Polish Academy of Sciences
Institute of Fluid Flow Machinery
Cooperation between science and aerospace industry
Piotr Doerffer
Transonic flow control by streamwise vortices.
Research offer
1) Start-up of research – EPFL first investigations and patent applic.
2001/3
2) Research at Gdansk
2003/4
3) Inclusion of AJVG into AITEB2 project (coord. RRD), patent applic. 2005/9
4) Inclusion of AJVG into UFAST project (coord. IMP PAN)
2005/9
5) Further research in the FACTOR project
2010/13
6) New concept of RVG, patent applic., research projects
2011/14
14 June 2011 –
Session III (P2)
General Meeting of AERONET
1
Polish Academy of Sciences
Institute of Fluid Flow Machinery
One of very important flow cases
In transonic compressor cascades shock
waves are formed
These shock waves interact with
boundary layers and cause:
-shock induced separation
-unsteady effects of shock-boundary
layer interaction
To limit these negative effects different
flow control methods were tested,
mainly for external aerodynamics
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Session III (P2)
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Reaearch idea from MIT
ALSTOM Project for EPFL Lausanne
Transonic compressor blades are:
- very thin
- strong spanwise variation
14 June 2011 –
Session III (P2)
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Flow control concept – Stream-Wise Vortices (SV)
Methods of SV Generation
Vane Vortex Generators
14 June 2011 –
Session III (P2)
Air Jet Vortex Generators
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Test Model and Measurement
Techniques
EFMC 2003, Toulouse,
Shock Wave – Boundary
Layer Interaction Control
by Stream-Wise Vortices
Piotr Doerffer –
IMP PAN, Gdansk, Poland
Albin Bölcs, Klaus Hubrich EPFL, Lausanne, Switzerland
pressure measurement through
wall taps
 PSP – pressure sensitive paint
 schlieren visualisation of shock
system
 oil visualisation
14 June 2011 –
Session III (P2)
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
ALSTOM Patent
The Patent Application bears
following data:
Our. Ref.:
B03/172-0 DE
Title of invention:
Verfahren zur Verbesserung der
Strömungsverhältnisse in einem
Axialkompressor sowie
Axialkompressor zur
Durchführung des Verfahrens
 = 1 mm
60°
20º
20º
20º
20º
20º
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Session III (P2)
60°
60°
60°
 = 1 mm
 = 1 mm
 = 1 mm
60°
60°
Application No.:
Filing Date:
 = 1 mm
 = 1 mm
 = 0.4 mm
 = 0.4 mm
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103 55 108.5
24.11.2003
Legal Owner/Applicant:
ALSTOM Technology Ltd,
CH-5400 Baden
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Own research at IMP PAN
Pivoted wall
Measurement nozzle
shock wave
Traverse upstream
the shock, 25 mm
Traverses downstream
the shock, 30 and 55
mm
Location
of AJVG
Flat wall
Plate with
the AJVG
Supply cavity
0
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X [mm]
Polish Academy of Sciences
Institute of Fluid Flow Machinery
Experimental
investigations
VG holes
Plate with the
AJVG
14 June 2011 –
Session III (P2)
Mach numbers: 1.25, 1.35, 1.45, 1.55
Static
pressure
holes
Main measurement:
• Static pressure along the wall
• Boundary layers in 3 traverses
• Schlieren pictures
• Oil visualisation
• Oscillations of the shock wave
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Boundary layers 30 mm downstream
u/u_delta = F(y/y_delta), M=1.35
u/u_delta = F(y/y_delta), M=1.45
1.40
1.40
BL for No Jets
BL for Jets
1.00
0.80
0.60
1.00
0.80
0.60
0.40
0.40
0.20
0.20
0.00
0.00
0
0.2
0.4
0.6
BL for No Jets
BL forJets
1.20
y/y_delta
y/y_delta
1.20
0.8
1
0
0.4
0.6
u/u_delta
u/u_delta
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0.2
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0.8
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Shock wave oscillations
Main
shock
Power spectrum, M=1.35, Rear Shock
0.25
No Jets
Jets
Amplitude
0.20
Rear
shock
0.15
0.10
RMS Rear shock
0.05
0.00
0
10
20
30
f [Hz]
14 June 2011 –
Session III (P2)
40
50
60
M
No Jets
Jets
1.35
0.95473
0.79997
1.45
1.13944
1.02838
1.55
2.18671 1.97621
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
AITEB-2
Coordinator RRD
14 June 2011 –
Session III (P2)
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Increased blade load – increased pitch
Geometry:
IGG Mesh:
Chord: 120 mm
208,288 cells (y+ ~1)
Axial Chord: 76.1 mm
Numerical scheme:
Central Difference Scheme: SPARC, FINE
2nd Order Upwind: FLUENT
Turbulence model: Spalart-Almaras
pitch/chord = 1.11
14 June 2011 –
Session III (P2)
Boundary conditions for pitch/chord =1.13:
Inlet:
Outlet:
Total pressure 27983 Pa
Static pressure 15840 Pa
Total temperature 303.3 K
Inlet angle
48.6 deg
Viscosity ratio
10
pitch/chord = 1.13
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Final adjustment of the
shock location and
smoothing of the blade
shape
14 June 2011 –
Session III (P2)
General Meeting of AERONET
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Reference case experimental results
