Introduction Of An Improved Axial Compressor Profile Shape Modelling Approach For Increased Flexibility In Transonic Profile Design

<jats:p>With the goal to reduce carbon emissions of future aircraft engines the concept of shape adaptive rotor blading for transonic fan and compressor applications is researched within the Excellence Cluster SE2A. As the aerodynamic design point is shifted by the morphing of the blade shape, the transonic profile design plays a major role in keeping the respective operation point efficiency close to the initial design point efficiency. To increase flexibility and accuracy in transonic profile design, an improved profile modelling approach is presented. To keep the number of modelling parameters to a minimum, a superposition of a generalized parabolic arc camber with a CSM (Class Function / Shape Function) thickness distribution is applied. As the CSM methodology offers an extension of the modelling parameters, the number of parameters is successively increased within this research to enable a better representation of transonic profile shapes. Additionally, the impact of leading edge design and suction side curvature on the blade-shock interaction is explored by specifically manipulating the CSM thickness distribution in the leading edge area. The proposed modelling approach is then applied to a redesign of the tip area of the NASA rotor 67 and evaluated through Q3D RANS simulations in Ansys CFX.</jats:p>