dr. k. srinivasan department of mechanical engineering indian institute of technology madras...
TRANSCRIPT
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Dr. K. SrinivasanDepartment of Mechanical Engineering
Indian Institute of Technology Madras
Nonlinear Spectral Analysis in Aeroacoustics
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Acknowledgement• Funding agencies:
– AFOSR (Dr. John Schmisseur)– ISRO (ISRO-IITM Cell)
• Co-researchers:– Prof. Ganesh Raman, IIT, Chicago– Prof. David Williams, IIT Chicago– Prof. K. Ramamurthi, IIT Madras– Prof. T. Sundararajan, IIT Madras– Dr. Byung Hun-Kim, IIT, Chicago– Dr. Praveen Panickar, IIT, Chicago– Mr. Rahul Joshi, IIT Chicago– Mr. S. Narayanan, IIT Madras– Mr. P. Bhave, IIT Madras
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Roadmap of the talk
• Examples of nonlinearity in aeroacoustics– Twin jet coupling– Hartmann whistle
• Twin jet coupling: Results from linear spectral analysis
• Motivation to use nonlinear spectral analysis • Results from nonlinear spectra• Interaction density metric• Universality of interaction density metric• Conclusions
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Scenarios in resonant acoustics
(a) Impingement (b) Hole tone,Ring tones
(c) Resonance tube (d) Edge tone (e) Cavity tones
Jet interaction with solid devices
Free-jet Resonance: Screech
Hartmann Whistle
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Screech
Raman, Prog. Aero. Sci., vol. 34, 1998
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Other complications
• Non-axisymmetric geometry
• Spanwise oblique geometry and shock structure,
From: Raman, G., Physics of Fluids, vol. 11, No. 3, 1999, pp. 692 – 709.
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Y
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Hartmann Whistle
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Hartmann Whistle
Hartmann Tube
Jet Nozzle
Flow Direction
Tube Length Adjustment
Spacing Adjustment
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Relevant Parameters
s
L
• Tube Length (L)
• Spacing (S)
• Nozzle Pressure Ratio (NPR)
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New Frequency Prediction Model
• Dimensionless numbers involving frequency
• Linearity used indeveloping a frequency model
220
220
02 Sf
RT
Sf
P
Dimensionless no 2 vs L/s 6bar
10
20
30
40
50
60
70
0.5 1 1.5 2 2.5
L/S
s23
s28
s32
s35
s39
s42
2
SkLkS
cf
21
0
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Resemblance with Helmholtz resonator
ALS
Acf
2
Volume V
Llength of neck
AArea of neck
Tube Volume AL
Shock Cell(s)
Spill-over
Spacing S
VL
Acf
2
SkLkS
cf
21
0
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Evidence of Non-linearityMic 1
Mic 2•Highly coherent spectral components summed.
•Intense modulation (quadratic nonlinearities)
•Lissajous show complex patterns. Similar with 2 Piezos.
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Twin jet Coupling
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Literature on twin jet coupling
• Berndt (1984) found enhanced dynamic pressure in a twin jet nacelle.
• Tam, Seiner (1987) Twin plume screech.• Morris (1990) instability analysis of twin jet.• Wlezien (1987) Parameters influencing interactions.• Shaw (1990) Methods to suppress twinjet screech.• Raman, Taghavi (1996, 98) coupling modes, relation
to shock cell spacing, etc.
• Panickar, Srinivasan, and Raman (2004) Twin jets from two single beveled nozzles.
• Joshi, Panickar, Srinivasan, and Raman (2006) Nozzle orientation effects and non-linearity
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Resonant coupling induced damage (Berndt, 1984)
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Twin jet coupling
• Aerodynamic, acoustic and stealth advantages derived from nozzles of complex geometry.
• Acoustic fatigue damage observed in earlier aircraft.
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Our earlier work
• Panickar et al.(2004) concluded the following from their experiments:
– Single beveled jet - symm, antisymm and oblique modes.
– Twin jet - only spanwise symmetric and antisymmetric modes during coupling.
– A simple change to the configuration eliminated coupling between the jets.
Journal of Sound and Vibration, vol.278, pp.155-179, 2004.
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Modal Interactions in twin jets
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Illustration of earlier results(a) Single jet modes
(b) V-shaped configuration: Twin jet coupling modes
(c) Twin jet: Arrowhead-shaped configuration
Jet Flow Direction
Bevel Angle = 300
Nozzle
Microphone
No coupling
Spanwise symmetric coupling mode
Spanwise antisymmetric coupling mode
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Experimental SetupParameters
• Stagnation Pressure: 26 psig to 40 psig, in steps of 1 psi
• Mach No. Range: 1.3 Mj 1.5
• Nozzle spacings: 7.3 s/h 7.9Measured Quantities
• Stagnation Pressure• Sound Pressure signals
s
h
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Signal Conditioning & DAq
Mic+Preamp. + Pow. Supp.
Anti-alias filter
1 – 100 kHz
NI Board
1 – 100 kHzSampling rate:200 kSa/s
Sampling time: 1.024 s
Interface
Stagnation Pressure
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Outline of the Method
• Spectra• Frequency locking• Phase locking• Phase angle
substantiated by high phase coherence.
