some challenging problems in (active) flow and noise · pdf fileflorida state university...
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![Page 1: Some Challenging Problems in (Active) Flow and Noise · PDF fileFlorida State University Florida Center for Advanced Aero-Propulsion Some Challenging Problems in (Active) Flow and](https://reader031.vdocuments.us/reader031/viewer/2022022421/5a80f1927f8b9a571e8cf5ff/html5/thumbnails/1.jpg)
Florida State University Florida Center for Advanced Aero-Propulsion
Some Challenging Problems in
(Active) Flow and Noise Control
A (Limited) Experimental Perspective
F. S. Alvi
Future Directions in CFD Research
Aug 6-8, 2012, Hampton Roads, VA
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R. Kumar, A. Uzun, M. Y. Hussaini, A. Krothapalli,
J. Solomon, J. Gustavsson, W. Oates, Y. Ali, C. Foster,
E. Thomas, A. Wiley, H. Lou, V. Kumar, N. Zhuang
…. many, many more
S. Haack, B. Cybyk (JHU/APL)
Collaborators
Acknowledgements
Research Sponsors
AFOSR, AFRL, DARPA, BOEING NASA,
ONR, State of Florida and others
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Outline
• Problems
– Supersonic Cavity Flows
– Supersonic Impinging Jets
– Separated Flows
• Experimental & Computational Results
– Base Flowfield
– Response to Active Control
• Steady Microjets
– Pulsed Microjet Actuators
• Final Thoughts
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acoustic waves/pressure disturbances
kMM
rm
L
fUSt
1
2
11
5.0
2
m – Mode no.
r – Phase delay
k – Uconv/U∞
Modified Rossiter’s Model
(Heller & Bliss, 1975) structures
scale-LargeTELE
esdisturbanc pressure
/ wavesAcoustic
Waves
yInstabilit
Receptivity
Cavity Flows Flow –Acoustic Resonance
Resonance observed for
Low subsonic to high
Supersonic Flows
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Phase-locked Schlieren Images,
L/D = 2, M = 0.5
(Kegerise, et al., 1999)
Cavity Flow Visualizations
Subsonic Flow Subsonic to Transonic
Krishnamurti, 1955
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Cavity
Flow
Supersonic Cavity Flow
M = 2
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“Quantitative” Measurements M∞= 2, L/D =5
• High unsteady pressures throughout the cavity
• Maximum loads near the aft
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Large- scale
structures
L/D ~ 5
Velocity Field Phase-Conditioned
Phase-conditioned
component
Ensemble
averaged component Periodic
component
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Effect of Microjet Control
Mach 2 Cavity Flow
baseline with control
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Unsteady Pressure Spectra Effect of Microjet Control
Frequency KHz
SP
Ld
B
5 10 15 20110
120
130
140
150
160
Control Off
Control On
Cavity front
Frequency KHz
SP
Ld
B
5 10 15 20130
140
150
160
170
180
Control Off
Control On
Cavity aft
9 dB OASPL reduction
20+ dB Tonal reduction
Zhuang, Alvi, Shih
AIAA J, 2006
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Microjet Control
Effect of Microjet Control
Unsteady Velocity, Vrms
Baseline
LES (courtesy CRAFT Tech)
Ensemble-Averaged (using PIV)
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Velocity Iso-surfaces
Microjets & Slot Jets Simulations*
Microjets
Slotjets * S. Arunajatesan et al.
AIAA Jrnl, 2009
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Effect of Microjets : Simulations*
Velocity Iso-surfaces *Courtesy CRAFT Tech
Microjet Control Baseline
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Complex Cavity Flows
* S. Arunajatesan et al., AIAA Jrnl, 2009
Microjet Control (40 psi)
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Unsteady Flow Field -
Simulations
Baseline Microjets Slotjets
* S. Arunajatesan et al., AIAA Jrnl, 2009
Simulations provide insight into the 3-D nature of the flow
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Frequency(Hz)
Prms
5000 10000 15000 20000 25000 30000 35000110
120
130
140
150
160
170
180
190Ground PlaneLift PlateMicrophone
37-s-nc-h4-GPLPMic.lay
NPR 3.7 h = 4.0 No Control
Unsteady Pressure Loads:
Ground Plane ~ 185-195 dB
Lift Plate ~ 165-175 dB
Pressure Spectra
Supersonic Impinging Jets
Instantaneous Shadowgraph
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Microjets (dm =400m)
de =27.5 mm
Lift plate
Kulite
400 m Microjets
Control of Impinging Jets
Using Steady Microjets
Frequency(Hz)
Prms
5000 10000 15000 20000 25000 30000 35000130
140
150
160
170
180
190
No Control100 psi
37-s-nc10-h4-GP.lay
NPR 3.7 h = 4.0 Ground Plane
To date, control demonstrated for cold and hot
impinging Jets
Alvi et al. - AIAA J, 2003, 2006; JFM:2008;
Kumar et al. AIAA J 2009
Unsteady Pressures and Noise
Reduced by 4-12+ dB
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Heated Mach 1.5 Jet
Mean Axial Velocity (U/Uj)
Experiments & Simulations*
•Near-ideally expanded isothermal and
heated impinging jet matching
experimental cases
