Abstract. This paper addresses a new approach to aircraft engine parts designing using the topological optimization algorithm for production by additive manufacturing. The full mathematical formulation which includes the problem statement within the elasticity theory and the SIMP optimization procedure is presented. The criterion particularities for evaluation of strength properties of the gas turbine engines parts according to the Aviation Regulations are specified. Optimization of the typical hinge bracket topology is performed, and the stress state of the part with the initial geometry and the optimized geometry is evaluated.
This paper presents the results of software (ANSYS software) improvements specific for modeling the physical process of SLM (Selective Laser Melting). Improvement goal was to create a set of mathematical models and user environment (a set of APDL programs) based on the ANSYS finite element analysis system solver, allowing to perform the technological procedure of physical SLM process numerical modeling to the required degree of precision with an estimate of the final distortion and residual stresses of gas turbine engine parts to optimize the manufacturing process.
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