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|Title: ||The performance of compressor outlet guide vanes and downstream diffuser|
|Authors: ||Young, Kim F.|
|Issue Date: ||1988|
|Publisher: ||© Kim Frushard Young|
|Abstract: ||A large-scale compressor/diffuser test rig has been designed and constructed which,.
together with an automated data acquisition system, permits more detailed and more accurate
measurements than were previously possible - especially in the region of the compressor
Results are presented based on experiments carried out using two different single-stage
axial-flow compressors operating immediately upstream of a straight-core annular diffuser,
each compressor being tested with a conventional stator row and a double-dihedral chevron
type of stator row i.e. four main configurations were investigated. In addition to these main
tests, the effects of operating the stator row at low Reynolds number, and of operating the
stator row with a small hub clearance have been investigated.
The chevron OGV shows a clear improvement, compared to the straight OGV, in t=s
of diffuser performance and diffuser exit velocity profiles, at the expense of a general
tendency for the OGV loss to increase.
When hub clearance is used on a straight OGV, a hub corner stall arises, but this can be
eliminated by incorporating blade dihedral at the hub.
It seems likely that further improvements in diffuser exit conditions could be achieved by
. careful design of the blade shape to encourage radial movement of flow.
Traversing within the blade passage, for a straight type OGV, has revealed significant
vortices rotating in the opposite sense to classical curved duct secondary flows.|
|Description: ||A Doctoral Thesis. Submitted in partial fulfilment of the requirements for the award of Doctor of Philosophy of Loughborough University.|
|Sponsor: ||Royal Aerospace Establishment, Pyestock,
Farnborough under Contract/Agreement number D/ERl/9/4/2170/110/RAE(P).|
|Appears in Collections:||PhD Theses (Aeronautical and Automotive Engineering) |
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