DESIGN OFA PULSED JET ACTUATOR FOR SEPARATION CONTROL CEAS Conference 2017 Bucharest, Oct 16-19

Transcription

1 DESIGN OFA PULSED JET ACTUATOR FOR SEPARATION CONTROL CEAS Conference 2017 Bucharest, Oct Philipp Schlösser (Airbus Defence and Space GmbH) Matthias Bauer (NAVASTO)

2 Separation Control at the Pylon/Wing Junction Motivation Integration of UHBR engines requires larger slat cutouts reduced high-lift performance Relevant (sub-)systems tested in real-size under realistic flow conditions (Ma, Re) TRL 4 Test side plates single slotted flap deployed slat AFC location Flow-through UHBR nacelle Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

3 Installation of Pulsed Jet Actuator on WTM Model span: ~6 m Model chord: ~3.3 m Actuated span: ~1 m Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

4 Pulsed Jet Actuator Design Two-stage Concept Driving/1st stage: fluidic oscillator control signal Outlet/2nd stage: fluidic diverter elements generation of pulsed jets 2nd stage element Illustration of fluid flow inside acutator 1st stage Adapted design for application at engine/wing junction Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

5 Pulsed Jet Actuator Design Separation Control Injection of high-momentum into boundary layer Entrainment of high-momentum free-stream fluid Benefits of pulsed actuation Generation of vortical structures increased mixing rate increased momentum transfer Benefits of two-stage design Efficiency conversion of total to dynamic pressure is more efficient due to the application of several diverters driven by only one oscillator Compactness driving multiple diverters with one oscillator Variability independent setting of actuation amplitude and frequency Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

6 Requirements Flow control / physics jet velocity / Mach number pulsation frequency range mass flow rate or outlet slot dimensions number of slots geometric jet exit angle jet quality criterion (jet velocity homogeneity) Model / geometry location of AFC system integration installation space interfaces for structure and pressure supply Environment / wind tunnel loads on the AFC system temperature of ambient and working fluid security factors issued by the wind tunnel operators can act as significant cost drivers for testing and manufacturing! Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

7 Design Workflow Theoretical Design Set approx. dimensions Set number of elements Estimate dimensions of critical cross-sections Diverter Design (Outlet Stage) Iterative with CFD and experiment Use of rapid prototyping (3D-printing) Oscillator Design and Combination Experimental design (CFD uneconomical) First full prototype testing Final Design Interfaces (structure, air supply) Characterization prior to WTT Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

8 Ground Testing of Pulsed Jet Actuator Prototype Final actuator for WTT Prototype Testing First investigation of complete system Tuning of actuation frequency with variable feedback length First characterization of jets Final Testing Final system including air supply interface for WTT Including monitoring system (21 pressure sensors) Calibration of system for WT application Aquired Data Mass flow Frequency Jet Mach numbers (from three-hole probe) 21 pressure sensors for monitoring during WTT Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

9 Ground Test Results Prototype Testing Focus on actuation frequency by variying feedback length Frequency decreases with length of feedback lines Frequency increases with mass flow Selection of final design from extrapolated data Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

10 Ground Test Results Additional feedback length in final design Frequency and size req satsified! Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

11 Ground Test Results Testing of final actuator Mach numbers evaluated from three-hole probe Diverter #7 Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

12 Ground Test Results Testing of final actuator Mach numbers evaluated from three-hole probe Instants of peak Mach number for each slot Similar symmetric patterns High homogenity (M > 0.8 for large area) Mach number histories of two points Full modulation Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

13 Installation of Pulsed Jet Actuator Actuator successfully installed into wind tunnel model Testing finished in September 2017 Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

14 Summary Flow control / physics number of slots geometric jet exit angle jet velocity / Mach number pulsation frequency range mass flow rate jet quality criterion (jet velocity homogeneity) Model / geometry location of AFC system integration installation space interfaces for structure and pressure supply Environment / wind tunnel loads on the AFC system temperature of ambient and working fluid security factors issued by the wind tunnel operators Ground Tests Installation Successful WTT Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October

15 Thank you for your attention! Partners Presenter Philipp Schlösser Co-Author Matthias Bauer Acknowledgement The work described in this presentation and the research leading to these results have received funding from the European Community's Seventh Framework Programme FP7/ , under grant agreement n , AFLONEXT project. Design of a Pulsed Jet Actuator for Separation Control - CEAS Conference - October