EHTC 2009

Aeroengine's Component Optimization through Mesh Morphing Approach

Paolo Peraudo, Politecnico di Torino, Avio

Generally speaking two approaches are usually used to modify the shape of an aeronautical component, the CAD-centric and the CAE-centric approach. Concerning the first approach, the geometric shape of the part is realized with a CAD tool and meshed with a FEM tool; the next step is the optimization loop, in which the geometric shape is modified to satisfy the objective function. Otherwise, the CAE-centric approach includes a different procedure that is presented in this activity. The aeronautical component considered is a counter-rotating turbine blade, located in the last stage of the low pressure turbine (LPT). The blade is stressed by a pressure field, a centripetal force and by a thermal field. The first step of the analysis was the creation of a mathematical mesh with Hypermesh to verify the internal stress. Then, thanks to the morphing technique, some changes were applied to the shape of the blade: the goal is to determine whether some stiffeners could be reduced in thickness to obtain a lighter structure. Finally an optimization process was managed with Hyperstudy: both the Method of Feasible Directions method and an Adaptative Response Surface Method (ARSM) are compared, then the second one was adopted to reach to desidered goal. A last analysis was conducted to verify the result obtained with the ARSM: the blade was meshed in a finest way and the results confirmed the optimization process.

 

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