Steady fluid flow investigation using piv in a multi-pass
coolant channel
Dr.-Ing. Marc P. JARIUS
German Aerospace Center
Dipl.-Ing. Martin ELFERT
German Aerospace Center
Institute of Propulsion Technology
Institute of Propulsion Technology
Linder Höhe, D -51147 Köln, Germany
Fax Number: +49 2203 64395
Linder Höhe, D-51147 Köln, Germany
Fax Number: +49 2203 64395
E-mail address: marc.jarius@dlr.de
E-mail address: martin.elfert@dlr.de
KEY WORDS: MULTI-PASS COOLANT CHANNEL, PARTICLE IMAGE VELOCIMETRY, LASER-2FOCUS VELOCIMETRY.
ABSTRACT
In a stationary two -pass coolant channel system the fluid flow is investigated experimentally. One of the main objectives of this paper is to describe the capability of the measuring technique Particle-Image Velocimetry (PIV). Results of heat exchange and pressure losses are not the objectives of this paper. The investigated system has an enginenear lay-out with an 180° turn and has smooth walls in the beginning of this project, later on ribbed walls will be
investigated. As a first step, the system is analyzed in non-rotating mode. During future work it will rotate about an
axis orthogonal to the center-line of the straight passes. The results shown in this paper demonstrate the effect of the
180° bend with isothermal flow condition excluding any buoyancy. Turbulent channel flow with a REYNOLDS number
of 25.000 and 50.000, derived with the hydraulic diameter of the first pass, was investigated.
At the test rig at DLR several test models were mounted to investigate pressure drop behavior and fluid motion
separately. Numerical investigations regarding flow structure and pressure drop have been carried out in order to validate a CFD code against the experimental data. The numerical solution is compared with streamline pictures, obtained
from flow visualization of all walls using oil flow technique, and near wall PIV results. Mid-span flow distribution is
received from laser light sheet visualization technique with oil fog as indicator and also from PIV. Figure 1 shows a
comparison of the measured mean flow velocity distribution at mid-span (cut 1 & camera position 1) with and without
turning vane.
The results presented in this paper clarify the complex flow situation given by the two pass system with inherent
turn. Especially in the bend region appear separation regions and vortices with high local turbulence. These very demanding measuring task represents a benchmark test case for the used measuring techniques.
245
245
240
240
235
230
230
z in mm
z in mm
235
225
220
225
220
215
215
210
210
205
Figure 1. Comparison of the mean flow velocity distribution at mid-span (cut 1 & camera position 1) with and without turning vane
1
1
INTRODUCTION
The power generation industry and the aero-engine industry operate in a highly competitive market. Major objec tives are high requirements in terms of high technology development as well as cost and development time reduction.
On the other hand, environmental and safety constraints are an increasingly stringent necessity, which enforces the
demand for new technologies. Currently the industry relies on expensive and time consuming rig test programs,
whereas the existing numerical design tools have a number of deficiencies in accurately describing the complex multipass coolant channel flow. Under these conditions the Institute of Propulsion Technology is involved in national and
European research programs aimed to providing the industry with high quality experimental data from the flow field
for CFD validation.
In past projects the flow behavior in rotating passages was analyzed at DLR. Laser-2-Focus velocimetry (L2F)
was used to obtain flow velocity components and fluctuations. Although time-consuming, this non-intrusive, singlepoint measurement technique worked very well within straight and smooth duct flows, which generally have a moderate degree of turbulence. However, state of the art, serpentine shaped, multi-pass systems are equipped with ribbed
walls, in order to improve heat exchange which is typical in realistic configurations. In this case L2F velocimetry was
not able to measure accurate flow properties due to the increased turbulence intensities in the vicinity of the ribs as in
the bend region and further downstream. The dividing wall separating the two passages forces the flow into a sharp
turn which generally results in a flow separation. The flow within the separation bubble itself is very unsteady.