Same shock
location
Maximum Mach number reached
Obtained reduction of M upstream of the shock
Smaller -foot in experiment
14 June 2011 –
Session III (P2)
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Films with reference shock and with cooling and AJVG
Stabilisation of the shock wave
14 June 2011 –
Session III (P2)
General Meeting of AERONET
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Cooling + AJVG
oil visualisation
14 June 2011 –
Session III (P2)
General Meeting of AERONET
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Stagnation pressure
X = 128
X = 171
20
18
16
14
12
10
8
6
4
2
0
0.45
y= f(PP/P0), X=171, Theta=45 alfa=90
reference Shock X=114
Cooling on VG off Shock X=114
Cooling on VG on Shock X=114
y [mm]
y [mm]
y= f(PP/P0), X=128, Theta=45 alfa=90
0.55
0.65
0.75
0.85
0.95
20
18
16
14
12
10
8
6
4
2
0
0.45
reference Shock X=114
Cooling on VG off Shock X=114
Cooling on VG on Shock X=114
0.55
PP/P0
0.65
0.75
PP/P0
Application of cooling increases b.l. thickness considerably
AJVG decreases the effect
14 June 2011 –
Session III (P2)
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0.85
0.95
Polish Academy of Sciences
Institute of Fluid Flow Machinery
Optimisation of AJVG parameters
Objective function: maximum of vorticity X-component
at the section 50mm downstream of the jet
Variables: jet skew angles „alfa”
jet pitch angles „theta”
14 June 2011 –
Session III (P2)
General Meeting of AERONET
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
The invention submission EM 70518 by Rolls-Royce
dated 04th December 2008,
Title: “Method and apparatus to passively control flow separation on
turbine airfoils by means of streamwise vortices generated by air jets”
14 June 2011 –
Session III (P2)
General Meeting of AERONET
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Unsteady effects of shock wave induced
separation
Project starting date: 1st of December, 2005
Project duration:
3,5 years
Coordinated by IMP PAN
14 June 2011 –
Session III (P2)
General Meeting of AERONET
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Interaction types considered in UFAST:
Possibly wide representation of characteristic physical cases
of shock wave boundary layer interaction
Transonic interaction
14 June 2011 –
Session III (P2)
Nozzle flow
Oblique shock reflection
General Meeting of AERONET
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
No.
Participant name
Short name
IMP PAN
1
Institute of Fluid Flow Machinery, Gdansk
PL
2
CNRS Lab. IUSTI, UMR 6595, Marseille
F
IUSTI
3
ONERA:
F
ONERA
4
University of Cambridge, Dept. of Engineering
UK
UCAM-DENG
5
Queens University Belfast, School of Aero. Eng.
UK
QUB
6
Russian Academy of Science, Siberian Branch,
Novosibirsk, Inst. of Theor. App. Mech.
( DAFE, DAAP)
ITAM
RUS
7
Delft University of Technology, Aerodyn. Lab.
NL
TUD
8
INCAS, Romanian Institute for Aeronautics
RO
INCAS
9
University of Southampton, (SES)
UK
SOTON
10
University of Rome "La Sapienza",
I
URMLS
11
University of Liverpool, Dept. of Aero. Engin.
UK
LIV
12
NUMECA, Belgium, SME
B
NUMECA
14
Institute Mécanique des Fluides de Toulouse
F
IMFT
16
FORTH/IACM, Found. for Res. and Techn.-Hellas
GR
FORTH
17
Ecole Centrale de Lyon
F
LMFA
19
EADS-M, Deutschland GmbH Military Aircraft
D
EADS-M
20
Institute of Aviation, Warsaw
PL
IoA
14 June 2011 –
Session III (P2)
New partner
Ukraine
CFD
General Meeting of AERONET
Large tunnels
SME
IND
Large tunnels
22
Polish Academy of Sciences
Institute of Fluid Flow Machinery
Observer Group
Observer Name
14 June 2011 –
Session III (P2)
1
Rolls-Royce Germany, RRD
2
Dassault Aviation
3
Alenia
4
Ansys Germany GmbH
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
Transonic interaction
Channel flow
Shock reflection
PM=638
14 June 2011 –
Session III (P2)
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
ALTERNATIVE SOLUTION TO AJVG
Rod Vortex Generator
STREAMWISE VORTICITY CONTOURS
MEMS – sub-layer device ~ δ1
14 June 2011 –
Session III (P2)
General Meeting of AERONET
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
FACTOR
2010 - 2013
Full Aero-thermal Combustor-Turbine interactiOn Research
Zastosowanie AJVG w
gorącym środowisku
14 June 2011 –
Session III (P2)
General Meeting of AERONET
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
New project topic:
Laminar – turbulent transition effects
on unsteady behaviour
of shock wave induced separation
UFAST  TUFAST  SWIFT?
Przemysł: Dassault Aviation, Rolls-Royce Germany,
AVIO, AIRBUS
14 June 2011 –
Session III (P2)
General Meeting of AERONET
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Polish Academy of Sciences
Institute of Fluid Flow Machinery
THE PEOPLE PROGRAMME – Marie-Curie
Industry-Academia Partnerships and Pathways
STA-DY-WI-CO (LMS Belgium - IMP PAN Poland)
STAtic and DYnamic piezo-driven StreamWIse vortex
generators for active flow Control
Initial Training Networks
IMESCON
Innovative MEthods of Separated Flow CONtrol in Aeronautics
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