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Date of Award

Fall 2008

Document Type

Thesis - Open Access

Degree Name

Master of Science in Aerospace Engineering

Department

Aerospace Engineering

Committee Chair

Dr. Magdy Attia

Committee Member

Dr. Reda Mankbadi

Committee Member

Dr. Eric Perrell

Abstract

The purpose of this thesis was to design and evaluate a three stage counter-rotating compressor that employed well established design principles and technologies using a phased approach. The objective of the first phase was to generate the preliminary annulus shape and estimate the major parameters by modeling the flow as inviscid and time independent. The second and third phases refined the design approximating the flow using Euler's equations and the Navier-Stokes equations respectively.

The performance predictions decreased as the design move forward and more accurate flow and loss models were used. The final three dimensional analysis, which was limited to the individual blade analysis, predicted pressure ratios of 2.26 and 1.60 for the second and third stage rotors at 0.91 and 0.85 adiabatic efficiencies. Stator blade performances were satisfactory while rotor blade performances could have been improved if more suited supersonic airfoil sections would have been employed.

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