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114 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Piotr Doerffer
Transonic flow control by streamwise vortices. Research offer
Cooperation between science and aerospace industry
1) Start-up of research – EPFL first investigations and patent applic.
2) Research at Gdansk
3) Inclusion of AJVG into AITEB2 project (coord. RRD), patent applic.
4) Inclusion of AJVG into UFAST project (coord. IMP PAN)
5) Further research in the FACTOR project
6) New concept of RVG, patent applic., research projects
2001/3
2003/4
2005/9
2005/9
2010/13
2011/14
214 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute 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
314 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Reaearch idea from MIT ALSTOM Project for EPFL Lausanne
Transonic compressor blades are:
- very thin
- strong spanwise variation
414 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Flow control concept – Stream-Wise Vortices (SV)
Methods of SV Generation
Vane Vortex Generators Air Jet Vortex Generators
514 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Test Model and Measurement Techniques
pressure measurement through wall taps
PSP – pressure sensitive paint schlieren visualisation of shock
system oil visualisation
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
614 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
20º 20º 20º 20º 20º
60° 60° 60° 60° 60° 60°
= 1 mm = 1 mm = 1 mm = 1 mm = 1 mm = 1 mm
= 0.4 mm = 0.4 mm
ALSTOM Patent
The Patent Application bears following data:
Our. Ref.: B03/172-0 DETitle of invention: Verfahren zur Verbesserung der Strömungsverhältnisse in einem Axialkompressor sowie Axialkompressor zur Durchführung des Verfahrens
Application No.: 103 55 108.5Filing Date: 24.11.2003
Legal Owner/Applicant: ALSTOM Technology Ltd,CH-5400 Baden
714 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Own research at IMP PAN
0 540 X [mm]
Pivoted wall
Flat wall
Supply cavity
shock wave
Plate withthe AJVG
Location of AJVG
Traverse upstream the shock, 25 mm
Traverses downstream the shock, 30 and 55 mm
Measurement nozzle
814 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Experimental investigations
Plate with the AJVG
VG holesStatic pressure holes
Main measurement:• Static pressure along the wall• Boundary layers in 3 traverses• Schlieren pictures• Oil visualisation• Oscillations of the shock wave
Mach numbers: 1.25, 1.35, 1.45, 1.55
914 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Boundary layers 30 mm downstream
u/u_delta = F(y/y_delta), M=1.35
0.00
0.20
0.40
0.60
0.80
1.00
1.20
1.40
0 0.2 0.4 0.6 0.8 1
u/u_delta
y/y_
delt
a
BL for No JetsBL for Jets
u/u_delta = F(y/y_delta), M=1.45
0.00
0.20
0.40
0.60
0.80
1.00
1.20
1.40
0 0.2 0.4 0.6 0.8 1
u/u_delta
y/y_
delt
a
BL for No Jets
BL forJets
1014 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Shock wave oscillations
Power spectrum, M=1.35, Rear Shock
0.00
0.05
0.10
0.15
0.20
0.25
0 10 20 30 40 50 60
f [Hz]
Am
plit
ud
e
No JetsJets
RMS Rear shock
M No Jets Jets
1.35 0.95473 0.79997
1.45 1.13944 1.02838
1.55 2.18671 1.97621
Main shock
Rear shock
1114 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
AITEB-2
Coordinator RRD
1214 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
pitch/chord = 1.11 pitch/chord = 1.13
Increased blade load – increased pitchGeometry: IGG Mesh:
Chord: 120 mm 208,288 cells (y+ ~1)Axial Chord: 76.1 mm Numerical scheme:Central Difference Scheme: SPARC, FINE2nd Order Upwind: FLUENTTurbulence model: Spalart-Almaras
Boundary conditions for pitch/chord =1.13:Inlet: Outlet:Total pressure 27983 Pa Static pressure 15840 Pa Total temperature 303.3 KInlet angle 48.6 degViscosity ratio 10
1314 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Final adjustment of the shock location and smoothing of the blade shape
1414 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Reference case experimental results
Maximum Mach number reached
Obtained reduction of M upstream of the shock
Smaller -foot in experiment
Same shock location
1514 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Films with reference shock and with cooling and AJVG
Stabilisation of the shock wave
1614 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Cooling + AJVG
oil visualisation
1714 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
y= f(PP/P0), X=128, Theta=45 alfa=90
02468
101214161820
0.45 0.55 0.65 0.75 0.85 0.95
PP/P0
y [
mm
]
reference Shock X=114Cooling on VG off Shock X=114Cooling on VG on Shock X=114
y= f(PP/P0), X=171, Theta=45 alfa=90
02468
101214161820
0.45 0.55 0.65 0.75 0.85 0.95
PP/P0
y [
mm
]
reference Shock X=114Cooling on VG off Shock X=114Cooling on VG on Shock X=114
Stagnation pressure
Application of cooling increases b.l. thickness considerablyAJVG decreases the effect
X = 128 X = 171
1814 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Objective function: maximum of vorticity X-component at the section 50mm downstream of the jet
Variables: jet skew angles „alfa” jet pitch angles „theta”
Optimisation of AJVG parameters
1914 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute 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”
2014 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Project starting date: 1st of December, 2005
Project duration: 3,5 years
Unsteady effects of shock wave induced separation
Coordinated by IMP PAN
2114 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Interaction types considered in UFAST:
Transonic interaction Nozzle flow Oblique shock reflection
Possibly wide representation of characteristic physical cases
of shock wave boundary layer interaction
2214 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
No. Participant name Short name
1 Institute of Fluid Flow Machinery, Gdansk PL
IMP PAN
2 CNRS Lab. IUSTI, UMR 6595, Marseille F IUSTI
3 ONERA: ( DAFE, DAAP) 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. RUS
ITAM
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
Large tunnels
Large tunnels
SME
New partnerUkraine
CFD
IND
2314 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Observer Name
1 Rolls-Royce Germany, RRD
2 Dassault Aviation
3 Alenia
4 Ansys Germany GmbH
Observer Group
2414 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
PM=638
Transonic interaction Channel flow Shock reflection
2514 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
ALTERNATIVE SOLUTION TO AJVG ALTERNATIVE SOLUTION TO AJVG
STREAMWISE VORTICITY CONTOURS
MEMS – sub-layer device ~ δ1
Rod Vortex Generator
2614 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Full Aero-thermal Combustor-Turbine interactiOn ResearchFACTOR
Zastosowanie AJVG w gorącym środowisku
2010 - 2013
2714 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
Laminar – turbulent transition effects
on unsteady behaviour
of shock wave induced separation
New project topic:
UFAST TUFAST SWIFT?Przemysł: Dassault Aviation, Rolls-Royce Germany,
AVIO, AIRBUS
2814 June 201114 June 2011 – – Session III (P2)Session III (P2)
General Meeting of AERONET General Meeting of AERONET
Polish Academy of SciencesInstitute of Fluid Flow Machinery
THE PEOPLE PROGRAMME – Marie-Curie
Industry-Academia Partnerships and PathwaysSTA-DY-WI-CO (LMS Belgium - IMP PAN Poland)
STAtic and DYnamic piezo-driven StreamWIse vortexgenerators for active flow Control
Initial Training NetworksIMESCON
Innovative MEthods of Separated Flow CONtrol in Aeronautics