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October 2007 edition

Optimisation techniques applied to the design of gas turbine blade cooling systems

By L. Bucchieri, L. Brugali, M.Galbiati, EnginSoft, D. Coutandin, S. Zecchi, Avio S

Background

Multi-objective optimisation techniques were applied to a three dimensional CFD model for the design of the cooling system of a gas turbine blade tip. A parametric CFD model of a high pressure rotor blade was developed in order to study the cooling efficiency in the tip area. The model was integrated in an optimisation software and several different analyses were automatically carried out for different configurations of the system. The application of a multi-objective genetic algorithm and the use of Neural Nets lead to the optimal design with a reduced number of simulations. The comparison between the optimal and the standard configurations gives evidence that the cooling mass flow can be considerably reduced, keeping the same wall heat flux on the blade tip surface.

The parametric CFD model was developed with ANSYS CFX, ANSYS ICEM CFD Hexa and ANSYS ICEM CFD Tetra. For brevity, these are referred to as CFX, Hexa and Tetra respectively, and ICEM is used to denote Hexa and Tetra. These codes were linked and integrated in the optimisation software modeFRONTIER.

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....

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EnginSoft S.p.A. Computer-aided Design, Research/Consulting Services

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