Optimization design method based on parameter reduction and active subspaces: Redistribution of chordwise loading at blade tips in a transonic axial-flow fan
Physics of Fluids,
Год журнала:
2024,
Номер
36(9)
Опубликована: Сен. 1, 2024
In
practical
optimization
design,
an
excessive
number
of
design
variables
have
a
highly
detrimental
influence
on
the
efficiency
and
accuracy
final
scheme
expose
problem
to
curse
dimensionality.
Therefore,
incorporating
only
most
essential
into
facilitates
obtaining
accurate
cost-efficient
solutions.
Reported
here
is
method
based
parameter
reduction
active
subspaces,
it
used
redistribute
tip
load
in
transonic
fan.
Specifically,
coupled
strategy
developed
reduce
parameters
needed
describe
three-dimensional
blade
shape,
which
leads
far
fewer
being
involved
design.
Moreover,
subspaces
are
perform
sensitivity
analysis
establish
low-dimensional
surrogate
models.
After
represented
effectively
by
three
parameters,
each
has
significant
fan
performance.
Three
one-dimensional
established
for
maximum
mass
flow
rate,
total
pressure
ratio,
efficiency,
linear
models
obtained.
Next,
chordwise
loading
optimized,
after
rotor
at
point
increased
1.1%,
while
ratio
remains
nearly
unchanged.
Finally,
field
analyzed
understand
mechanism
this
performance
improvement,
results
show
that
optimized
reduces
aerodynamic
losses
caused
shock-induced
separation
interaction
between
shocks
leakage
flows.
Язык: Английский
Effect of radial inlet distortion on aerodynamic stability in a high load axial flow compressor
Physics of Fluids,
Год журнала:
2024,
Номер
36(10)
Опубликована: Окт. 1, 2024
Radial
inlet
distortion
induced
by
boundary
layer
separation
can
significantly
affect
the
aerodynamic
performance
of
compressor.
The
effect
radial
on
flow
structure
is
numerically
investigated
in
a
high
load
axial
determined
experimental
results
at
downstream
generator.
reveal
that
tip
leads
to
reduction
stall
margin,
whereas
hub
extends
it.
redistributes
main
toward
undistorted
region
due
obstructive
lattice
ring.
deficit
velocity
with
causes
rotor
operate
higher
incidence
angle
near
casing,
while
alleviates
blade
loading.
detailed
three-dimensional
field
analysis
indicates
increased
loading
shifts
trajectories
both
primary
and
secondary
leakage
leading
edge,
thereby
expanding
blockage
region.
Conversely,
unloads
region,
reducing
flow.
Additionally,
distortion,
location
line
suction
surface
moves
closer
around
trailing
edge
intensified.
Язык: Английский
Design optimization of axial slot casing treatment and blade in an axial compressor based on deep learning and reinforcement learning
Aerospace Science and Technology,
Год журнала:
2025,
Номер
unknown, С. 110209 - 110209
Опубликована: Апрель 1, 2025
Язык: Английский
Experimental investigation of unsteady nature of shock waves induced by various ramps
Physics of Fluids,
Год журнала:
2024,
Номер
36(12)
Опубликована: Дек. 1, 2024
The
ramp
induced
shock
wave
boundary
layer
interaction
(RI-SWBLI)
has
been
investigated
experimentally
at
different
angles
in
a
Ma
=
3
flow.
unsteady
nature
examined
detail
by
using
semi-quantitative
processing
of
Schlieren
images.
shock-wave
locations
are
extracted
to
allow
spectral
analysis
the
oscillations.
Results
show
that
motion
is
associated
with
state
separation,
which
categorized
into
three
classifications
based
on
measurements,
namely,
unseparated,
initially
separated,
and
fully
separated.
statistical
oscillation
illustrates
probability
distribution
function
power
density
(PSD)
along
two
certain
height
follow
almost
same
principles
time–frequency
domain.
PSD
results
significant
variations
lower
location
occur
30°
flow
according
PSD,
characterized
energy,
wide
range,
uniformly
distributed
motion.
reattachment
events
first
rises
24°
With
increase
angle,
axial
position
peak
slowly
transfers
upstream
positions.
Moreover,
conceptual
model
proposed
preliminarily
reveal
RI-SWBLI,
including
scenarios:
In
nonseparating
flows,
mainly
affected
turbulent
shear
ramp.
During
initial
separation
process,
pulsations
bubble.
full
impact
movement
primarily
controlled
newly
designed
aerodynamic
Язык: Английский