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Flow-Induced Noise Technical Group
Center for Acoustics and Vibration
Spring Workshop
May 14, 2012
Presented by:
Dean E. Capone, Group Leader
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Overview
• The mission of the Flow-Induced Noise Group of the Center for
Acoustics and Vibration is the understanding and control of
acoustic noise and structural vibration induced by fluid flow.
• Research Areas
– Numerical simulations of high speed jet noise
– Experimental jet noise
– Marine renewable energy turbine noise
– Acoustic Detection of Cavitation
Numerical Simulations of High Speed Jet Noise
Philip J. Morris
Boeing/A. D. Welliver Professor
Department of Aerospace Engineering
CAV Workshop
May 2012
Jet Noise Research Projects
Noise from dual stream jets (Pratt & Whitney) – Swati Saxena (RA)
Noise reduction in supersonic jets (ONR) – Dr. Yongle Du & Nidhi Sikarwar (RA)
Nonlinear propagation of jet noise (Boeing) – Don Hyatt (RA)
LES for high speed jets (NAVAIR) – Dr. Yongle Du
Unsteady loading in nozzles with UAV applications (Pratt & Whitney) – Michael Lurie (RA)
Forward Flight Analysis of Single Stream Jet Mj = 0.9, TTR = 1.0, Mcf = 0.0 to 0.28
Q Iso-surfaces and FW-H surface
Potential core length comparison Centerline Turbulence Intensity
Centerline mean axial velocity OASPL (dB) variation with polar angle
Flow Visualization of Military- Style Nozzle Flows
Time-averaged solution
Experiment
Munday et al, 2008
Prediction
Baseline nozzle jet, Mj=1.56
Flow Visualization
Unsteady Jet Flow and Noise Radiation
Baseline, Mj=1.47 cold jet Baseline, Mj=1.47 hot jet
Color: Density gradient Gray: Time derivative of static pressure
Simulation of Bypass Cooling Flow
Preliminary reults of the Mj=1.47 jet with bypass cooling flow
Temperature Vorticity magnitude
Noise Source Identification Using Virtual Beamforming
Noise source locations
Mj=1.47, unheated jet
Experiment
Mj=1.47, unheated baseline jet
Nonlinear propagation from Distributed Noise Sources
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2 212
: 0
( ): 0
( ): 0
( ) ( ): 0
: ( 1) ( )
u vContinuity
t x y
u u p uvx momentum
t x y
v uv v py momentum
t x y
E uE up vE vpEnergy
t x y
State p E u v
Initial and time dependent conditions can be enforced near the center of the domain to drive waves. This figure shows the result of Gaussian Distribution of pressure and density.
Numerical and Computational Approach
The system of equations is nonlinear. Without damping, shocks will inevitably be produced. To cope with the numerical issues this introduces, a non-oscillatory scheme is used. A distributed source can be used to approximate noise from a jet, with solution resolved in the plane normal to the jet axis These methods lend themselves to parallel computing, and is currently able to be run on nVidia graphics processing units via the CUDA programming language.
4 4.1 4.2 4.3 4.4 4.5 4.6 4.7 4.8 4.9 50.94
0.96
0.98
1
1.02
1.04
1.06
1.0133
x 105
X: 4.673
Y: 1.013e+005
meters
Pre
ssure
(P
a)
Pressure
File: CAV Seminar May 2012.pptx
Aeroacoustic Experiments on
Supersonic Jets Exhausting from
Military-Style Nozzles
Russell Powers and Dennis K. McLaughlin
Department of Aerospace Engineering
Penn State University
Presented at CAV Seminar
May, 2012
File: CAV Seminar Apr 2010.pptx
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Technical approach
The Current Objectives are to examine several modifications to
supersonic nozzles to produce significant noise reduction.
Acoustic measurements are conducted in the anechoic
chamber: dimensions: 5 6 2.8 m, cut-off frequency: ~250 Hz.
Penn State High-Speed Jet Noise Facility
Helium canisters
File: CAV Seminar Apr 2010.pptx
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Technical approach Nozzle Design and Manufacture
- Nozzles Fabricated Using Rapid Prototyping Technology.
- Several different nozzles manufactured in this Study, which
use interior hard walled corrugations.
File: CAV Seminar Apr 2010.pptx
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Experimental Results Two Corrugations
- Results Shown for an over-expanded jet with
the nozzle pressure ratio = 3.0 and TTR = 3.0
- Narrowband spectra at several polar angles
- Shadowgraph images which show the
flow and shock structure within the jet
File: CAV Seminar Apr 2010.pptx
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Experimental Results Three Corrugations
- The variation of the overall sound pressure
level (OASPL) is shown in addition to
narrowband spectra.
- Notice the high frequency reduction at low
polar angles.
- Azimuthal directivity at low polar angles,
but very little difference in the sideline and
forward arc.
Successful
noise reduction
File: CAV Seminar Apr 2010.pptx
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Experimental Results Six Corrugations
- The variation of the overall sound pressure
level (OASPL) is shown in addition to
narrowband spectra.
- Notice the high frequency reduction at low
polar angles.
