Date of Award
4-2016
Access Type
Thesis - Open Access
Degree Name
Master of Science in Aerospace Engineering
Department
Graduate Studies
Committee Chair
Dr. Magdy Attia
First Committee Member
Dr. William Engblom
Second Committee Member
Dr. Reda Mankbadi
Abstract
A new vortex solution to the Simple Radial Equilibrium Equation (SREE) is presented that incorporates endwall effects into the preliminary design stage of a single stage, low pressure compressor with a hub-to-tip ratio of 0.4 and non-axial inlet flow. This vortex solution is proposed to overcome the rapidly approaching asymptotic peak in compressor performance in the industry today. The Hybrid Vortex theory incorporates a versatile, higher-order solution to the SREE, resulting in more accurate preliminary designs requiring less manipulation in the final design stages. This new solution results in significant changes in hub geometry with the stagger of the hub changing up to 20°. A numerical study was conducted, evaluating the new Hybrid Vortex method in comparison to the well-known Free Vortex design method. The study revealed the Hybrid Vortex solution not only shows improved flow features at the hub, but has great potential for increasing the surge margin of a compressor. It also demonstrated an 11% increase in the mass flow operational range over that of the baseline blade during off-design conditions.
Scholarly Commons Citation
Port, Daniel, "A Hybrid Vortex Solution for Surge Margin Enhancement in Axial Compressors" (2016). Doctoral Dissertations and Master's Theses. 233.
https://commons.erau.edu/edt/233
