关键词: 气动优化, 流体拓扑优化, 空间拓扑, 发动机叶片, 可压缩流动

Abstract: Aerodynamic optimization of compressor and turbine components is essential for enhancing aero-engine performance. While conventional shape-based optimization offers limited improvements, topology optimization explores the entire design space to identify optimal aerodynamic layouts beyond predefined geometries. This work presents two advanced topology optimization frameworks for blade design. First, a density-based approach incorporating compressible turbulent flow physics, with variables defined over the design domain, a discrete adjoint method enables efficient sensitivity analysis, yielding physically consistent configurations from subsonic to supersonic conditions, this method applied to turbine blades and tip clearance regions demonstrates notable efficiency gains. Second, a shape–topology parameterization method is introduced, building on the concept of “aerodynamic elements + topological factors.” Using blade profiles as foundational elements, the approach parameterizes both geometric and topological variables, avoiding the ambiguous fluid–solid interfaces and adjoint convergence issues of density-based methods. Optimized compressor cascades designed with this method exhibit reduced total pressure loss. This study broadens the paradigm for aerodynamic design for blades, offering new pathways toward high-performance next-generation aero-engines.

Key words: aerodynamic optimization, fluid topology optimization, spatial topology, aero-engine blades, compressible flow