Thermal Energy Storage Devices - NASA
Transcript of Thermal Energy Storage Devices - NASA
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TFAWS-2006
Thermal Energy Storage Devices
Mike Pauken, Nick EmisJet Propulsion Laboratory
August 8, 2006TFAWS 2006
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TFAWS-2006
Why Thermal Energy Storage?
• Dampen effects of periodic boundary conditions on low thermal mass objects.– Spacecraft on orbit– Spacecraft on planetary surfaces such as Mars– Terrestrial Applications
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Periodic Boundary Condition
Thermal Response without Storage
Thermal Response with Storage
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Why Thermal Energy Storage?
• Reduce heating rates of light weight, high powered devices on short duration missions to extreme environments– Landing on Venus Surface– Atmospheric probes to the Gas Giant Planets
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Boundary Condition
Thermal Responsewithout StorageThermal Responsewith Storage
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Back-of-the-Envelope Analysis
• Five basic equations describe Thermal Energy Storage Performance:– Conservation of Mass
• Mass of Phase Change Material, Filler Material and Casing– Conservation of Energy
• Maximum energy storage capacity– Temperature Range Constraint
• Temperature gradient between component and melting temperature
– Computation of Equivalent Conductance• Net conductance of filler plus PCM.
– Additive Area Relationship• Heat flow cross-sectional area of PCM and filler materials
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Back-of-the-Envelope Analysis
{1} Mass = (ρPCMAPCM + ρFAF )t + ρC(2AT + 4tAT0.5)tC
{2} EMAX = ρPCMAPCM·t·hf + [ρFAFCP-F + ρPCMAPCMCP-PCM]t/2(Tcomp - Tmelt)
{3} Q = kTAT(Tcomp - Tmelt)/t
{4} kTAT = kPCMAPCM + kFAF
{5} AT = APCM + AF
t
tc PCM Filler Case
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Back-of-the-Envelope Analysis
• Sample Results from Simple Analysis
• Area Ratio is:Filler area/Total Area
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10-2
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Area Ratio
Log
Sca
le
Mass (kg)Mass (kg)
Thickness (m)Thickness (m)
Temperature Excursion (C)Temperature Excursion (C)
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Thermal Modeling
• Examine more complex shapes/geometry than rectangular boxes
• Evaluate 2-D and 3-D effects• Utilize more accurate specific
heat data (as a function of temperature and phase)
• Shown is a model of a simple unit with aluminum fins
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Thermal Modeling
• Thermal models make it easy to model complex geometries or configurations.
• Module w/ graphite shell, Rubitherm-35 PCM and copper foam filler.
• Copper heater plate mounted on top
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Phase Change Materials
• Conducted search of phase change materials with high heats of fusion.
• Paraffins are most common melt material.• Lithium Nitrate has one of the highest heats of fusion
and has a high density especially compared to paraffins.– Measured hf for LiNO3 was ~287 kJ/kg
– Most paraffins range from 170 to 230 kJ/kg
– Density of LiNO3 is ~1.5 g/cc
– Most paraffins are around 0.8 g/cc
• Implication: For a given container size, LiNO3 has more than double the heat capacity of a paraffin!
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Lithium Nitrate Developments
• LiNO3 is more difficult to handle than paraffins:– Must add water to it to form LiNO3-3H2O
– It readily absorbs water from ambient air and reduces heat capacity.
• Must keep it sealed until loaded into Thermal Storage Module
– Melting point is about 30°C, freezing point is around -5°C.
• This phenomenon is called subcooling.
• Can be reduced with a catalyst: add 1% by weight of ZnNO3
• With catalyst, freezing point is around 28°C.
• LiNO3 appears to be compatible with aluminum, no corrosion products have been observed.
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Heat Capacity Measurements
• Heat capacity of LiNO3was measured because literature data in both solid and liquid phases were incomplete
• Measurements were made using Differential Scanning Calorimetry– This tends to produce
broader melting temperatures than observed in bulk samples.
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10 15 20 25 30 35 40 45 50Temperature (ºC)
Cp
(J/g
-ºC
)
run1
run2
run3
average
Specific heat measurements of LiNO3
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Filler Material Developments
• Aluminum fins have traditionally been used as the filler material for conducting heat into the melt material.
• Carbon foam, trademarked name “Pocofoam”, has been used successfully as a filler material with paraffin loaded storage modules by others.
• Carbon foam is hydrophobic and will not absorb water based materials such as LiNO3-3H2O.
• Adding a small amount of surfactant to LiNO3-3H2O solves the absorption problem.
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Pocofoam Testing
• Pocofoam floats in untreated water as shown in top photograph demonstrating hydrophobia.– This means LiNO3 would not be
absorbed into Pocofoam
• Adding surfactant to the water causes immediate absorption by the Pocofoam as shown in bottom photograph and sinks.– Same trick works for water spiders!
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Prototype Design Features
• A phase change thermal energy storage module was designed with the following features:– A stiff lid to make a stable mounting surface for accommodating
electronic components (we just used a heater for testing).– A thin backplate to act as a diaphragm to reduce pressure
variations as LiNO3 changed phase.– Carbon foam filler core– LiNO3-3H20 plus 1% zinc nitrate plus surfactant
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Prototype Components
LIDENCLOSURE
POCO Foam
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Plexiglas Model
• Before making the aluminum casing module, a Plexiglas unit was fabricated to verify filling because of the hydrophobic nature of Pocofoam.
Completely filled moduleLiquid line evident during filling
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Aluminum Casing Prototype
• Photographs of the completed phase change module
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Thermal Testing of Prototype
• Power levels applied to unit: 15, 30, 60 and 90 watts• Tests ran from 0 to 90ºC• Tests repeated 5 times each to check consistency• Module was placed inside insulated box to reduce heat
leaks.– Observed approximately 8 watts of heat leak through insulation
Test Set up at Vendor’s facility
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Test Results
PCM Tests Comparing Different Heat Loads
Elapsed Time, (min)
Tem
pera
ture
, (C
)
7 Watts (15)
22 Watts (30)
52 Watts (60)
82 Watts (90)
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Correction for Heat Leak
• Energy absorbed during melt should not change with power.
• Observed 15 Watt case took much longer to melt than expected.
• Estimated 8 Watt heat leak and corrected the melt energy to be around 40 W-hr/kg.– If paraffin were the melt
material, melt energy would be around 20-30 W-hr/kg
Energy Absorbed by Phase Change ModuleDuring Melt Phase
Power Level, (W)E
nerg
y (W
-hr)
Corrected for 8 Watt heat leak
Uncorrected Data
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Conclusions
• An improved Thermal Energy Storage Device suitable for spacecraft applications has been developed.
• The melt material was lithium nitrate and had a melt temperature around 30C.
• The freezing point subcooling was reduced to only 2C with the addition of 1% zinc nitrate.
• Pocofoam was used as the filler material, hydrophobic effects were eliminated using a surfactant.
• Energy storage capacity of unit is 30% to 100% greater than a paraffin filled unit.
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Acknowledgments
• This work was performed by Jet Propulsion Laboratory, California Institute of Technology under contract with the National Aeronautics and Space Administration.
• Fabrication and testing of the thermal storage device was performed by XC Associates, Stephentown, NY.