Axial compressor: Design and optimization of a three-stage compressor
Completely parameter based geometry generation
Shock system at the first stage rotor in working point conditions
Assessment of aeroelasticity: flutter stability analysis of rotor geometry
Speedlines in the performance map
Design from scratch and optimization of a three-stage compressor (total pressure ratio 6.2) with two axial and one diagonal stage for small scale turboshaft engines in the 80kW class. Basic thermodynamic considerations and parameter studies are carried out to evaluate different compressor concepts. For the application, a three stage compressor consisting of two axial and one diagonal stage is chosen. This concepts represents a reasonable compromise for the lowest SFC at design and off-design conditions but also requires a sophisticated design process due to the multistage configuration. The design and optimization process is conducted with a combined aerodynamic and mechanical optimization for the compressor stages at multiple operating points. Finally, the chosen blade geometry is assessed concerning the aeroelasticity in a flutter-analysis.