Advanced Engine Noise Control Based on Plasma Actuators. Franck Cléro, Onera Victor Kopiev, TsAGI

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1 Advanced Engine Noise Control Based on Plasma Actuators Franck Cléro, Onera Victor Kopiev, TsAGI

Fan Soufflante Compresseur Compressor Combustion Combustinr Jet Turbine Turbine Aerodynamique Airframe noise Avion Soufflante Fan Compresseur Compressor Combustion Turbine Aerodynamique Airframe

2 Fan Soufflante Compresseur Compressor Combustion Combustinr Jet Turbine Turbine Aerodynamique Airframe noise Avion Soufflante Fan Compresseur Compressor Combustion Turbine Aerodynamique Airframe noise Avion Jet Context ACARE goals for 2020 Reduction of the external noise by 10 EPNdB per operation of fixedwing aircraft (reference 2000) 5 db Silence(R) Project has reached the mid-term reduction of 5 EPNdB (Generation 1) 5 db Source ICCAIA & Airbus Squid nozzle developed in Silence(R) 2

3 Fan Soufflante Compresseur Compressor Combustion Combustinr Jet Turbine Turbine Aerodynamique Airframe noise Avion Soufflante Fan Compresseur Compressor Combustion Turbine Aerodynamique Airframe noise Avion Jet Context ACARE goals for 2020 Reduction of the external noise by 10 EPNdB per operation of fixedwing aircraft (reference 2000) 5 db Silence(R) Project has reached the mid-term reduction of 5 EPNdB (Generation 1) 5 db Source ICCAIA & Airbus Squid nozzle developed in Silence(R) 3

Average Decibels per Aircraft Operation Context "Generation 2" approach to meet ACARE goals in noise suppression 0 2020 VISION - 3 Integrated Powerplant Design Maximizing Benefit of Novel Passive &

4 Average Decibels per Aircraft Operation Context "Generation 2" approach to meet ACARE goals in noise suppression VISION - 3 Integrated Powerplant Design Maximizing Benefit of Novel Passive & Variable Noise Reduction Technologies, associated to further Airframe noise reduction Baseline: Generation 1 Powerplant & Airframe Noise Reduction Technologies (Silence(R) Solutions: Generation 1 Noise Technologies Noise Abatement Procedures Active, Adaptive and Flow Control Noise Reduction Technologies optimized vs performance and weight impact Technology Breakthrough - 9 Implementation of Generation 2 Noise Reduction Technologies in Novel Engine & Aircraft Architectures Base (2000) ACARE Goal Years 4

5 Presentation of the ORINOCO project 3rd call: FP7-AAT-2010-RTD-RUSSIA: co-funded by European Commission and Ministry of Industry and Trade of Russian Federation 13 partners, mainly from research institutes 41 months (August 2010-Dec. 2013) Fundamental objectives: To develop and enhance plasma actuators technologies dedicated to jet noise reduction To investigate instability waves concepts for jet noise To formulate noise control strategy To implement jet noise control based on plasma actuators 5

6 Organisation of ORINOCO European partners ONERA - Leader CIRA ECL-LMFA CNRS Poitiers NLR University Roma Tre Erdyn The Consortium Industrial Expert Panel Alenia Aermacchi Beriev Airbus Sukhoi Snecma Tupolev Russian partners TsAGI Leader Aviadvigatel CIAM GPI RAS JIHT RAS TRINITI Regular overview on the project 6

7 3 concepts under investigations 7

8 3 concepts under investigations 8

9 Sketch of the instability wave concept for noise calculation Initial amplitude of instability wave A 0 Shear layer h( x) V 0 o x Small internal disturbances initiating instability waves Instability wave packet x p A0 (, n) exp i ( x) dx exp( i t in ) p( r, x) 0 Pressure disturbances in wave packet 9

10 The ways of exciting of instability waves o x Turbulent disturbances as natural excitation o x Artificial acoustic excitation o x Artificial exciting by plasma actuators 10

11 Formulation of the control strategy for artificially excited jet Near field charcteristics o x Artificial acoustic excitation characterized by amplitude and phase at given frequency Closed-loop system Near field measurements Instability wave disappear o x Artificial acoustic excitation Artificial exciting by plasma actuators 11

12 Control of artificially excited jet Sketch of the experiment f=800hz Gen2 Cold subsonic jet: D nozzle = 52mm U jet = 50m/s Gen1 External cone 43mm 100mm Hot-wire probe Flow 25mm Nozzle 12 S5 S6 S13 S14 S15 Microphones in the near field S16

13 Control of artificially excited jet 13

14 Filtered hot-wire signal Frequency band Hz Typical value of velocity pulsations is about V~1 m/s (not acoustics) 14

15 PIV measurements, f exc =f samp =1kHz V y -<V y > Pure jet 15

16 PIV measurements, f exc =f samp =1kHz V y -<V y > Inner source 16

17 PIV measurements, f exc =f samp =1kHz V y -<V y > Outer source 17

18 PIV measurements, f exc =f samp =1kHz V y -<V y > Δφ =

19 PIV measurements, f exc =f samp =1kHz V y -<V y > Δφ =

20 Plasma actuators 20

21 Plasma actuators based on HF DBD Power generator parameters: High voltage up to 20 kv Oscillation frequency within khz Modulation frequency up to 20 khz Modulation depth is 100% Power up to 1kWt 200 m/s Unforced jet Forced jet, 1kHz 21

