advanced engine noise control based on plasma actuators

Advanced Engine Noise Control Based on Plasma Actuators

Franck Cléro, Onera

Victor Kopiev, TsAGI

2

AirTN Network Meeting

27th September, Cranfield University, UK

Context

• ACARE goals for 2020

• Reduction of the external noise by 10 EPNdB per operation of fixed-

wing aircraft (reference 2000)

Silence(R) Project has reached the

mid-term reduction of 5 EPNdB

(Generation 1)

Squid nozzle developed in Silence(R)

Source ICCAIA & Airbus

Com

bustio

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Jet

Ae

rod

yn

am

iqu

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Tu

rbin

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Com

pre

sseur

Souff

lante

5 dB

Com

bustio

n

Jet

Air

fra

me

no

ise

Tu

rbin

e

Com

pre

ssor F

an

5 dB

Com

bustin

r

Jet

Aero

dynam

ique

Avio

n

Tu

rbin

e

Com

pre

sseur

5 dB

Souff

lante

Com

bustio

n

Jet Airfr

am

e n

ois

e

Tu

rbin

e

Com

pre

ssor

5 dB 5 dB


Fa

n

3



Context

• ACARE goals for 2020

• Reduction of the external noise by 10 EPNdB per operation of fixed-

wing aircraft (reference 2000)

Silence(R) Project has reached the

mid-term reduction of 5 EPNdB

(Generation 1)

Squid nozzle developed in Silence(R)


Com

bustio

n

Jet

Ae

rod

yn

am

iqu

e A

vio

n

Tu

rbin

e

Com

pre

sseur

Souff

lante

5 dB

Com

bustio

n

Jet

Air

fra

me

no

ise

Tu

rbin

e

Com

pre

ssor F

an

5 dB

Com

bustin

r

Jet

Aero

dynam

ique

Avio

n

Tu

rbin

e

Com

pre

sseur

5 dB

Souff

lante

Com

bustio

n

Jet Airfr

am

e n

ois

e

Tu

rbin

e

Com

pre

ssor

5 dB 5 dB


Fa

n

4



Years

0

+ 12Base (2000) + 4 + 20

- 3

- 9

- 6

Ave

rag

e D

ec

ibe

ls p

er A

irc

raft

Op

era

tio

n

+ 8 + 16

Active, Adaptive and Flow

Control Noise Reduction

Technologies optimized vs

performance and weight impact

Implementation of Generation 2

Noise Reduction Technologies

in Novel Engine &

Aircraft Architectures

2020

VISION

Baseline: Generation

1 Powerplant & Airframe Noise

Reduction

Technologies(Silence(R)

Integrated Powerplant

Design Maximizing

Benefit of Novel Passive &

Variable Noise Reduction

Technologies, associated to

further Airframe noise reduction

2010 Solutions:•Generation 1 Noise Technologies

•Noise Abatement Procedures

ACARE Goal

Technology

Breakthrough

Context

• "Generation 2" approach to meet ACARE goals in noise

suppression

5



• 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

Presentation of the ORINOCO project

6



Organisation of ORINOCO

European partners

ONERA - Leader

CIRA

ECL-LMFA

CNRS Poitiers

NLR

University Roma Tre

Erdyn

Russian partners

TsAGI – Leader

Aviadvigatel

CIAM

GPI RAS

JIHT RAS

TRINITI

The

Consortium

Industrial Expert Panel

Alenia Aermacchi

Airbus

Snecma

Beriev

Sukhoi

Tupolev

Regular

overview

on the

project

7



3 concepts under investigations

8




9



x0V o

0A

( )h x

Initial

amplitude of

instability wave

Shear

layer

Instability wave

packet

Small internal disturbances

initiating instability waves

Sketch of the instability wave concept for noise calculation

0

0

( , ) exp ( ) exp( ) ( , )

x

p A n i x dx i t in p r x

Pressure disturbances in wave packet

10



Turbulent disturbances as

natural excitation

xo

Artificial acoustic excitation

xo

Artificial exciting by

plasma actuators

xo

The ways of exciting of instability waves

11



xo

Artificial exciting by

plasma actuators

Instability wave disappear


Near field

measurements Closed-loop

system

xo


characterized by amplitude and

phase at given frequency

Near field

charcteristics

Formulation of the control strategy

for artificially excited jet

12



Cold subsonic jet:

