Topological optimization of the axial compressor blade of aircraft gas turbine engine

Maryna Pikul, Kateryna Balalaieva, Anton Balalaiev, Andrii Melchenko

Abstract


The requirements for the efficiency, reliability, and environmental friendliness of technical systems in modern mechanical engineering are constantly increasing. The achievement of high mechanical and functional characteristics with minimal weight is an important task in the development of new engineering designs. The subject of this study is the topological optimization of an aircraft engine’s axial compressor blade. The study focuses on the axial compressor blade of an aircraft gas turbine engine. The study assumed that the blade shape should be simplified, and the blade installation angles, chord, aerodynamic profile, and blade thickness along the entire height did not change. This study aims to minimize the mass of the axial compressor blade of an aircraft engine by topological optimization. Tasks: to perform topological optimization of the compressor blade based on the results of aerodynamic calculations and strength; create a three-dimensional model of the compressor blade considering the results of topological optimization. The study was conducted using a numerical experiment in the Ansys Workbench Student software. When solving the problem, the CFD, FEM, Topology Optimization methods were used. Results: To conduct the study, we simulated streamlining within the first stage and performed strength calculations during the second stage. Topological optimization was performed based on the obtained strength results. Based on the topological optimization results, an updated compressor blade model was built. This study assesses the minimization of the axial compressor blade mass of an aircraft engine by topological optimization. The use of the topological optimization method made it possible to reduce the mass of the compressor blade by 31.4%, while the resulting compressor blade has the required safety margin and the same aerodynamic characteristics as the basic version of the compressor blade. Scientific novelty and practical significance: new data on the possibility of using topological optimization for axial compressor blades The obtained research results can be used in further research on promising gas turbine engine compressors and fans.

Keywords


gas turbine engine; axial compressor; blade; topological optimization; numerical experiment; CFD; mass minimization; RANS

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DOI: https://doi.org/10.32620/aktt.2025.4sup1.16