22 Laboratory tests Preparation of the assessment tests Nozzle Ø 50 mm equipped with 12 Plasma Synthetic Jets PIV measurement Acoustic arrays with actuator no actuator Analysis of the effect of PSJs on the jet Generation of strong coherent structures Increase of the divergence angle of the shear layer 22

Assessment test of PSJ In LMFA facility Jet

23 Assessment test of PSJ In LMFA facility Jet M=0.6 and 0.9 Different actions of PSJ 3 frequencies 5 modes (0,1,2,3,6) Acoustic campaign Far field measurements Aerodynamic measurements Caracterisation of the jet and the micro-jet Analysis of the effect of PSJ on the turbulence 23

24 Large Eddy Simulations as support to understand tests results Nozzle Ø 50 mm, M j = 0.9 Control with 12 PSJs Located on nozzle lip, Ø 1mm f F = 820 Hz (St F = 0.14) All PSJs in phase (mode m=0) Experimental setup - LFMA PSJs generate a large coherent vortex in the shear layer Results similar to experiments 24

25 Active Control of Instability waves Results Proof of existence of instability wave as mechanism of jet noise radiation Possibility to articificially generate instability waves Effective reduction of instability wave magnitude thanks to plasma actuators 25

26 3 concepts under investigations Second concept 26

Possibility of Instability Waves Coupling if jet flow near nozzle orifice has weak nonaxisymmetric feature Close location of eigenvalues for round jet 1 Coupled oscillators Weak azimuthal

27 Possibility of Instability Waves Coupling if jet flow near nozzle orifice has weak nonaxisymmetric feature Close location of eigenvalues for round jet 1 Coupled oscillators Weak azimuthal nonuniformity of mean jet flow near the nozzle orifice can be created by: corrugation of nozzle cross section chevrons lobed nozzle steady microjet of plasma actuators 2 Nonresonance case 1 A A O(1) 1 2 O() A O(1) O() 2 1 A ~ 1 2 1,2 Resonance case 1 2 1, A O(1) A O(1) A A O(1) 2 O(1) 1 27

28 Experiments on jet noise reduction by corrugated nozzles Experimental conditions: Cold jet, V=240 m/s, Venturi tube for measuring flow rate Microphones Bruel&Kjaer type 4189С R= 2m, 90, 60 deg. 28

29 Far-field noise spectra at angles 90deg for corrugated nozzle Decrease in the far field noise levels around the spectral peak (0,1<St<0,7) and weak increase at high frequencies. The max noise attenuation (in the band 0,16 25,6 khz) was measured to be 2.3dB 29

30 Modification of jet mean flow for instability wave coupling 1st stage: corrugated nozzle 2nd stage: plasma actuators 30

31 Combined HF +DC discharge Autospectrum(Signal 2) - Without discharge (Real) \ FFT Analyzer averagenumber : 1500 Autospectrum(Signal 2) - With discharge (Real) \ FFT Analyzer LinDelta Cursor [db/20u Pa] Start: Hz Stop: 2.650k Hz 70 Delta: db/20u Pa Delta: db/20u Pa Photo of operating plasma actuator with HF discharge k 8k 12k 16k 20k 24k [Hz] Autospectrum(Signal 2) - Without discharge (Real) \ F Autospectrum(Signal 2) - With discharge (Real) \ FFT [db/20u Pa] ,8dB averagenumbe Delta Cursor Start: Stop: 2.650k H Delta: Delta: k 2k 3k 4k 5k 6k 7k [Hz]

32 Azimuthal Mode Coupling Technique (AMCT) Results Demonstration of principle realization AMCT on the base of corrugated nozzle; Demonstration of principle realization AMCT on the base of plasma-actuator. 32

33 3 concepts under investigations 33

Reduced Order Model Linear stability analysis provides the main behaviour of the jet on the first 5 diameters Armax (auto-regressive moving average

34 Reduced Order Model Linear stability analysis provides the main behaviour of the jet on the first 5 diameters Armax (auto-regressive moving average exogeneous) Identification performed on measurement No physical analyis required Based on azimuthal modes Experimental setup near field azimutal array 34

35 Conclusions Formulation of active control strategy is realized with three steps: (i) suppression of artificially excited instability wave (SAIW) is designed and manufactured (sound-sound and sound-plasma); on this base the formulation of control strategy for natural instability waves (SNIW) (ii) implementation of mode coupling techniques with plasma actuators (iii) Formulation of feedback control system (PLANT) for a jet using PSJ plasma actuators is realized; These suppression strategies will contain closed-loop system. It was demonstrate using SAIW (acoustic-acoustic or/and plasma- acoustic) 35

36 Thank you for your attention! 36

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