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Doctoral Research Overview
Pablo Mora
University of Cincinnati
Department of Aerospace Engineering
Cincinnati, Ohio, 45221
Acknowledgment:
This research has been sponsored by the Office
of Naval Research (ONR) through the Jet Noise
Reduction (JNR) Project under the Noise
Induced Hearing Loss (NIHL) program, as well
as the NRL 6.1 Computational Physics Task
Area.
Heated Jet Noise Facility
Facility
Hemi-anechoic chamber / high-temperature supersonic jet Remote Control Room
Supersonic Nozzles
Reduce noise levels for those exposed to high-intensity jet noise
160 90 100 110 120 130 140 150 160
110
115
120
125
130
135
140
145
OASPL
90 100 110 120 130 140 150 160
110
115
120
125
130
135
140
145
OASPL
Increasing
Temperature
Heated Jet Noise Research
Motivation
Noise increases dramatically
with jet temperature
Uc
a∞
Φ
Mach wave radiation and
Crackle noise waves
Additional noise components in high-
temperature high-speed jets
https://acoustics.byu.edu/research/beamforming-understand-military-jet-noise
Overall Sound Pressure Level [dB]
Heated Jet Noise Facility
Capabilities
Acoustic Measurements
• Free-field and surface microphones
Flow Measurements
• PIV & LDV (velocity and turbulence)
• Pressure transducers and thermocouples
• Supersonic pitot tube
Flow Visualization
• High-speed shadowgraph & schlieren
Near-field Microphone
Array on Traverse System
Aluminum oxide particle seeder
for Laser Doppler Velocimetry
• Two supply air tanks with 22,000lbs capacity at
1800psig are filled by a 360SCFM compressor
• Jet air can be heated up to 1200oF by inline
72kW and 96kW Osram Sylvania electric heaters
Concentric far-field
microphone arrays
LDV optics on a 3-axis Traverse System
Nozzle Geometries
Design Mach Number = 1.5
Rectangular Nozzle
Nozzle Geometry
Equivalent Dexit [in] AR Height [in] Width [in]
0.813 2:1 0.51 1.02
Circular Nozzles
Dexit [inches]
Base Chev M.O.C.
0.542
0.813 0.813 0.813
1.085
Baseline Chevrons Contoured
Method of Characteristics
Scale Study
Jet Over a Flat Surface
Reflections and Jet-Surface Interaction Noise
http://www.nasa.gov/larc/helicopter-drop-test-a-smashing-success
http://avioners.net/wp-content/uploads/blogger/-4CzoQlxE3ls/TpywPDKioSI/AAAAAAAAGbo/iu2wo3nSr5U/s1600/f18_afterburner_takeoff.jpg1
• To simulate ground effect • To simulate propulsion systems tightly integrated
with the airframes in futuristic aircraft designs
Flat plate with rectangular nozzle
Flat plate with circular nozzle
Shadowgraph and Schlieren
Flow Visualization
Shadowgraph Schlieren
• High-speed Flow Visualization
• Frame Rate = 25KHz
• Phantom v1610/v1210 high-speed cameras
• Jet-surface interaction study
• Strong screech instability captured
(scroll down to watch videos)
Screech Waves
0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23
100
200
300
400
500
600
700
800
Ux
ave
(m/s)
x/D
Dashed – Exp. PIV
Solid – CFD
100% ∗ 𝑻𝑲𝑬
Ujet,isen
2
TKE
Ux Ux
(m/s)
- Velocity measurements matched with results from LES simulations
* Hafsteinsson, H., Eriksson, L., Andersson, N., Mora, P., and Gutmark, E.J., “Exploration of temperature effects on the far-field acoustic radiation from a supersonic jet,” 20th AIAA/CEAS Aeroacoustics Conference, Atlanta,
Georgia, 2014, AIAA-2014-2454
High-temperature supersonic jet
1. 5 design Mach number, and Temperature Ratio of 3.0
PIV and Microphone Arrangements
Streamwise PIV
Jet Velocity and Turbulence Measurements
Acoustic Measurements
Microphone Array
X
y
55o
10o
Flow
Baseline Chevrons
SPL
St=0.2
dP/dt
Skewness
Near-field microphone array
on traverse system
• Contour plots of near-field noise statistics
• Identifying noise source location and propagation patterns
• Noise mitigation with chevrons
Traverse
[dB]
Geometry - Mesh
- Design Mach Number = 1.5
- Throat Diameter = 0.75in
- Throat Radius of Curvature = 4in
- 3D Mesh, 336875 cells
RANS
- Turbulence Model: Realizable k-epsilon
- Discretization: Second Order
- Inlet Total Temp = 700K
- Inlet Total Press = 388547 Pa
- No-slip condition
Mach Number Contours
Contoured Nozzle
Design of a Shock-Free Nozzle
Sharp-Throat
Circular Nozzle
Internal Contours designed by
the Method of Characteristics
CFD simulations before nozzle fabrication
Contact Information
Pablo Mora
(859) 468-4427
morapa@mail.uc.edu
www.linkedin.com/in/pmora
www.researchgate.net/profile/Pablo_Mora2