An important work package within these research programs is to provide detailed information of the flow field in side the multi-pass coolant channel using planar techniques such as Particle Image Velocimetry (PIV) [ADRIAN , 1991,
WILLERT , GHARIB, 1991, RAFFEL et al, 1998] or Planar Doppler Velocimetry (PDV) [RÖHLE, 2000]. Modern planar
measurement techniques such as PIV are capable of obtaining complete maps of flows even at high turbulence. As a
first step toward applying this technique, a multi-pass cooling system with and without turning vane is investigated in
stationary (e.g. non-rotating) mode using two -component PIV. The results are compared with results from L2F (multipass cooling system with turning vane), flow visualization and CFD. The high quality of the obtained new results
encourage the application of two-component PIV to the rotating system. As a logical consequence, the application of
three-component PIV will be necessary to obtain the complete flow field information within the complex flow passages. This paper’s intention is to report on the status of applicability of PIV in a multi-pass coolant channel.
2
dh
f
f#
ν
n
Re
τ
v
v0
x, y, z
NOMENCLATURE
m
mm
m²/s
rpm
µs
m/s
m/s
mm
Hydraulic diameter
Lens focal length
Lens f-number
Kinematic viscosity
Speed
REYNOLDS number, Re=ρv0 d/η
Pulse delay
Volumetric absolute velocity
Intake velocity
CARTESIAN co-ordinates
Abbreviations
p.s.
pressure side
s.s.
suction side
t.e.
trailing edge
t.v.
turning vane
2
3
TEST FACILITY AND INSTRUMENTATION
3.1.
Test Facility
A large-scale coolant multi-pass system rotating spanwise was investigated during the past experiments. Air is
supplied in the rig through a rotary sealing assembly, a second one is used for venting after the air has passed through
the test section. Both are mounted to the end of the double hollow shaft. A schematic of the test rig is given in Figure 2. More detailed information about the test facility are presented in [RATHJEN et al, 1999]. Re ynolds number and
rotation number can be adjusted appropriately to the models inserted. For the PIV investigations a non-rotating test rig
is installed at a laboratory and shown in Figure 3.
3.2.
Test Model Geometry
Figure 4 shows a schematic draw of the coolant multi-pass -model with turning vane. The test section consists of a
leading edge duct (first pass) with a trapezoidal cross-section extending radially outward, a 180° bend with a 90°
turning vane and a second pass with a different trapezoidal cross-section extending radially inward. The ratio between
the hydraulic diameter of the second pass and the hydraulic diameter of the first pass is 1.5. The length of each pass is
9.975 dh, where dh denotes the hydraulic diameter of the first passage. In the bend region the flow is not only directed
through the 180° u-bend but also perpendicular to that following the turbine airfoil shape. The test section is 12 dh
long. The distance between the tip plate and the divider wall is about 1.875 dh . The divider wall has a thickness of 0.3
d h. The model has a small plenum chamber and an inlet and outlet length, both are 3 d h long.
A schematic draw of a second cooling multi-pass-model without turning vane and with a modified second pass is
shown in Figure 5. The length of the wall 1* is reduced to 1.3 d h , the angle is reduced to 8° and the wall 1* is now
parallel to 3*. The length of each pass is increased to 10.65 d h and consequently the distance between the tip plate and
the divider wall is reduced to 1.2 dh . A CAD-picture of the model geometry without turning vane is presented in Figure 6.
3.3.
Measuring Techniques
3.3.1.
PIV – Particle Image Velocimetry (Flow)
The flow field is measured first in steady mode by means of PIV. This modern technique is a scientific tool for
qualitative and quantitative investigations of flow fields. The principle of the PIV with laser, light sheet optic, laser
light sheet and test section is shown in Figure 7 and the existing test set-up in the laboratory is shown in Figure 2.
