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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