Date of Award

12-1995

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Paul I. King, PhD

Abstract

This study focuses on predicting axial compressor stage characteristics using a single performance point comprised of mass flow, temperature and pressure rise coefficients obtained in experimental testing and a generic stage temperature characteristic. A new temperature characteristic is generated using a mapping technique where changes in stage blade angles are iterated from assumptions of free vortex flow and constant increment of flow turning angle with increased flow incidence. If additional data corresponding to the new curve are available, the characteristic is adjusted using non-linear least squares estimation, Essentially, the modified mapped curve results from a re-estimated change in the stator outlet angle which is iterated to minimize the total error between the new curve and the new aggregate of the given data. A pressure characteristic for the single data point may be predicted from the new temperature characteristic and an assumption of constant efficiency. Upon collection of additional data points, an improved pressure characteristic is obtained using an improved model for efficiency. The predicted characteristics agreed well with calibration data in pre-stall regions. For those data near stall, the assumed linear relationship between incidence and flow turning is invalid, and a new model for flow turning is required.

AFIT Designator

AFIT-GAE-ENY-95D-21

DTIC Accession Number

ADA303235

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