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 %.