PIV is based on the principle to capture the image of the flow field two times (pulse delay in the range of 5 µs). Tracer
particles (aerosol) with an average size of 0.1 µm are added to the flow. These particles reflect in the laser light sheet,
which is formed with a light sheet optic consisting of a system of one spherical and two cylindrical lenses. It generates
a light sheet with a thickness of 1 mm and a divergent angle of 24°. The laser light sheet is adjustable and visualizes
the first pass as well as the second pass, due to a mirror. Illumination was provided by a standard, frequency-doubled,
double-cavity Nd:YAG laser (NewWave, Gemini PIV) with a pulse energy of up to 120 mJ per pulse at 532 nm. On
the recording side, a thermo -electrically cooled, interline transfer CCD camera (PCO, 1280 x 1024 pixel resolution)
with a f = 55 mm, f# 2.8 lens (Nikon) was used. A bandpass filter with center frequency 532 nm and width 5 nm
(FWHM) placed in front of the lens rejected most of the unwanted radiation. The pulse delay between the laser pulses
varied between τ = 6 µs (investigation of mean flow) and τ = 12 µs (investigation of secondary flow). The high resolution CCD 1 camera takes two pictures, depending on the pulsing laser. Each picture has a size of 2.5 MB. The CCD
camera, perpendicularly positioned to the light sheet, is a so-called cross correlation camera having double-frame
single-exposure evaluation. Now it is possible to calculate the value, direction and orientation of the absolute velocities with the Cross Correlation Function (CCF). 50 pictures at each camera position are taken to calculate the mean
value of the absolute velocity. For the secondary flow investigations (cut 1...6) into the first pass from the multi-pass
coolant channel one camera positions is adjusted (Figure 8a) and for the investigations of the mean flow (cut 1 & 2)
into the second pass of the multi-pass coolant channel five camera positions are necessary (Figure 8 b).
1
Charge Coupled Device
3
3.3.2.
OFV – Oil Flow Visualization (Wall Flow)
To analyze the flow phenomena, several kinds of flow visualization techniques have been applied. Using the oil
flow visualization method, wall streamline patterns could be achieved within the duct. It is possible to show and localize the boundary layer separation, the reverse flow and vortex regions next to the surfaces. To some extent it is poss ible to draw conclusions from the two-dimensional method for application to the strongly three-dimensional character
of the flow field. The duct wall has been previously painted with a mixture consisting of oil of appropriate viscosity,
oil acid and Titanium dioxide (TiO2 ) for contrast purpose. Then it has been exposed to the flow for a time period
(approx. 10 minutes) long enough to dry the oil paint. The duct is dividable in two halves and is opened after the test
run for viewing. A detailed description of the range of application is given in [MALTBY , KEATING, 1962].
3.3.3.
L2F – Laser-Two-Focus Velocimetry (Flow)
For the non -intrusive measurement of flow velocities, angles and fluctuations inside the rotating duct the Laser-2Focus (L2F) technique [BEVERSDORFF, HEIN , SCHODL, 1992] has been applied using a newly developed optical unit
to direct the laser beams into the rotating frame of reference. The optical device mounted in front of the rotor enables
the system to stationary non-triggered signal processing. Following the beam path from the laser to the probe volume,
the laser light is emitted by an Ar+ ion laser of 4 Watt power output which is connected to the launching unit mounted
to the test rig by an optical fiber for vibration decoupling purpose. The L2F method is based on time of flight measurements of co-flowing particles. Small oil droplets with a size less than 0.5 µm were added to the flow before entering the shaft. The flow-following behavior of these particles even at high accelerations has been successfully demonstrated and thereby a correlation between particle and flow velocity is assured [SCHODL , 1977].
3.3.4. LLSV – Laser-Light-Sheet Visualization (Flow)
To obtain more information about the flow around the turning vane and the separation zone, a camera system has
been installed to the Perspex duct observing inside the second pass with the mid plane lighted with a laser light sheet.
In order to visualize the flow structures, seeding of the flow with oil steam is provided by an oil fog generator. With
frame grabbing on a PC the video pictures were captured. The digitized pictures have been improved with regard to
luminance and brightness.
4 RESULTS
In the following, some exemplary experimental results are presented. All results are presented in the form of isolines and vectors. For a better understanding of the isolines, red areas represent high velocities, blue areas represent
areas with lower velocities. The shown vectors all have a uniform size to represent only the orientation of the flow
field. With regard to PIV processing, standard cross correlation algorithms were used with an interrogation window
size of 32 x 32 pixel and a 50 % overlap. The velocity of the intake flow into the first pass amounts to v0 = 15.25 m/s,
and consequently the REYNOLDS number is about 25.000 for the PIV measurements.
