Date of Award

Spring 5-2019

Access Type

Thesis - Open Access

Degree Name

Master of Science in Aerospace Engineering

Department

Aerospace Engineering

Committee Chair

Magdy Attia

First Committee Member

R.R. Mankbadi

Second Committee Member

Mark Ricklick

Abstract

A hybrid vortex solution using the radial equilibrium equation for three dimensional design in axial compressors is generated. One of the most common used vortex solutions is Free Vortex. However, it ignores the fact that axial velocity varies with radius. The Hybrid Vortex includes axial velocity distribution with radius, which gives a more effective design. A single stage is first designed using the Free Vortex design method. A low hub-to-tip ratio is set to ensure subsonic flow. The axial velocity profile is exported from the CFX solver of the inlet diffuser. Using the Hybrid Vortex solution to the radial equilibrium equation, a redesign is conducted by altering the circumferential velocity distribution to adhere to the imported axial velocity distribution and the newly derived method. A tip-strong pressure distribution is also used in new design to adjust loading on the blade. CFX simulations are generated after 1D design, meanline design, throughflow design and blade design.

One of the key factors to evaluate compressor operation is off-design performance, which can be represented by the compressor map. Compressor maps are also generated and compared for each blade to show the advantage of the new design approach. It can be said that, by introducing real axial velocity profiles, complete with 3D effects, into the early stages of design and incorporating it with the new vortex solution, this new design approach delivers airfoils that are better aligned to the real boundary conditions with enhanced surge and stability margins, which is verified by CFD results.

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