blood pressure measurement device. The geometric model is defined in fig.1, from which it is possible to note that we consider 6 variables: the 2D ellyptical section semiaxes, the position and the the angle of incidence of the inlet and outlet pipes. 

    paper 2002
  • Three-dimensional inverse design of axial compressor stator blade using neural networks and direct Navier-Stokes solver

    In this paper we describe a new method for the aerodynamic optimisation and inverse design problem resolution. This method is based on the coupling of a gradient-based l optimiser with a neural network. A Navier-Stokes flow solver is used for an accurate computation of the objective function.

    paper 2002
  • Gas Assisted Injection Molding optimization with M.O.G.A.

    Gas assisted injection molding is a processing technique used to produce hollow sections in plastic parts. This is achieved by injecting a gas into a tool cavity partially filled with resin, while the resin injection continues to prevent a hesitation of the flow front. After the resin injection is completed, the gas injection continues, forming a gas bubble that keeps the resin flow front moving until the resin skin reaches the end of the mold.

    paper 2001

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