The comparison of the axial velocity component at cut 1 and 2 between L2F and PIV measurement in the second
pass at the position z = 193 mm is presented in Figure 9. The axial velocity component at the z-position is extracted
off the measured PIV results. For the case with t.v. the results shows relatively good agreement with the L2F results.
The position of the jet and the wake is slightly different, which depends on deviations in model manufacturing. Measurements in the region of the separation bubble were not possible with the L2F system due to too high turbulence. For
the case without t.v. the flow separation on the dividing wall is much larger then with t.v. and the value of the axial
velocity component inside the bubble is even higher. By means of the thickness of the separation bubble, the open
cross section is contracted, due to that fact the value of the axial velocity component is increased. At mid-span the
axial velocity component is smaller and the separation region is nearly not remarkable.
The measured flow field of the secondary flow within the first pass in six cuts (z = 190...240 mm, step size
10 mm) for a REYNOLDS number of 25.000 are shown in Figure 10. At a distance of 190 mm from the duct entry
(Figure 10a, cut 1) a relatively big and strong vortex occurs (x = 16.0 mm, y = 13.0 mm). A smaller vortex exists at
the channel too (x = 8.0 mm, y = 5.0 mm). An interpretation of that phenomenon is, that the flow is disturbed due to
the inlet distortions, which are still visible at this position. The same result was found during CFD simulation where
the complete inlet geometry with settling chamber was modeled (Figure 15) at cut 1. The mean value of the secondary flow velocity is in the range of about 1 m/s. At the position of cut 2 (Figure 10b, z = 200 mm) the big vortex
4
moved closer to the side wall (x = 17.5 mm, y = 11.0 mm) and the smaller vortex is already disappearing. The mean
value of the secondary flow velocity is in the same range like before. If the position of the light sheet is varied to the
positions of cut 3, 4, 5 and 6 (Figure 10c, d, e and f) all vortices are disappeared. The mean value of the secondary
flow velocity is increasing more and more from cut to cut and is finally reaching a value of 13 m/s at cut 6 (Figure 10f) and is becoming now the main stream velocity component due to the flow turning process. At cut 6 at the
leading edge the beginning of the recirculation from the upper passage corner can be observed.
Within the second pass with turning vane the measured flow field of the main flow in two cuts 2 mm (right, wall
section) and 10 mm (left, mid-span) for a REYNOLDS number of 25.000 are shown in Figure 11. At the mid-span
section (left) a relative stationary separation bubble occurs at the upper surface (s.s.) of the t.v.. Behind the separation
bubble exists a relative high flow deviation with high velocities about 24 m/s close to the wall. An other separation
bubble with reverse flow is visible on the dividing wall. Due to that flow recirculation a jet flow with velocities about
24 m/s exists on the pressure side at the t.e. of the t.v.. The thickness of the separation bubble is decreasing in downstream direction. The form and extension of the separation bubble with a length of approximately 5 dh is similar to
those found by visualization (Figure 16a). The areas of high velocity are coinciding further downstream
(z = 190 mm) where mixing of both jets leads to an uniform velocity profile. The mean value of the main flow velocity further downstream is in the range of about 13...16 m/s. At the wall section (right) the mean value of the velocity is
increased to 25 m/s on the upper side of the t.v.. Turning of the flow leads to an impingement effect to the leading
wall of the second leg due to the inclination of the center-lines of both cross-sections. The separation bubble on the
dividing wall is much larger in longitudinal extension than before. At the s.s. of the t.v. appears a boundary layer separation (x = 20 mm, z = 215...220 mm) due to side wall effects. The jet flow at the pressure side of the t.v. is still existing. But the mean value of the main flow velocity distribution is decelerated further downstream to a range of about
8...10 m/s.
