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Abstract

A broad investigation of the unsteady flow phenomena
which occur in an axial flow compressor is presented. It is
based on an analysis of hot wire measurements of the time variation
in velocity at fixed points in the flow through a single stage
machine with three blade rows. The study has been confined mainly
to the "potential flow" unsteadiness due to the rotor movement and
the effect of wakes from one blade row interacting with downstream
rows. A general experimental investigation of the compressor blade
wakes is included. The results are compared with velocity distributions
calculated from existing potential flow models of the flow
through a cascade, and a new model lased on the approximations of
thin aerofoil theory is developed by the author. Consideration is
given to the development of a model of a blade wake and the author's
potential flow model is extended to include a wake and boundary. layer
thickness effect. Also included is an account of a brief experimental
investigation of the noise generated by the compressor due to
blade row interaction effects.

Item Type:	Thesis - Coursework Master
Authors/Creators:	Boxhall, Peter James
Keywords:	Axial flow compressors
Copyright Holders:	The Author
Copyright Information:	Copyright 1971 the Author - The University is continuing to endeavour to trace the copyright owner(s) and in the meantime this item has been reproduced here in good faith. We would be pleased to hear from the copyright owner(s).
Additional Information:	Thesis (M. Eng. Sc.) - University of Tasmania, 1971. Bibliography: l. 125-126
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