The Experts below are selected from a list of 18 Experts worldwide ranked by ideXlab platform

L.j. Julyk - One of the best experts on this subject based on the ideXlab platform.

  • Waste Feed Delivery Transfer System Analysis [SEC 1 & 2]
    2001
    Co-Authors: L.j. Julyk
    Abstract:

    This document provides a documented basis for the Required Design Pressure rating and pump Pressure capacity of the Hanford Site waste-transfer system in support of the waste feed delivery to the immobilization plant for processing. The scope of the analysis includes the 200 East Area double-shell tank waste transfer pipeline system and the associated transfer system pumps for all Phase 1B and Phase 2 waste transfers from AN, AP, AW, AY, and AZ Tank Farms.

  • Waste Feed Delivery Transfer System Analysis
    2000
    Co-Authors: L.j. Julyk
    Abstract:

    This document provides a documented basis for the Required Design Pressure rating and pump Pressure capacity of the Hanford Site waste-transfer system in support of the waste feed delivery to the privatization contractor for vitrification. The scope of the analysis includes the 200 East Area double-shell tank waste transfer pipeline system and the associated transfer system pumps for a11 Phase 1B and Phase 2 waste transfers from AN, AP, AW, AY, and A2 Tank Farms.

Maryam Khelghatibana - One of the best experts on this subject based on the ideXlab platform.

  • Multi-Objective and Multi-Point Aerodynamic Optimization of Transonic Fan Blades
    Volume 1: Advances in Aerospace Technology, 2014
    Co-Authors: Maryam Khelghatibana, Jean-yves Trépanier, Christophe Tribes, Jason Nichols
    Abstract:

    A multi-objective and multi-point optimization methodology is developed for aerodynamic Design of transonic fan blades. The optimization method aims to increase Design efficiency, near stall efficiency and stall margin while maintaining the Required Design Pressure ratio and high speed choke margin. Numerical analyses are performed by solving three-dimensional Reynolds-Averaged Navier-Stokes equations combined with shear stress turbulence model. A multi-level blade parameterization is employed to modify the blade geometry. The proposed method is applied to reDesign NASA rotor 67. First, an optimization case with considering two operating conditions at peak efficiency and near stall is performed to demonstrate the relation between near stall efficiency and stall margin. An investigation on Pareto optimal solutions of this optimization shows that the stall margin is increased with improving near stall efficiency. Then, in order to maintain the Required choke margin, an operating point at high speed choked flow is added to the optimization process. A final optimized Design is selected by considering the interaction of Design requirements at all three operating points. The new Design presents higher efficiency and stall margin without any reduction in the chocking mass flow rate.© 2014 ASME

  • An Approach for Aerodynamic Optimizaton of Transonic Fan Blades
    2014
    Co-Authors: Maryam Khelghatibana
    Abstract:

    RESUME L'optimisation de la soufflante du moteur est une procedure longue et complexe a cause de la complexite du champ d'ecoulement a l'interieur du soufflante, les exigences contradictoires de conception et l'espace de conception de grande dimension. Afin de repondre a tous ces defis, une methode d'optimisation aerodynamique des pales des soufflantes des moteurs transsoniques a ete developpee dans ce projet. Cette methode automatise le processus de conception en integrant une methode de parametrage geometrique, un solveur CFD et des methodes d'optimisation numerique. Cette methode peut etre appliquee a la fois a des problemes de conception a un ou plusieurs points de Design. Une parametrisation multi-niveau pour les pales de soufflantes transsoniques a ete utilisee pour modifier la geometrie des pales. Des analyses numeriques sont effectuees par la resolution des equations 3D Reynolds-Averaged Navier-Stokes combine avec un modele turbulence SST. Les algorithmes genetiques et les methodes d'optimisation hybrides sont appliquees pour resoudre le probleme d'optimisation. Afin de verifier l'efficacite et la faisabilite de la methode d'optimisation, un probleme d'optimisation visant a maximiser l'efficacite du point de Design a ete formule et applique dans le but de reDesigner un cas de test. Cependant, la conception des pales de soufflantes transsoniques est en soi un probleme a multiples facettes qui traite de plusieurs objectifs tels que l'efficacite, la marge de pompage, et la marge d’etranglement. La methode d'optimisation multi-point proposee dans l'etude actuelle est formulee comme un probleme bi-objectif dans le but de maximiser les efficacites du point de Design et au point pres du decrochage tout en maintenant le rapport de pression au point de Design. L'amelioration de ces objectifs se deteriore de maniere significative au niveau de la marge d’etranglement, en particulier a des vitesses de rotation elevees. Par consequent, une autre contrainte est integree dans le probleme d'optimisation en vue de prevenir la reduction de la marge d’etranglement a des vitesses elevees. Etant donne que la localisation du debut du decrochage est numeriquement tres couteuse, la marge de pompage n'a pas ete consideree comme un objectif dans l'enonce du probleme. Cependant, l'amelioration de l'efficacite a la condition d’operation proche du decrochage entraine une meilleure performance a la condition de decrochage qui pourrait ameliorer la marge de pompage. Une enquete est donc effectuee sur les solutions Pareto-optimales pour demontrer la relation entre l'efficacite aux conditions pres du decrochage et de la marge de pompage.----------ABSTRACT Aerodynamic Design optimization of transonic fan blades is a highly challenging problem due to the complexity of flow field inside the fan, the conflicting Design requirements and the high-dimensional Design space. In order to address all these challenges, an aerodynamic Design optimization method is developed in this study. This method automates the Design process by integrating a geometrical parameterization method, a CFD solver and numerical optimization methods that can be applied to both single and multi-point optimization Design problems. A multi-level blade parameterization is employed to modify the blade geometry. Numerical analyses are performed by solving 3D RANS equations combined with SST turbulence model. Genetic algorithms and hybrid optimization methods are applied to solve the optimization problem. In order to verify the effectiveness and feasibility of the optimization method, a single-point optimization problem aiming to maximize Design efficiency is formulated and applied to reDesign a test case. However, transonic fan blade Design is inherently a multi-faceted problem that deals with several objectives such as efficiency, stall margin, and choke margin. The proposed multi-point optimization method in the current study is formulated as a bi-objective problem to maximize Design and near-stall efficiencies while maintaining the Required Design Pressure ratio. Enhancing these objectives significantly deteriorate the choke margin, specifically at high rotational speeds. Therefore, another constraint is embedded in the optimization problem in order to prevent the reduction of choke margin at high speeds. Since capturing stall inception is numerically very expensive, stall margin has not been considered as an objective in the problem statement. However, improving near-stall efficiency results in a better performance at stall condition, which could enhance the stall margin. An investigation is therefore performed on the Pareto-optimal solutions to demonstrate the relation between near-stall efficiency and stall margin. The proposed method is applied to reDesign NASA rotor 67 for single and multiple operating conditions. The single-point Design optimization showed +0.28 points improvement of isentropic efficiency at Design point, while the Design Pressure ratio and mass flow are, respectively, within 0.12% and 0.11% of the reference blade. Two cases of multi-point optimization are performed: First, the proposed multi-point optimization problem is relaxed by removing the choke margin constraint in order to demonstrate the relation between near-stall efficiency and stall margin. An investigation on the Pareto-optimal solutions of this optimization

