Molecular Sensors Temperature Sensitive Paint
36
Purdue University - School of Aeronautics and Astronautics Molecular Sensors Temperature Sensitive Paint John Sullivan Professor – School of Aeronautics and Astronautics Director - Center for Advanced Manufacturing Purdue University Special Government Employee – NASA West Lafayette, IN 47907-2022 Telephone (765)494-1279 Fax (765)496-1180 [email protected]
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Molecular Sensors Temperature Sensitive Paint. John Sullivan Professor – School of Aeronautics and Astronautics Director - Center for Advanced Manufacturing Purdue University Special Government Employee – NASA - PowerPoint PPT Presentation
Transcript of Molecular Sensors Temperature Sensitive Paint
Purdue University - School of Aeronautics and Astronautics
Molecular SensorsTemperature Sensitive
PaintJohn Sullivan
Professor – School of Aeronautics and AstronauticsDirector - Center for Advanced Manufacturing
Purdue University
Special Government Employee – NASA
West Lafayette, IN 47907-2022Telephone (765)494-1279
Fax (765)[email protected]
Purdue University - School of Aeronautics and Astronautics
Objective
• Measure temperature distribution and heat transfer distribution on a hydraulic experiment at Beihang University in the next three weeks.
Purdue University - School of Aeronautics and Astronautics
Lamp LED
CCD camera
Temperature Sensitive Paint
Luminescent
MoleculeExcitation
Emission
QuantitativeHeat Flux
Mach 10 –Tunnel 9
Feature Detection-Transition-Vortices-Separation
High-mass planetary probes are affected by transitionLaminar flow results in 2-8 times less aeroheating
Purdue University - School of Aeronautics and Astronautics
TSP -Temperature Sensitive Paint PSP - Pressure Sensitive Paint
E m is s io n
O p tica lF ilte r
E x cita tio nU V L am pL a se rF la sh L am p
D etecto rC C DP M TP D
B in d e r P o ly m er P o ro u s S o lid
L u m in esc e n t M o lecu le
Calibrate O u tputfor Tem peratureor P res s ure
Photo-physical process:-absorb a photon -transition to excited state-Oxygen quenching (PSP) or thermal quenching (TSP)=> Pressure and/or temperaturedependent luminescent intensityand luminescent lifetime
Purdue University - School of Aeronautics and Astronautics
Temperature Sensitive Paint High temperature causes non-radiative decay “thermal quenching”• Obeys Arrhenius relation: For limited temp. range
lT T Tref ref
nI(T)
IERref g( )
1 1
• Similar molecules to PSP, but in oxygen impermeable binder
IT
toC
~1 5%
0
Purdue University - School of Aeronautics and Astronautics
Luminescent Paint (TSP/PSP)
coated model
Excitation
short-pass filter
excitation source
Acquisition
photodetector
long-pass filter
Iref/IP/Pref
Data Processing
Iref/I
P/Pref
calibration
surface maplow costeasy to apply
Purdue University - School of Aeronautics and Astronautics
Current State of the Art of PSP/TSP
•Temperature Sensitive Paint–T= -196 C to 200 C M=.01 to 10–Accuracy 1 Degree Centigrade Resolution <. 01 C–Time Response 1 sec Typical (<1 ms demonstrated)•Pressure Sensitive Paint–P=.001 to 2 atm M=.05 to 5–Accuracy 1.0 mbar Resolution .5 mbar–Time response .5 sec Typical
( 1 microsec demonstrated)
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Basic Photophysics
Purdue University - School of Aeronautics and Astronautics
Jablonski Diagram
f ph kic kisc
kisc
S0
T1S1
(triplet state)
(ground state)
(singlet state)
vibration intersystem crossing (ISC)
internal conversion (IC)
fluorescence phosphorescenceexcitation
kic
kic
S2
Sn
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Data Reduction Methods
Purdue University - School of Aeronautics and Astronautics
Data Reduction Methods
• Intensity Reference• Multi-luminophore Paint• Time Based Methods
Purdue University - School of Aeronautics and Astronautics
Intensity Reference
• Wind Off / Wind On• Corrects for non-uniform model
motion, nonuniform concentration
ref
refref
ppTBTA
II
)()(
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Multi-luminophore Paint
• Luminescent molecules with different pressure and temperature sensitivities, overlapping excitations and different emission wavelengths
Purdue University - School of Aeronautics and Astronautics
Time Based Methods
• Direct Decay• Phase Based
Purdue University - School of Aeronautics and Astronautics
Direct Decay• Modulated Light Source
– Pulse, Sine wave, square wave• Point Systems• Camera Systems with image intensifier
