Introduction of a Streamline Curvature Design Methodology for the Vortex Design of Shape Adaptive Compressor Blading

Authors

Marcel Seidler - Institute of Jet Propulsion and Turbomachinery, TU Braunschweig
Kamsan Sivamoorthy - Institute of Jet Propulsion and Turbomachinery, TU Braunschweig
Jens Friedrichs - Institute of Jet Propulsion and Turbomachinery, TU Braunschweig

Abstract

The increasing technological and environmental requirements for aircraft engines present new challenges for modern compressor designs. To improve the overall compressor efficiency, the concept of shape morphing rotor blades is introduced. The application of this concept to the NASA rotor 67 requires an aerodynamic redesign for multiple operating conditions. To cope with this increase in overall design effort, a time optimized C++implementation of a streamline curvature methodology is introduced and applied to optimize the vortex design for two shape adaption scenarios. Within this study, the SLC tool showed good convergence for different swirl velocity distributions and design point operating conditions, while contributing to the resolution of a major conflict between aerodynamic design and structural deformation requirements.