•Re ≈ 0.9 × 106 to 1.3 × 106 h/d = 5
•Laminar nozzle inflow conditions
•Fully 3-D LES using 200 million grid
points *Uzun, A. Hussaini, M. Y. et al, 2010
Iso-thermal Jet
Total velocity magnitude iso-surfaces
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Heated Mach 1.5 Jet
Experiments & Simulations
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Pressure Iso-Surfaces Associated with Vortex Ring Structures
at the Most Amplified Frequency using DMD
Identification of Coherent Structures
Uzun, A., Hussaini, M. Y. et al, 2012
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Pulsed (Micro)Actuators
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hm (h/d)m=1-2
L/dm=1-5 L
D=1.6 mm
Cylindrical cavity
H=hm+L
dm=1mm
Po
Four micro nozzles at
the bottom of the
cavity(400 μm dia)
Unsteady
Microjets Solomon et al. (AIAA J 2010, 2012)
NPR= Po/Pamb
Under expanded source
jet
Pamb
Resonance Enhanced Microjet (REM)
Actuator Schematic
Dime
Nozzle (d =1mm)
Cavity (L=1-5 mm)
Micro
nozzles
h/d (1-2)
Actuator model-Gen 1
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L/d= 1 fmin = 42 kHz f max= 58 kHz L/d= 2 fmin = 24 kHz f max= 36 kHz
•ΔL (1mm) produce Δf = 22 kHz
Actuator Frequency
Effect of L/d & NPR
L/d= 5 fmin = 6 kHz fmax= 10 kHz
•ΔL (4mm) produce Δf = 52 kHz
Configuration
Po
Source jet h
Impinging
Cavity L
Δ NPR ~ 1 changes the frequency from 6-10 kHz
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Actuator Performance Summary
idealmideal UfdSt /45.1)/(4.0 mideal dHSt
dm : diameter of source jet
Uideal : ideally expanded velocity corresponds to the source jet NPR
Δh=0.6 mm =>Δf= 20 kHz
ΔNPR=1 =>Δf= 5 kHz
Δh=0.6 mm =>Δf= 13 kHz
ΔNPR=1 =>Δf= 11 kHz
Δh=0.6 mm =>Δf= 12 kHz
ΔNPR=1.1 =>Δf= 7 kHz
Δh=0.6 mm =>Δf= 6 kHz
ΔNPR=1.1 =>Δf= 5 kHz
Cylindrical geometry
45.1
12/1
1
)/()(1)(1
24.0
dHNPRRTNPR
df o
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Phase-Conditioned Images
REM: Pulsed Actuator
Phase Averaged Instantaneous
30° - 210° ‘filling’*
240° - 0° ‘spilling’*
100 images averaged at each phase
Foster, Alvi et al.
AIAA 2011
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Uzun, A., Hussaini, M. Y. et al,
REM Actuator
Simulations & Experiments
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REM Actuator
Simulations & Experiments
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REM Actuator:Simulations
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SmartREM Actuator
8/20/2012
Source Jet
Movable Walls
Controlled by
Piezo-Stack
Actuators
Impingement Cavity
Cavity
Spreader
V
NPR = P0/Pamb P0
h
d = 1 mm
3.43kHz
3.52 kHz
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Separated Flows (& Control of)*
• Separated flow past an airfoil is
characterized by frequencies
associated with the
– wake
– shear layer (SL)
– separation bubble (SB)
– actuation (if applied)
29
• “Lock-on” describes when these components are the same or are harmonics
– Harmonics could be evidence of non-linear interactions
• Effectiveness of a control strategy may be related to the presence of lock-
on [Kotapati et al. 2001]
* Courtesy: Cattafesta, Mittal & Rowley
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Experiments Increasingly sophisticated, providing high-fidelity data
2-D/Stereo/Tomo-PIV /(Plenoptic)
=> 2 component/3component/volumetric measurements
High-speed/time resolved and Phase conditioned
Synchronous: P, V, ρ…
They provide significant physical insight into flow physics.
Difficult and expensive to run; limited conditions
Actuators A wider array of actuators with a range of control authority and bandwidth
Plasma Based (LAFPA, SJA, DBD); ZNMF (Synthtetic Jets); COMPAct, REM and more
REM: Simple, robust, scale-adapt/able, appropriate complexity & capability
Smart REM: ‘on-the-fly’ frequency control BUT more complex
Still unclear: “which actuator and under what conditions”
Parting Thoughts
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Simulations Increasingly sophisticated, provide high-fidelity data for increasingly complex flows
More rigorous validation using better experimental data
Good to excellent agreement (for some cases?)
Provide physical insight into flow physics, provide properties not easily measured.
Difficult and expensive to run; limited conditions
Rarely go beyond experimental conditions?
As we Progress Simulations+Theory used to better explore flow dynamics;l arger range of conditions
Provide guidance for active-adaptive control (that is realistic/feasible):
Temporal and Spatial requirements (freq., wavelength) for actuation and
Location (where to best place them)
Type of actuation: momentum, body force, thermal…
Provide guidance for (sparse/minimal, practical) sensing requirements
Help develop, simpler/low-order/…, practical models for closed-loop control
Plan experiments and computations together from the start
We need to improve our communication skills
Parting Thoughts