Time
Intensity
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Phase Based• Lock-in Amplifier• FLIM (Fluorescent Lifetime Imaging Method)
t(arb)0 5 10 15
ampl
itude
(arb
)
0
1
2
3
ExcitationEmission
ref
PPD(t)C(t)ref
tan()=
Purdue University - School of Aeronautics and Astronautics
Temperature Sensitive PaintTSP
Same or similar Luminophore as in PSP
Oxygen impermeable binder
Purdue University - School of Aeronautics and Astronautics
Temperature Sensitive PaintThermographic Phosphors Infrared CameraTemperature Sensitive Liquid CrystalsArray of Thermocouples
Global Surface Temperature Measurements
Toolbox
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Temperature Sensitive Paint
• Surface Temperature– Correction for Pressure Sensitive Paint
• Transition Detection• Quantitative Heat Transfer• Shear Stress - Heat transfer Analogy
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Temperature Sensitive Paint Calibrations
Purdue University - School of Aeronautics and Astronautics
TSP Time Response
ch
Laser Pulse Heating
density of polymer c specific heat paint thickness h convection heat transfer coefficient
Purdue University - School of Aeronautics and Astronautics
Ruthenium based TSP tris(2,2’-bipyridyl)ruthenium - Ru(bpy)
Wavelength (nm)
200 300 400 500 600 700 800 900
Inte
nsity
(arb
uni
ts)
0
100
200
300
400
Excitation Emission
UVUVlamplamp
BlueBlueLEDs LEDs
Greenlaser
Excitation and Emission Spectrum of a Ruthenium Based Paint
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EuTTA based TSP Europium III Thenoyltrifluoroacetonate EuTTA
Excitation Spectrum Emission Spectrum
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EuTTA in Model Airplane Dope
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Applications Temperature Sensitive Paint
(TSP)
• Transition Detection– Low Speed– Cryogenic Wind Tunnel
• Quantitative Heat Transfer– Camera Based – M=10– Scanning System Laser Spot Heating
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Transition DetectionLow Speed
TSP –EuTTA in dope
Wing heated with photographic spot lampsto ~20 C above ambient
8 bit Camera
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Raw Image(false color)
ResultsLow Speed Transition
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Quantitative Heat Transfer
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Heat Transfer Data Reduction• Model make out of Thermally Insulating material• Measure
• Match the temperature to analytic solution for a semi-infinite body (Cook-Felderman)
• Make Model out of a Conductor with a thin insulator on the surface
)(tTsurface
)(/ modelsurface TTkq
Method 1
Method 2
1 model k
1 model k
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Tunnel #9M=10Run time ~1.0 sec1.5 meter Diameter
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TSP - EuTTA in dopeMetal modelInsulating Layer – mylar film (model airplane monokote) 50 microns thick
Raw Image
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Purdue University - School of Aeronautics and Astronautics
Purdue University - School of Aeronautics and Astronautics
Mach-6 Quiet Tunnel
National Aeronautics and Space Administration
www.nasa.gov 35
-1 -0.5 0 0.5 1 1.5 2 2.5 3 3.5 4 4.5-1
-0.8
-0.6
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1x 10
4
Qpa
ints
[W/m
2 ]
run8.tif
-1 -0.5 0 0.5 1 1.5 2 2.5 3 3.5 4 4.5-1
-0.8
-0.6
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1x 10
4
QHF
S-4 [W
/m2 ]
HIFiRE-5 ModelQuiet Flow, α=0
Re = 2.6*106 /ft
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Temperature profile of machining acquired with TSP sensor (Rubpy)
350 400 450 500 550 600
250
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450
20
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Area of
Interestworkpiece
Cutting toolChip
degree C
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Area of
Interestworkpiece
Cutting toolChip
350 400 450 500 550 600
250
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20
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Area of
Interest
350 400 450 500 550 600
250
300
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400
450
20
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Area of
Interestworkpiece
Cutting toolChip
degree C
Temperature profiles from TSP measurement of grinding stainless steel at spark-out condition
TSP Measurements ofMaterial Temperature
