How to Improve the Design of a Mixed-Flow Transonic Compressor for an Active High-Lift System?

Aircraft electrification is one of the most promising trends in tackling global emissions. By using a 3D Inverse Design Methodology, it is now possible to improve the design of a mixed-flow transonic compressor.

Advanced Design Technology presented a paper at the ASME Turbo Expo 2020 that explores the redesign of an electrically driven mixed-flow transonic compressor by using a 3D Inverse Design Methodology. As part of a collaborative work between the Institute of Turbomachinery and Fluid Dynamics of the Leibniz University Hannover and Advanced Design Technology Ltd., an existing optimized compressor stage has been redesigned in this paper using a 3D inverse method.

 

Fig. 1. Prototype design of the electrical compressor system and manufactured compressor stage.

The compressor will be used for an active high-lift system application that aims to delay the onset of stall and thus contributing to the reduction of both the aircraft noise footprint and the impact of aviation emission on local air quality.

The advantage of using an inverse design methodology is shown in this paper as a method that allows a very simple parameterization, reducing significantly the design time and hence allowing the exploration of wider design spaces, with the potential of reaching more innovative and efficient designs. The fast and reliable design and analysis of components represents an important advantage for the enhancement of aircraft electrification, where long design times are often a barrier for the exploration of system configurations.

Fig. 2. Mach number contours at peak efficiency.

A 3D inverse design code, TURBOdesign1, is used to further improve the performance for the mixed flow rotor and stator of a transonic compressor. CFD simulations are previously validated at part-speed and are presented for both, the original and new designs. As was set up as objectives in the beginning of the study, the performance curves of the new compressor stage were shifted to lower mass flow such that the operating points are further from the compressor surge conditions.