Dnozzle= 52mm

Ujet= 50m/s

Control of artificially excited jet

Sketch of the experiment

S5

Microphones in the near field

S6 S13 S14 S15 S16

25mm

43mm Hot-wire probe

100mm

Flow

External cone

Nozzle

Gen1

Gen2

f=800Hz

13



Control of artificially excited jet

14



Filtered hot-wire signal

Frequency band 790…810Hz

Typical value of velocity

pulsations is about V~1 m/s

(not acoustics)

15



Pure jet

PIV measurements , fexc=fsamp =1kHz

Vy -<Vy>

16



Inner source


Vy -<Vy>

17



Outer source


Vy -<Vy>

18



Δφ = -1800


Vy -<Vy>

19



Δφ = -600


Vy -<Vy>

20



Plasma actuators

21



Plasma actuators based on HF DBD

Unforced jet Forced jet, 1kHz

Power generator parameters:

High voltage up to 20 kV

Oscillation frequency within 100-300

kHz

Modulation frequency up to 20 kHz

Modulation depth is 100%

Power up to 1kWt

200 m/s

22



Laboratory tests Preparation of the assessment tests

• Nozzle Ø 50 mm equipped with 12

Plasma Synthetic Jets

• PIV measurement

• Acoustic arrays 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

with actuator

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

24



Large Eddy Simulations as support to understand tests results

• Nozzle Ø 50 mm, Mj = 0.9

• Control with 12 PSJs • Located on nozzle lip, Ø 1mm

• fF = 820 Hz (StF = 0.14)

• All PSJs in phase (mode m=0)

• PSJs generate a large coherent

vortex in the shear layer

• Results similar to experiments

Experimental setup - LFMA

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

26




Second concept

27



Coupled

oscillators

1

2

1

1

2

1 2

1

2

1

2

1(1)OA 2

( )OA 1

( )OA 2(1)OA

1(1)OA

2(1)OA

1(1)OA 2

(1)OA

Nonresonance case

Resonance case

1 2 1,2~

1 2 1,2

Possibility of Instability Waves Coupling

if jet flow near nozzle orifice has weak nonaxisymmetric feature

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

Close location of eigen-

values for round jet

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.

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

30



Modification of jet mean flow for instability wave coupling

1st stage: corrugated nozzle 2nd stage: plasma actuators

31



Photo of operating plasma actuator

with HF discharge

0 4k 8k 12k 16k 20k 24k[Hz]

20

30

40

50

60

70

[dB/20u Pa]

averageNumber : 1500Delta CursorStart: 194.000 HzStop: 2.650k HzDelta: 75.8691 dB/20u PaDelta: 75.0732 dB/20u Pa

Autospectrum(Signal 2) - Without discharge (Real) \ FFT Analyzer Lin

Autospectrum(Signal 2) - With discharge (Real) \ FFT Analyzer Lin

0 1k 2k 3k 4k 5k 6k 7k[Hz]

35

40

45

50

55[dB/20u Pa]

averageNumber : 1500Delta CursorStart: 194.000 HzStop: 2.650k HzDelta: 75.8691 dB/20u PaDelta: 75.0732 dB/20u Pa

Autospectrum(Signal 2) - Without discharge (Real) \ FFT Analyzer Lin

Autospectrum(Signal 2) - With discharge (Real) \ FFT Analyzer Lin

0,8dB

Combined HF +DC discharge

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.

33




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

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)

36



Thank you

for your attention !

advanced engine noise control based on plasma actuators

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