Joury M. Temis, , Denis A. Yakushev

DOI Number: N/A

Conference number: IFASD-2015-188

The paper concerns optimal structural design of blade and disk of compressor for aviation engine. Structural optimization takes into account the shape of blade and disk design. Methodology for optimal design was applied to optimize the shape of the blade by changing the offsets and sizes of the blade section profile. The problem of mismatching minimization of the blade shape in operating position and predefined aerodynamic blade shape and natural frequency retuning is discussed. The estimation of the flutter boundaries is considered for design process. The problem of disk weight minimization with constraints on permissible radial displacement is investigated. Optimization criteria and constraints, parameterization model, design model, design parameters are discussed. All results were obtained using finite element analysis program connected with the sequential quadratic programming (SQP) optimization procedure.

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In Categories: 2. IFASD 2015, Rotation System
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