The measured flow field of the main flow within the second pass without turning vane in two cuts 2 mm (right,
wall section) and 10 mm (left, mid -span) for a REYNOLDS number of 25.000 are shown in Figure 12. At the mid-span
section (left) a separation bubble with reverse flow is visible on the dividing wall. The thickness of the separation
bubble is decreasing more and more in downstream direction. The form and extension of the separation bubble with a
length of approximately 2d h is similar to those found by vis ualization (Figure 1 6 b). At the top of the duct exists a
relative high flow deviation with the highest velocities with a value of over 24 m/s. This area of high velocity
(> 24 m/s) reaches up to z = 150 mm downstream. At the wall section (right) the area with high velocity over 24 m/s
is increased and the extension of the separation zone at the dividing wall is larger as at the other cases.
The streamline patterns on the pressure side (Figure 13) and the suction side (Figure 14) obtained from oil flow
visualization experiments for both cases, with and w/o turning vane are compared with a numerical solution inclusive
t.v. close to the wall. The streamlines on both walls show the combined effect of the 180° turn, the influence of the
turning vane and clearly the extension and thickness of the separation bubble at the top of the dividing wall in the
second channel. The main phenomena in this engine-near configuration are: (i) The separation bubble at the dividing
wall is larger at the pressure side than at the opposite wall. (ii) The deflection of the flow within the bend due to an
inclination of the orientation axis of the two passes forms a strong secondary motion after the bend running from the
concave wall (p.s.) around the rear wall to the s.s. of the 2nd pass. (iii) The bend induces a counter-rotating pair of
secondary vortices, These are affected by the secondary motion described above. The vortex along the p.s. has an
adverse orientation and is strongly weakened whereas the other along the s.s. is enlarg ed recognizable at the slope of
streamlines against the pass axis. The saddle lines between both vortices were expected normally at the center of the
side walls in a rectangular U-turn. In this case of an inclined-oriented two-pass system the saddle lines were shifted to
the p.s. and to the corner of the rear side, respectively. After the separation bubble at the top of the divider wall, almost cross-oriented streamlines are visible over a curtain area at the pressure side confirming the dominance of the coflowing secondary vortices of (ii) and (iii). Both vortex generation mechanisms depend on inertia effects in viscous
flows.
A comparison of a calculated result (Figure 15a) and measured results with PIV with t.v. (Figure 1 5 b) and without
t.v. (Figure 15c) is presented. The relatively big vortex close to the dividing wall is visible in all results, but the position of this vortex is a little different for the case without t.v.. The core of the vortex is centred more into the middle of
the channel and the o rientation is changed.
5
Two captures of the flow around the bend with and without t.v. obtained by laser-light-sheet visualization is
shown in Figure 16a & b. This technique confirms the already recognized and already described flow phenomena.
5 SUMMARY
This paper describes experimental investigations of a typical two -pass cooling channel system of a turbine blade
with respect to fluid flow phenomena affected by geometry effects and flow turning. A complex flow situation is
present showing several kind of separation and vortices:
(i)
At the upper surface of the t.v. due to a to high angle of attack versus the incoming flow,
(ii)
further downstream at the s.s. of the t.v. due to too strong curvature,
(iii)
at the dividing wall due to the sharp edge where the flow is incapable to follow.
The jet region under the t.v. and the wake from the t.v. are leading to high velocity gradients and corresponding
high shear stresses at the contact layer producing very high turbulence levels there. Higher turbulence levels than
30 % leads to uncertainties in L2F results. With supposed levels of 50 % and more the PIV technique has no difficulties. But in order to give an accurate value of the turbulence level by PIV, you will need about 2000 pictures or more.
This relatively big amount of data demand high storage capacities.
The performed flow visualization and simulation are very helpful in that case to understand the interaction of all
apparent effects. The presented experiments were mainly intended to assess the feasibility of applying PIV in a multipass cooling channel used for applied cooling research. The results have shown that it is possible to apply PIV in a
multi-pass cooling channel. The application of PIV is approved and will be adopted to the rotating system in the near
future. As a logical consequence, the application of three-component PIV will be necessary to obtain the complete
flow field information within the complex flow passages.
