1 14 June 2011 14 June 2011 – – Session III (P2) Session III (P2) General Meeting of AERONET General Meeting of AERONET Polish Academy of Sciences Institute 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 2010/1 3 2011/1 4
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1 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Piotr Doerffer Transonic flow.
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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
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
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