• Observations for different geometric and flow parameters
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Time series Analyses
• presence of neighbouring jet in close proximity, and dissimilarities between the two jets.
• Parity plots of average spectra of the two channels in the frequency domain shows dissimilarities between jets, although they were frequency/phase locked.
Mach No. 1.33 Mach No. 1.4
Mic 1 Power, (Log units)
M
ic 2
Po
wer
, (L
og
un
its)
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Phase plots of time series data• Time series data of acoustic pressure from a channel plotted against
the other: • X-Y phase plots
Time Series: Xi
Time Series: Yi
Xi
Yi
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X-Y phase plots & non-linearity
• Phase plots (time domain) also pointed out to non-linearity at some Mach numbers.
1.3
1.33
1.37
1.4 1.5
Fuzziness
Curvature
X and Y axes: Acoustic Pressures. Range: -2000 Pa to 2000 Pa for all plots
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Time-Localization Studies• To gain additional knowledge, phase plots
within a data set were plotted: x-x phase plots
t
x(t)
titi+t ti+2t
Window 1 Window 2
x(w1)
x(w2)
x-x Phase plot
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Cross Spec, x-x, y-y, and x-y plots
A
B
C
D
Note: x-x and y-y plots are dissimilar, but x-y plots look similar
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A
B
C
D
Note: x-x, y-y, and x-y plots change within the time series.
Cross Spec, x-x, y-y, and x-y plots
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Further attempts to understand the non-linear behaviour
• Simulation of non-linear sinusoids to match their phase plots with experimental ones.– A Lissajou simulator for generating various
artificial phase plots. – These attempts were not much successful
and not an elegant approach to decipher the non-linearities.
• Conventional spectral analysis (SOS) does not reveal information about non-linearities.
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Drawbacks of SOS
• SOS cannot discern between linearly superposed and quadratically modulated signals.
• So, use restricted to linear systems.
t = [0:1e-5:1]';x = 0.5*(sin(2*pi*3000*t)+sin(2*pi*13000*t));y = sin(2*pi*5000*t).*sin(2*pi*8000*t);[p f] = spectrum(x,y,1024,[],[],100000);semilogy(f,p(:,1),f,p(:,2));xlabel ('Frequency (Hz)');ylabel ('PSD (1^2/Hz)');legend('3k+13k','5k*8k');
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Higher order spectral methods
• Tool Employed – Cross Bispectrum.
• Description: In two time series signals, Quantifies the relationship between a pair of frequencies in the spectrum.
• x-Bispectrum:
• Ensemble Average:
• x-Bicoherence:
)()()(),( 2)*(
1)*(
21)(
21)( fXfXffYffS kkkk
YXX
M
k
kYXXYXX ffS
MffS
121
)(21 ),(
1),(
M
k
kkM
k
k
YXXc
fXfXM
ffYM
ffSffb
1
2
2)(
1)(
1
2
21)(
2
2121
2
)()(1
)(1
),(),(
212211
0
2121 )(2exp)()()(1
lim),( ddffidttxtxtyT
ffBT
Tyxx
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Use of HOS in shear flows
• Thomas and Chu (1991, 1993): Planar shear layers, traced the axial evolution of modes.
• Walker & Thomas (1997): Screeching rectangular jet, axial evolution of non-linear interactions.
• Thomas (2003): Book chapter on HOS tools applicable to shear flows.
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Demonstration
• Two sinusoids generated:
Spectra Cross-Bicoherence
tttf 21 sinsin)( )sin(sin)( 21 tttg
(a) (b)
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Interpreting results from CBC spectra
Plot shows CBC contours
• X and Y axes: Frequencies interacting non-linearly.
• Resultant frequencies read from the plot.
• Strength quantified by CBC value (color)
, - participating frequencies.
- Resultant frequency
Sum Int. Region
Diff. Int. Region
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Influence of Phase on CBC
• To examine the effect of phase (), on the cross-bicoherence, various used.
• The resultant plot showed that CBC is insensitive to small phase differences, but declines sharply for large phase differences ( /2 and greater).
tttf 21 sinsin)( )sin(sin)( 21 tttg
0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1
0 1 2 3 4
Phase Difference (radians)
Cro
ss
-Bic
oh
ere
nc
e
Phase
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Effect of Magnitude of Non-Linear part
• Nonlinear part systematically varied.
• The resultant spectra of g(t) and cross-bicoherence between f(t) and g(t) examined.
• Note that the cross-bispectrum looks similar. Only the magnitudes differ.
)sin(sin½)( 21 tttf)sin(sin)()( 21 ttBtfAtg A + B = 1
0 0.05
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How do SOS and HOS compare in their respective tasks?
A = 0.5, B = 0.5
A = 0.9, B = 0.1
A = 0.95, B = 0.05
A = 0.99, B = 0.01
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HOS is more robust; detects even very small magnitudes of non-linearity
A = 0.995, B = 0.005
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How to use CBC
• Obtain the second order and third order spectra for the entire parametric space.