6 REFERENCES
ADRIAN, R. J., 1991, Particle -Imaging Techniques for Experimental Fluid Mechanics, Annual Review of Fluid Mechanics 23.
B EVERSDORFF , M., HEIN, O., SCHODL , R., 1992, An L2F-Measurement Device with Image Rotator Prism for Flow
Velocity Analysis in Rotating Coolant Channels. 80th Symp. On Heat Transfer and Cooling in Gas Turbines,
AGARD PEP, Antalya, Turkey.
ELFERT, M., HOEVEL , H., TOWFIGHI, K., 1996, The Influence of Rotation and Buoyancy on Radially Inward and
Outward Directed Flow in a Rotating Circular Coolant Channel, Proc. 20th ICAS Conference, Sorrento, Italy, 24902500
MALTB Y, R. L., KEATING, R. F. A., 1962, The Surface Oil Flow Technique for Use in Low Speed Wind Tunnels,
AGARDograph 70.
RATHJEN , L., HENNECKE, D.K., ELFERT, M., BO C K, S., HENRICH, E., 1999, Investigation of Fluid Flow, Heat
Transfer and Pressure loss in a Rotating Multi-Pass Coolant Channel with an Engine Near Geometry, ISABEConference, Florence, ISABE- IS-216
RAFFEL, M., WILLERT, C., KOMPENHANS , J., 1998, Particle Image Velocimetry, Springer Verlag Berlin Heidelberg.
RÖHLE I. 2000, “Doppler global velocimetry”, in RTO Lecture Series 217, Planar Optical Measurement Methods for
Gas Turbine Components, Neuilly-Sur-Seine Cedex, France.
SCHODL, R., 1977, Entwicklung des Laser-Zwei-Focus-Verfahrens für die berührungslose Messung der
Strömungsvektoren, Dissertation, Tech. Univ. Aachen, Germany.
WILLERT, C., GHARIB , M., 1991, Digital Particle Image Velocimetry, Experiments in Fluids, No.10, Springer Verlag.
6
7
Figures
Ligh t sheet opti c
Acrylic mo del
La ser
CCD-camera
Fl o w mete r
Figure 3. Test set-up for stationary PIV-measurements
1.2 dh
1.875dh
Figure 2. Schematics of the test rig at DLR-Cologne
0.15dh
0.15 dh
0.12dh
1 .125dh
x /d h = 12.975
Leading wall
1.5 dh
2
10°
3
1.0dh
4
30°
35°
10.65 d h
4∗
0.3dh
2∗
12 d h
20°
35°
9.975dh
12dh
20°
2∗
1.0dh
x /d h = 22.95
axis of rotation
30°
25°
dh = hydraulic diameter of the first pass
x /d h = 22.95
x /d h = 0
Trailing wall
Inlet
Outlet
3 dh
3d h
1.3dh
1
4
axis of rotation
dh = hydraulic diameter of the first pass
Inlet
1∗
8°
1
25°
x /d h = 0
4∗
0.3dh
2
3
0.3dh
Outlet
0.3dh
Figure 4. Schematic of test model geometry with turning Figure 5. Schematic of test model geometry without
vane
turning vane
Mirror
Light sheet optic
Laser
Laser light sheet
Tracer particle into light sheet
Particle image from
first light pulse at t 0
Imaging optic
Image plane
Flow direction
Particle image from
second light pulse at t1
Figure 6. Test model geometry without turning vane
Figure 7. Principle of Particle -Image Velocimetry
7
a
b
Figure 8. Camera and cut positions. a. Secondary flow investigations into first pass (cut 1...6); b. Mean flow investigation into second pass (cut 1 & 2)
a
b
30
30
25
Wallsection, PIV without tv
Wall section, PIV with tv
Wall section, L2F
Wall section, L2F, cor r.
25
20
v in m/s
v in m/s
20
15
L2F
PIV
0
10
15
P IV
10
10
5
L2F
Region of
Backflow
Mid- span,
Mid- span,
Mid- span,
Mid- span,
5
15
20
x in mm
25
0
10
30
15
20
x in mm
25
PI V without tv
PI V with tv
L2F
L2F, corr.