- Less azimuthal directivity than for three
corrugations
Acoustics for a river-current turbine
Erick Johnson, Matt Barone Sandia National Laboratories
Michael Jonson, John Fahnline
Pennsylvania State University, Applied Research Laboratory
Motivation
• Baseline noise evaluation
– Turbine designed through straight transfer of wind knowledge
– Grounding for future improvements
• What is the environmental impact?
– Marine animal communication/behavior
– Barotrauma
CHAMP (Combined HydroAcoustic Modeling Program)
• A Penn State model
– Used extensively in marine propulsion systems
• Requires modal (structural) and CFD analyses
Blade Rate Noise Turbulence Ingestion Noise
Motor Noise Flow Noise and BBVN
Wake Harmonic Analysis
Unsteady Forces and Moments
(UFAM)
Structural Acoustic Transfer Function
Inflow Turbulence Characteristics
Unsteady Force Spectrum (TING)
Finite-Element Analysis (NASTRAN)
Boundary Element Analysis (POWER)
CFD RANS
Electromagnetic FE analyses
Self-generated Turbulence Statistics (TBL, Vortex Shedding, tip flows)
Boundary Element Analysis (POWER)
EM force harmonic content
Finite-Element Analysis (NASTRAN)
Boundary Element Analysis (POWER)
Finite-Element Analysis (NASTRAN)
Machinery Noise
Gear meshing and bearing analyses
Tonal loads and enforced
displacements
Finite-Element Analysis (NASTRAN)
Boundary Element Analysis (POWER)
Design Turbine: 3-bladed, stall regulated 5 m diameter rotor 0.6m diameter hub
Blade Material and Loading: Material Safety Factor = 2.5 Load Safety Factor = 1.5 Fiberglass/epoxy: E = 35 GPa σmax = 580 MPa
Max Thrust = 2.5 m/s (BEM)
Operating Conditions: Design Speed = 2.0 m/s
BEM (Blade Element-Momentum) Theory
• Approximate calculation for performance and loading of a turbine
– Relies on lift/drag tables for each foil
• Can be used to optimize a blade design from operating conditions
– Does not directly give stress results
– Still need manufacturability and hub attachment
Stress/Modal Results
28.91 Hz 65.60 Hz
80.51 Hz 151.91 Hz
Blade does not break! (at least not under static load)
Modal cont’d (1)
Mode # In Vacuo Interior Exterior
Both
Interior and
Exterior
1 29.2 Hz 24.1 Hz 12.5 Hz 12.0 Hz
2 65.9 Hz 57.5 Hz 61.4 Hz 59.9 Hz
3 154.0 Hz 68.9 Hz 34.2 Hz 32.1 Hz
4 183.2 Hz 109.5 Hz 69.7 Hz 64.1 Hz
5 266.7 Hz 208.4 Hz 160.8 Hz 178.3 Hz
6 391.5 Hz 182.7 Hz 117.7 Hz 106.3 Hz
7 416.7 Hz 257.3 Hz 183.3 Hz 158.3 Hz
8 444.6 Hz 475.3 Hz 361.6 Hz 393.9 Hz
Modal cont’d (2)
• Modal radiation efficiencies
– Decompose modes into monopole/dipole components
–
Monopole indicates a “breathing” of the blade
Acoustic results
0
20
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1 10 100
Sou
nd
Pre
ssu
re L
eve
l, d
B r
e 1
µP
a @
1m
in 1
Hz
ban
ds
Frequency, Hz
Total Noise
Leading Edge Forcing Function
Trailing Edge Forcing Function
Total noise: 128 dB re 1µPa @ 1m
By: Daniel Perlitz and Lee Thompson
August 23, 2011 The Pennsylvania State University-Applied Research Laboratory
The Pennsylvania State University
August 23,2011
Student Research Objective: Investigate acoustic localization techniques for cavitation.
Time Delays between Microphones in the Anechoic Chamber
Am
plitu
de
0.82 0.83 0.84 0.85
time(s)
time(s)
Microphone 1
Microphone 3
Microphone 2
Direct Signal Path
Reflected Signal Path
The Pennsylvania State University
Preliminary testing in ARL’s anechoic chamber in air
Noise source location was determined using an array of three microphones
Time Delays between Microphones in the Anechoic Chamber
August 23,2011
The Pennsylvania State University
August 23,2011
Processing of Acoustic Signals from a Reverberant Environment
A filter is used to eliminate spurious noise
The data is time-windowed to isolate the direct path signal
Produced cavitation with a cross flow rod in a twelve inch water tunnel Took images using a Basler A500K high speed camera
The Pennsylvania State University
August 23,2011
baslerweb.com
The Pennsylvania State University
Images are processed so that each bubble can be identified and analyzed
August 23,2011
The Pennsylvania State University
August 23,2011
Minna Ranjeva developed a system to produce cavitation in a water tank using a laser
A lens focuses the laser beam and a mirror deflects it into the tank
Perform cavitation localization in the 12-inch diameter water tunnel Nozzle cavitation
Hydrofoil cavitation
The Pennsylvania State University
August 23,2011
computationalfluiddynamics.com
Questions?