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Heated Jet Noise Rig

  • 1. Doctoral Research Overview Pablo Mora University of Cincinnati Department of Aerospace Engineering Cincinnati, Ohio, 45221 Acknowledgment: This research has been sponsored by the Office of Naval Research (ONR) through the Jet Noise Reduction (JNR) Project under the Noise Induced Hearing Loss (NIHL) program, as well as the NRL 6.1 Computational Physics Task Area. Heated Jet Noise Facility
  • 2. Facility Hemi-anechoic chamber / high-temperature supersonic jet Remote Control Room Supersonic Nozzles
  • 3. Reduce noise levels for those exposed to high-intensity jet noise 160 90 100 110 120 130 140 150 160 110 115 120 125 130 135 140 145 OASPL 90 100 110 120 130 140 150 160 110 115 120 125 130 135 140 145 OASPL Increasing Temperature Heated Jet Noise Research Motivation Noise increases dramatically with jet temperature Uc a∞ Φ Mach wave radiation and Crackle noise waves Additional noise components in high- temperature high-speed jets https://acoustics.byu.edu/research/beamforming-understand-military-jet-noise Overall Sound Pressure Level [dB]
  • 4. Heated Jet Noise Facility Capabilities Acoustic Measurements • Free-field and surface microphones Flow Measurements • PIV & LDV (velocity and turbulence) • Pressure transducers and thermocouples • Supersonic pitot tube Flow Visualization • High-speed shadowgraph & schlieren Near-field Microphone Array on Traverse System Aluminum oxide particle seeder for Laser Doppler Velocimetry • Two supply air tanks with 22,000lbs capacity at 1800psig are filled by a 360SCFM compressor • Jet air can be heated up to 1200oF by inline 72kW and 96kW Osram Sylvania electric heaters Concentric far-field microphone arrays LDV optics on a 3-axis Traverse System
  • 5. Nozzle Geometries Design Mach Number = 1.5 Rectangular Nozzle Nozzle Geometry Equivalent Dexit [in] AR Height [in] Width [in] 0.813 2:1 0.51 1.02 Circular Nozzles Dexit [inches] Base Chev M.O.C. 0.542 0.813 0.813 0.813 1.085 Baseline Chevrons Contoured Method of Characteristics Scale Study
  • 6. Jet Over a Flat Surface Reflections and Jet-Surface Interaction Noise http://www.nasa.gov/larc/helicopter-drop-test-a-smashing-success http://avioners.net/wp-content/uploads/blogger/-4CzoQlxE3ls/TpywPDKioSI/AAAAAAAAGbo/iu2wo3nSr5U/s1600/f18_afterburner_takeoff.jpg1 • To simulate ground effect • To simulate propulsion systems tightly integrated with the airframes in futuristic aircraft designs Flat plate with rectangular nozzle Flat plate with circular nozzle
  • 7. Shadowgraph and Schlieren Flow Visualization Shadowgraph Schlieren • High-speed Flow Visualization • Frame Rate = 25KHz • Phantom v1610/v1210 high-speed cameras • Jet-surface interaction study • Strong screech instability captured (scroll down to watch videos) Screech Waves
  • 8. 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 100 200 300 400 500 600 700 800 Ux ave (m/s) x/D Dashed – Exp. PIV Solid – CFD 100% ∗ 𝑻𝑲𝑬 Ujet,isen 2 TKE Ux Ux (m/s) - Velocity measurements matched with results from LES simulations * Hafsteinsson, H., Eriksson, L., Andersson, N., Mora, P., and Gutmark, E.J., “Exploration of temperature effects on the far-field acoustic radiation from a supersonic jet,” 20th AIAA/CEAS Aeroacoustics Conference, Atlanta, Georgia, 2014, AIAA-2014-2454 High-temperature supersonic jet 1. 5 design Mach number, and Temperature Ratio of 3.0 PIV and Microphone Arrangements Streamwise PIV Jet Velocity and Turbulence Measurements
  • 9. Acoustic Measurements Microphone Array X y 55o 10o Flow Baseline Chevrons SPL St=0.2 dP/dt Skewness Near-field microphone array on traverse system • Contour plots of near-field noise statistics • Identifying noise source location and propagation patterns • Noise mitigation with chevrons Traverse [dB]
  • 10. Geometry - Mesh - Design Mach Number = 1.5 - Throat Diameter = 0.75in - Throat Radius of Curvature = 4in - 3D Mesh, 336875 cells RANS - Turbulence Model: Realizable k-epsilon - Discretization: Second Order - Inlet Total Temp = 700K - Inlet Total Press = 388547 Pa - No-slip condition Mach Number Contours Contoured Nozzle Design of a Shock-Free Nozzle Sharp-Throat Circular Nozzle Internal Contours designed by the Method of Characteristics CFD simulations before nozzle fabrication
  • 11. Contact Information Pablo Mora (859) 468-4427 morapa@mail.uc.edu www.linkedin.com/in/pmora www.researchgate.net/profile/Pablo_Mora2

Editor's Notes

  1. Conical Nozzle with sharp throat: Double shock-cell Potential Core breaks down further upstream for heated jets Shock-cell spacing remains similar for different temperature ratios Results matching LES simulations Shear layer TKE levels increased with temperature