Instytut Maszyn Przepływowych
im. R. Szewalskiego
Polskiej Akademii Nauk

1. Shock Wave Boundary Layer Interaction (SWBLI)
   a) SWBLI in various configurations (transonic wind tunnel and CFD)
   
   • flat or convex walls
   • suction side of turbine profile (including film cooling)
   • compressor/fan profile
   • aircraft profile in cruise conditions (A320 profile)
   • helicopter rotor blade in hover and forward flight conditions
   • aircraft model in cruise conditions
   b) Mitigation of SWBLI effects
   
   • reduction of shock induced separation
   • shock wave stabilization
   • noise attenuation
   • drag reduction
   c) Effect of boundary layer transition on SWBLI
   
   • location effect - distance to shock wave
   • investigations of various tripping devices
2. Flow Control (active and passive)
   a) Perforated walls and suction slots
   
   • transonic flows
   • basic configurations (i.e. nozzles and 2d airfoils)
   • helicopter rotor
   • passive/active and hybrid approaches
   b) Jet (fluidic) Vortex Generators (JVG - streamwise vortices)
   
   • subsonic and transonic flows
   • basic configurations (i.e. nozzles and 2d airfoils)
   • turbomachinery
   • helicopter rotor
   c) Rod Vortex Generators (RVG- streamwise vortices)
   
   • subsonic and transonic flows
   • basic configurations (i.e. nozzles and 2d airfoils)
   • helicopter rotor
   • wind turbines
   d) Synthetic Jets
   
   • subsonic flows, basic configurations
   e) Roughness patches
   
   • transonic flows
   • turbomachinery
3. Turbomachinery Cooling
   a) Internal cooling
   
   • experimental and numerical investigations of rib configurations and channel aspect ratio effect on heat transfer and aerodynamic performance
   • real engine rib shape
   b) Impinging jet cooling
   
   • development and validation of active cooling system technology for turbine casing
   • effect of cooled surface shape on HTC
   c) Unsteady impinging jet cooling
   
   • experimental and numerical investigations of Strouhal (Sr) number effect
   • numerical investigations of cross flow effect on impinging jet and cooling effectiveness
4. Turbomachinery - Flow Structure
   a) Aerothermal investigation of turbine endwalls and blades
   
   • leakage effect on heat transfer and flow structure on NGV and sidewall
   • reduction of separation by streamwise vortices (NGV with film cooling)
   b) Aerothermal combustor – turbine interaction
   
   • investigations of hot-spot location and flow structure in turbine stage
   • simulations supporting test rig design (in DLR Goettingen)
   c) Transonic effects in compressor and turbine cascade
   
   • shock wave boundary layer interaction in cascade
   • boundary layer transition effect on aerodynamic performance
   d) Shroud leakage reduction
5. External Flow and Aeroacoustics
   a) Numerical simulations for improving the experimental techniques
   designed for aircraft model performance tests at flight Reynolds
   numbers in cryogenic wind tunnels (ETW-Cologne)
   b) Drag reduction by means of trailing edge excitation
   
   • measurements and simulations for A320 profile in cruise conditions
   c) Aerodynamic and aeroacoustic investigations on helicopter and wind
   turbine blades
   
   • thickness harmonic noise on helicopter rotor blade
   • high-speed impulsive noise on helicopter rotor blade
   • effect of flow control devices on wind turbine blades

Schemat tunelu aerodynamicznego

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Charakterystyka:

• obieg zamknięty pojedynczy,
• zamknięta komora pomiarowa,
• stopień kontrakcji: 16.0,
• wymiary główne: długość 11 m, wysokość 7 m, szerokość 3 m,
• kształt przekroju poprzecznego: ośmiokąt,
• współczynnik energii: 2.4,
• ruchome ściany dla zerowego gradientu ciśnienia.

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