ABSTRACT
In this chapter, optimization of a baseline axial compressor inspired from NASA Rotor 37 is performed. An in-house optimization code, which utilizes a genetic algorithm is coupled with the throughflow design software AxStream. Aerodynamically optimum geometry is obtained. Rotating and stationary bodies inside the turbo engine create transonic flow with vortices that may cause catastrophic failures, and even the loss of the whole engine. A compressor designer is expected to control such phenomena smartly while delivering requirements such as pressure ratio, mass flow rate and efficiency at a certain point, providing that the component would be able to operate at off-design and extreme conditions. The internal flow inside a turbo engine can be considered one of the most challenging fluid mechanics problems. The governing equation for the fluid motion in a continuum is the Navier-Stokes Equations.