30
Figure 9. Comparison of the axia l velocity component between L2F and PIV measurement in the second pass at the
position z = 193 mm. a cut 1; b cut 2; (according Figure 8b)
8
a
mm
CCut
u t 2,
2 , zz==200
200
mm
30
25
25
20
20
yz in mm
yz in mm
b
Cut 1,
1, z == 190
Cut
190mm
mm
30
15
15
10
10
5
5
0
0
0
5
10
15
20
25
0
5
x in mm
c
25
20
20
15
15
10
10
5
5
0
5
10
15
20
0
25
5
f
Cut
Cut 5,
5, z == 230
230mm
mm
30
10
15
20
25
x in mm
x in mm
mm
CCut
u t 6,
6 , zz==240
240
mm
30
25
25
20
20
yz in mm
yz in mm
25
CCut
u t 44,, zz==220
2 2 0mm
mm
30
25
0
15
15
10
10
5
5
0
0
5
10
15
20
0
25
0
x in mm
Figure 10.
20
yz in mm
yz in mm
d
0
e
15
x in mm
Cut 3,
mm
Cut
3, zz==210
210
mm
30
10
5
10
15
20
25
x in mm
Secondary flow velocity distribution in six cross cuts of the first pass measured with PIV (Re = 25.000)
9
v in m/s:
2
4
6
8
10
12 1 4 16
18
20 2 2 24
v in m/s:
Pos 1
245
4
6
8
10
12 1 4 16
18
20 2 2 24
235
Wall section
y = 2 mm
z in mm
240
235
230
230
225
225
220
220
215
215
210
210
205
Pos 2
205
200
200
195
195
190
190
185
185
180
180
175
175
170
170
Pos 3
165
165
160
160
155
155
150
150
145
145
140
140
135
135
130
130
Pos 4
125
125
120
120
115
115
110
110
105
105
100
100
95
95
90
90
Pos 5
85
85
80
80
75
75
70
70
65
65
60
60
55
55
50
50
5
10
15
20
25
30
35
5
x in mm
Figure 11.
2
245
240
z in mm
Mid-span
y = 10 mm
10
15
20
25
30
35
x in mm
Mean flow velocity distribution in two longitudinal cuts of the second pass with turning vane measured
with PIV (Re = 25.000)
10
Mid-span
y = 10 mm
2
4
6
8
1 0 1 2 1 4 16
18
20 2 2 2 4
Pos 1
245
245
240
240
235
235
230
230
225
220
215
210
205
205
Pos 2
6
8
10
12
14 1 6 1 8 20
22 2 4
Wall section
y = 2 mm
200
195
190
190
185
185
180
180
175
175
170
170
165
165
160
160
155
4
220
210
195
2
225
215
200
155
Pos 3
150
150
145
145
140
140
135
135
130
130
125
125
120
120
115
115
110
110
105
105
100
Pos 4
95
100
95
90
90
85
85
80
80
75
75
70
70
65
65
65
60
60
55
Pos 5
50
45
55
50
45
40
40
35
35
30
30
25
25
20
20
5
Figure 12.
v in m/ s: 0
z in mm
z in mm
v i n m/ s: 0
10
15
20
x in mm
25
30
35
5
10
15
20
x in mm
25
30
35
Mean flow velocity distribution in two longitudinal cuts of the second pass without turning vane measured with PIV (Re = 25.000)
11
Suction side
Figure 13.
Comparison between calculated and visualized wall velocities and streamlines on suction side, non rotating (Re = 50.000)
12
Pressure side
Figure 14.
Comparison between calculated and visualized wall velocities and streamlines on pressure side, nonrotating (Re = 50.000)
13
a
Figure 15.
b
c
Comparison of calculated and measured results. a Numerical simulation at cut 1 in first pass; b Measured at
cut 1 in first pass with turning vane; c Measured at cut 1 in first pass without turning vane
a
Figure 16.
b
Pattern of laser light sheet visualization at the bend region. a With turning vane; b Without turning vane
14