Introduction and Evaluation of an Aerostructural Coupling Approach for the Design of Shape Adaptive Compressor Blading

Abstract

To improve overall jet engine efficiency for a sustainable and energy-efficient future aviation, shape adaptive compressor blading is researched within the Cluster of Excellence SE2A. Depending on the present operating condition of the jet engine, spanwise blade twist and turning of the compressor rotor are adapted in order to match the varying inflow and flow deflection requirements throughout the flight mission. The design of shape adaptive compressor blading however requires an intensified aerostructural coupling in the early design stages of the compressor design process. To assess feasible deformations due to the actuation and to include structural design restrictions in the aerodynamic design process, structural FEA simulations are conducted and integrated in the design process. This research focuses on the integration process, with special emphasis on the rotor blade modelling as well as the post-processing of the FEA results in order to close the loop to the aerodynamic pre-design. A methodology for the re-engineering of the morphed rotor shapes is presented and applied to selected deformation scenarios. The study is concluded by 3D CFD simulations of re-engineered deformed rotor geometries in order to assess the potential of shape adaptive compressors.