Optimized Multidisciplinary Design of a Small Transonic Compressor for Active High-Lift Systems

Abstract

This paper presents the methodology and results of a design optimization of a single stage, axial compressor. At the design point, the compressor achieves a total pressure ratio of 2.33 at a mass-flow rate of 1.11 kg/s. The compressor is part of an electrically powered active high lift system (AHLS) for future civil aircraft. An automated process using numerical models to evaluate aerodynamic performances and mechanical loads due to centrifugal forces is used. This evaluation process is coupled to an evolutionary algorithm to help investigate the design-space. A parameterization strategy was developed to cover a wide design-space, excluding unreasonable designs. The goal was to satisfy the challenging design requirements of high pressure ratio, high power density and limited rotation speed imposed by the AHLS. The resulting design of a highly loaded compressor is characterized by significant end-wall slope and low blade aspect ratios, resembling a mixed flow compressor. According to CFD analysis it is predicted to cover the required operating points at total-total, polytropic efficiencies higher than 80 %.