dc.contributor.advisor |
Peacock, R. E. |
|
dc.contributor.author |
Overli, J. M. |
|
dc.date.accessioned |
2016-08-08T13:51:18Z |
|
dc.date.available |
2016-08-08T13:51:18Z |
|
dc.date.issued |
1974-11 |
|
dc.identifier.uri |
http://dspace.lib.cranfield.ac.uk/handle/1826/10248 |
|
dc.description.abstract |
Recent developments in
have made possible the
mic behaviour of rotor
stage compressor using
I
pressure sensing and transfer techniques
detailed investigation of the aerodyna-
blades. Tests on a low speed single
this instrumentation have given new
evidence on rotor behaviour.
The rotor blade performance with steady inlet flow condition
was assessed from surveys of total pressure, static pressure
and flow direction made upstream and downstreäm of the rotor
hub, mid-height and tip section.
In addition, measurements of the static pressure distributions
of the same blade sections were completed.
It is concluded that the combined effect of centrifugal force
and annulus wall boundary layer skewing aid the performance
of the rotor.
This suggests that the efficiency of compressors would be
improved if they were designed for reactions of rather more
than 50%.
The
presence of a tip shroud has the effect of enhancing the
overall
compressor performance.
A
comparison of compressor rotor and two-dimensional cascade
blade results is given, and predictions of the boundary layer
development and the pressure distribution around the blades
under various flow conditions are also presented.
A series of
experiments were also conducted at the mid-height
section in which the
compressor was subjected to 'sine-wave'
and
'square-wave' circumferential stagnation pressure distortions
including tests with the compressor operating in the
surge regime.
The deteriorating effect of total pressure distortion on overall
compressor performance is clearly demonstrated, and a
critical sector of spoiling is found.
The effect of the level of reduced frequency on the unsteady
normal force response of rotor blades is shown.
II
In all cases of distorted inlet flow,
stallwinception is
dela ed until values of normal force coefficient are reached
well in excess of those encountered at
steady state maximum.
For
'square-wave' type distortion this is ensued by a complex
stall situation with
separation bubbles apparently traversing
the rotor blade section and
promoting dynamic lift patterns
which
pass through secondary and tertiary peaks.
One
may conclude that the aerodynamic rotor behaviour in the
presence of such an unsteady flow environment is not predictable
by current mathematical models.
A theoretical
analysis of the transient flow applicable at
low values of reduced
frequency is given.
The transient
response of the pressure-transmitting system
was examined
thoroughly theoretically, and experimental
frequency response tests were conducted on the rotor blades
as well as on a
subsidiary rig.
Careful examination of the
fluctuating pressure signal was
performed including time and frequency analyses. |
en_UK |
dc.language.iso |
en |
en_UK |
dc.publisher |
Cranfield University |
en_UK |
dc.rights |
© Cranfield University, 1974. All rights reserved. No part of this publication may be reproduced without the written permission of the copyright holder. |
en_UK |
dc.title |
The aerodynamic behaviour of a compressor rotor with steady and unsteady inlet flow |
en_UK |
dc.type |
Thesis or dissertation |
en_UK |
dc.type.qualificationlevel |
Doctoral |
en_UK |
dc.type.qualificationname |
PhD |
en_UK |