Abstract:
This thesis presents a number of new solutions to reduce the
sensitivity of an existing compressor stage to a specified inlet flow
distortion._ The interacting effects of flow vorticity, the change of
rotor incidence and the time rate of change of íncidence are then
studied, yielding a new design criterion to reduce the sensitivity of
a
compressor stage to any circumferential inlet flow maldistribution.
Furthermore, the application of the unsteady thin
a stator or inlet
guide vane and a rotor, results
unsteady fluctuating lift function which contains
.functions as special cases. - Minimisation of the
aerofoil
theory to
inia new
generalised
Sears and Hor1ock's
resultant
fluctuating '
lift leads to a
design criterion for inlet guide vanes in agreement
with the above
conceptwhich is obtained by a different approach.
The thesis also discusses a number of
possible mathematical models
for
Cascade shear flow investígating their advantages and disadvantages
and'the
possibilities°of obtaining solutions. gA
linearised theory for-_
nonuniform cascade flow is presented.i This fs'main1y an extension of
Schlichting's method,`ref;(27) for uniform flow,i
'
The main contribution of this work is the development of a nonlinear
theory for nonuniform~cascade shear flow.â The.theory-accepts
large amplitudes of distortion of any smooth shape, that is, cusps and 'g
sharp corners in the Velocity distribution should be rounded. It is
also
capable of treating cascades of thick and highly cambered blades.
The solution of Poisson's equation is obtained in
the form of Fredholm'sV
integral equation of the second kind which reduces to Martensen's
equations, ref.(29), when the vorticity is zero everywhere in the flow
field (clean flow). .The vorticity transport equation is satisfied in
the flow field and its simultaneous solution with the solution of Poisson
equation is carried out through an iteration process. Good agreement is
obtained between the theoretical predictions and experimental test result