• Look for changes in gross features in the higher order spectra and establish a correspondence with earlier knowledge.
• Establish metrics from HOS to quantify non-linearity.
• If possible, trace the evolution of the spectra.
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Results: Coupled and Uncoupled Jets
V-shaped: Coupled
Arrowhead-shaped: Did not Couple
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Single and Twin Jets
• Single jets show lesser non-linearity than twin jets in terms of number and strength of interactions.
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Spectra at Mach numbers in the symmetric coupling range
Mj = 1.3 Mj = 1.33
Interaction Clusters
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As Mach number increases…
Mj = 1.4, Mode Switching Mj = 1.46, Antisymmetric
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Clustering illustrated
f
-f
f1
(f1+f)
(f1-f)
f1+f
(f1+2f)
(f1)
f1
(2f1)
2f1
(2f1+f)
2f1+f
(2f1+2f)
(2f1-f) (2f1-2f)
Cluster 1 Cluster 2
fs/2
fs
-fs
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Close-up view of a cluster
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Effect of inter-nozzle spacing
s/h = 7.3 s/h = 7.5 s/h = 7.7
More dots (NL interactions) as s/h increases
Mj = 1.32 (symmetric)
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A
B C
s/h = 7.5 s/h = 7.7 s/h = 7.9
Effect of inter-nozzle spacingMj = 1.46 (antisymmetric)
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Closer look at the straightly aligned interactions
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NL Interaction Quantification• Based on number of interactions
– Interaction Density: Number of peaks in the CBC spectrum above a certain (interaction threshold) value.
– Threshold values of 0.3, and 0.4 used. – Interaction density variation with parameters of
the study.
nffb
nffbjijiI
jic
jicN
i
M
jnc
),(
),(
0
1),(),,( 2
2
1 1,
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Interaction density (threshold 0.3) variation with Mach number
0
20
40
60
80
100
120
1.28 1.31 1.34 1.37 1.4 1.43 1.46 1.49 1.52
Fully Expanded Mach Number (Mj)
Inte
ract
ion
Den
sity
(Ic,
0.3)
V-shaped, 0 mm V-shaped, 1 mm V-shaped, 2 mm
V-shaped, 3 mm Arrowhead, 0mm Single jet7.3 7.5 7.7
7.9 7.3
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Interaction density (threshold 0.4) variation with Mach number
0
10
20
30
40
50
60
70
80
1.28 1.31 1.34 1.37 1.40 1.43 1.46 1.49 1.52
Fully Expanded Mach Number (M j)
Inte
ract
ion
Den
sity
(Ic,
0.4
)
Moderate increase around symmetric Peak at coupling-transition
Mach number
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Average Interaction density metric
0
10
20
30
40
50
7.3 7.5 7.7 7.9
Inter-nozzle spacing (s/h )
Av
g. i
nte
rac
tio
n d
en
sit
y
(Ic,
0.3)
0
10
20
30
40
50
60
70
1.29 1.32 1.35 1.38 1.41 1.44 1.47 1.50
Mach number
Av
g. I
nte
rac
tio
n d
en
sit
y
(Ic,
0.3)
0
10
20
30
40
50
1.29 1.32 1.35 1.38 1.41 1.44 1.47 1.50
Mach number
Avg
. in
tera
ctio
n d
ensi
ty
(Ic
,0.4)
0
5
10
15
20
25
7.3 7.5 7.7 7.9
Inter-nozzle spacing (s/h )
Avg
. in
tera
ctio
n d
ensi
ty
(Ic
,0.4)
(a)
(b) (d)
(c)
•Interaction density averaged over all Mach numbers for a particular spacing, and vice-versa.
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54Physics of Fluids, vol.17, Art.096103, 2005
Significance of Interaction Density Metric
nffb
nffbjijiI
jic
jicN
i
M
jnc
),(
),(
0
1),(),,( 2
2
1 1,
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Mic 1 Mic 2
Jet flow direction
Jet flow direction
Mic 1Jet 1
Mic 2Jet 2
Mic 3Twin jet
α = yaw angle
Significance of Interaction Density contd…
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Spacing 30mm, length 40 mm
Spacing 40mm, length 30 mm
Mic 1Mic 2CBC spectra of Hartmann
Whistle Data
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Interaction Density vs NPR
Interaction Density vs NPR
0
10
20
30
40
50
60
4 6 8
NPR
Ic,0
.3
s30d40 s40d30 s45d35
Mic 1Mic 2
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Conclusions
• Configurations that did not show conclusive linear coupling were found nonlinearly coupled. So, nonlinear coupling may be important in nozzle design.
• Nonlinearity in configs can be graded
• Two patterns of cross-bicoherence were observed, one that showed clustering, and another that showed a straight alignment.
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Conclusions…• A new interaction density metric identified
and seems a relevant parameter to quantify non-linear coupling.
• The average interaction density peaks in the vicinity of mode jumps
• Therefore, higher order spectra could serve as useful tools in theoretical understanding as well as in practical situations.
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