Jason Nichols - One of the best experts on this subject based on the ideXlab platform.

  • Multi-Objective and Multi-Point Aerodynamic Optimization of Transonic Fan Blades
    Volume 1: Advances in Aerospace Technology, 2014
    Co-Authors: Maryam Khelghatibana, Jean-yves Trépanier, Christophe Tribes, Jason Nichols
    Abstract:

    A multi-objective and multi-point optimization methodology is developed for aerodynamic Design of transonic fan blades. The optimization method aims to increase Design efficiency, near stall efficiency and stall margin while maintaining the Required Design Pressure ratio and high speed choke margin. Numerical analyses are performed by solving three-dimensional Reynolds-Averaged Navier-Stokes equations combined with shear stress turbulence model. A multi-level blade parameterization is employed to modify the blade geometry. The proposed method is applied to reDesign NASA rotor 67. First, an optimization case with considering two operating conditions at peak efficiency and near stall is performed to demonstrate the relation between near stall efficiency and stall margin. An investigation on Pareto optimal solutions of this optimization shows that the stall margin is increased with improving near stall efficiency. Then, in order to maintain the Required choke margin, an operating point at high speed choked flow is added to the optimization process. A final optimized Design is selected by considering the interaction of Design requirements at all three operating points. The new Design presents higher efficiency and stall margin without any reduction in the chocking mass flow rate.© 2014 ASME

Jean-yves Trépanier - One of the best experts on this subject based on the ideXlab platform.

  • Multi-Objective and Multi-Point Aerodynamic Optimization of Transonic Fan Blades
    Volume 1: Advances in Aerospace Technology, 2014
    Co-Authors: Maryam Khelghatibana, Jean-yves Trépanier, Christophe Tribes, Jason Nichols
    Abstract:

    A multi-objective and multi-point optimization methodology is developed for aerodynamic Design of transonic fan blades. The optimization method aims to increase Design efficiency, near stall efficiency and stall margin while maintaining the Required Design Pressure ratio and high speed choke margin. Numerical analyses are performed by solving three-dimensional Reynolds-Averaged Navier-Stokes equations combined with shear stress turbulence model. A multi-level blade parameterization is employed to modify the blade geometry. The proposed method is applied to reDesign NASA rotor 67. First, an optimization case with considering two operating conditions at peak efficiency and near stall is performed to demonstrate the relation between near stall efficiency and stall margin. An investigation on Pareto optimal solutions of this optimization shows that the stall margin is increased with improving near stall efficiency. Then, in order to maintain the Required choke margin, an operating point at high speed choked flow is added to the optimization process. A final optimized Design is selected by considering the interaction of Design requirements at all three operating points. The new Design presents higher efficiency and stall margin without any reduction in the chocking mass flow rate.© 2014 ASME

Christophe Tribes - One of the best experts on this subject based on the ideXlab platform.

  • Multi-Objective and Multi-Point Aerodynamic Optimization of Transonic Fan Blades
    Volume 1: Advances in Aerospace Technology, 2014
    Co-Authors: Maryam Khelghatibana, Jean-yves Trépanier, Christophe Tribes, Jason Nichols
    Abstract:

    A multi-objective and multi-point optimization methodology is developed for aerodynamic Design of transonic fan blades. The optimization method aims to increase Design efficiency, near stall efficiency and stall margin while maintaining the Required Design Pressure ratio and high speed choke margin. Numerical analyses are performed by solving three-dimensional Reynolds-Averaged Navier-Stokes equations combined with shear stress turbulence model. A multi-level blade parameterization is employed to modify the blade geometry. The proposed method is applied to reDesign NASA rotor 67. First, an optimization case with considering two operating conditions at peak efficiency and near stall is performed to demonstrate the relation between near stall efficiency and stall margin. An investigation on Pareto optimal solutions of this optimization shows that the stall margin is increased with improving near stall efficiency. Then, in order to maintain the Required choke margin, an operating point at high speed choked flow is added to the optimization process. A final optimized Design is selected by considering the interaction of Design requirements at all three operating points. The new Design presents higher efficiency and stall margin without any reduction in the chocking mass flow rate.© 2014 ASME