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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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Presentation on theme: "1 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Piotr Doerffer Transonic flow."— Presentation transcript:

1 1 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET 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 2010/ /14

2 2 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET 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

3 3 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Reaearch idea from MIT ALSTOM Project for EPFL Lausanne Transonic compressor blades are: - very thin - strong spanwise variation

4 4 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Flow control concept – Stream-Wise Vortices (SV) Methods of SV Generation Vane Vortex Generators Air Jet Vortex Generators

5 5 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET 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

6 6 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET 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 Application No.: Filing Date: Legal Owner/Applicant: ALSTOM Technology Ltd, CH-5400 Baden

7 7 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Own research at IMP PAN X [mm] Pivoted wall Flat wall Supply cavity shock wave Plate with the AJVG Location of AJVG Traverse upstream the shock, 25 mm Traverses downstream the shock, 30 and 55 mm Measurement nozzle

8 8 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Experimental investigations Plate with the AJVG VG holes Static 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

9 9 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Boundary layers 30 mm downstream

10 10 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Shock wave oscillations RMS Rear shock MNo JetsJets Main shock Rear shock

11 11 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET AITEB-2 Coordinator RRD

12 12 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET pitch/chord = 1.11 pitch/chord = 1.13 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 Boundary conditions for pitch/chord =1.13: Inlet: Outlet: Total pressure Pa Static pressure Pa Total temperature K Inlet angle 48.6 deg Viscosity ratio 10

13 13 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Final adjustment of the shock location and smoothing of the blade shape

14 14 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Reference case experimental results Maximum Mach number reached Obtained reduction of M upstream of the shock Smaller -foot in experiment Same shock location

15 15 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Films with reference shock and with cooling and AJVG Stabilisation of the shock wave

16 16 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Cooling + AJVG oil visualisation

17 17 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Stagnation pressure Application of cooling increases b.l. thickness considerably AJVG decreases the effect X = 128 X = 171

18 18 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET 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

19 19 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET The invention submission EM 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”

20 20 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Project starting date: 1st of December, 2005 Project duration:3,5 years Unsteady effects of shock wave induced separation Coordinated by IMP PAN

21 21 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Interaction types considered in UFAST: Transonic interactionNozzle flowOblique shock reflection Possibly wide representation of characteristic physical cases of shock wave boundary layer interaction

22 22 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET No.Participant nameShort name 1 Institute of Fluid Flow Machinery, Gdansk PL IMP PAN 2CNRS Lab. IUSTI, UMR 6595, Marseille F IUSTI 3ONERA: ( DAFE, DAAP) F ONERA 4University of Cambridge, Dept. of Engineering UK UCAM-DENG 5Queens University Belfast, School of Aero. Eng. UK QUB 6Russian Academy of Science, Siberian Branch, Novosibirsk, Inst. of Theor. App. Mech. RUS ITAM 7Delft University of Technology, Aerodyn. Lab. NL TUD 8INCAS, Romanian Institute for Aeronautics RO INCAS 9University of Southampton, (SES) UK SOTON 10University of Rome "La Sapienza", I URMLS 11University of Liverpool, Dept. of Aero. Engin. UK LIV 12NUMECA, Belgium, SME B NUMECA 14Institute Mécanique des Fluides de Toulouse F IMFT 16FORTH/IACM, Found. for Res. and Techn.-Hellas GR FORTH 17Ecole Centrale de Lyon F LMFA 19EADS-M, Deutschland GmbH Military Aircraft D EADS-M 20Institute of Aviation, Warsaw PL IoA Large tunnels SME New partner Ukraine CFD IND

23 23 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Observer Name 1Rolls-Royce Germany, RRD 2Dassault Aviation 3Alenia 4Ansys Germany GmbH Observer Group

24 24 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET PM=638 Transonic interaction Channel flowShock reflection

25 25 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET ALTERNATIVE SOLUTION TO AJVG STREAMWISE VORTICITY CONTOURS MEMS – sub-layer device ~ δ 1 Rod Vortex Generator

26 26 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET Full Aero-thermal Combustor-Turbine interactiOn Research FACTOR Zastosowanie AJVG w gorącym środowisku

27 27 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET 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

28 28 Polish Academy of Sciences Institute of Fluid Flow Machinery 14 June 2011 – Session III (P2) General Meeting of AERONET 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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