Modeling Jet-A Vaporization in a Wing Fuel Tank · Modeling Jet-A Vaporization in a Wing Fuel Tank...
Transcript of Modeling Jet-A Vaporization in a Wing Fuel Tank · Modeling Jet-A Vaporization in a Wing Fuel Tank...
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DHAVAL D. DADIA
Modeling Jet-A Vaporization in a Wing Fuel Tank
Constantine Sarkos, Richard HillSteven Summer, Robert I. Ochs
Federal Aviation AdministrationAtlantic City Airport, New Jersey
Dr. C.E. Polymeropoulos, Dr. Tobias RossmannRutgers, The State University of New JerseyPiscataway, New Jersey
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Motivation
Combustible mixtures can be generated in the ullage of aircraft fuel tanks.
Work currently being done to reduce flammability of wing tanks.
The proposed model will predict existing ullage concentrations during typical ground and flight conditions.
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Current Work
Predicting the influence of the following parameters in the development of flammable mixtures in the ullage.
Surface temperature
Fuel Temperature
Ullage temperature
Pressure
Amount of fuel in the tank
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Overview
Description of modelMass Transfer Considerations
Assumptions
Heat and Mass Conservation Relations
Heat and Mass Transfer Correlations
Jet-A characterization
ResultsAltitude Chamber
Air Induction Wind Tunnel
Flight Test NASA 747 SCA
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Mass Transfer Considerations
Natural convection and forced convection heat and mass transfer
Liquid vaporization
Vapor condensation
Variable ambient pressure and temperature
Vented Tank
Multi-component fuel
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Assumptions for Estimating Ullage Vapor Composition
Well mixed gas and liquid phasesBuoyancy induced mixing
Quasi-steady transport using heat transfer correlations
Low evaporating species concentrations
Time dependent values of liquid fuel, and tank wall temperatures are known.
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Supplementary Assumptions
Gases and vapors follow ideal gas behavior.
Tank pressure is the same as the ambient pressure.
Condensate layer forms on the tank walls.
Condensation occurs at the tank wall temperature.
No liquid droplets in the ullage and no liquid pool sloshing.
Fuel consumption is neglected.
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Heat and Mass Conservation Relations
Fuel Species Evaporation and Condensation
Henry’s Law
Species vapor pressure was calculated using Wagner’s or Frost-Kalkwarf-Thodos equations.
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Heat and Mass Transfer Correlations
Heat Transfer and Mass Transfer Correlations used:Forced Convection over a flat plate
Various modes of natural convection
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Jet-A Characterization
Jet-A fuel can be characterized in terms of a number of n-alkane hydrocarbons determined by gas chromatography.
This approach reduces the number of components in the fuel from 300 to 16 (c5-C20 alkanes).
This output of the approach is in terms of mole fractions.
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ALTITUDE CHAMBER TEST
WIND TUNNEL TEST
FLIGHT TEST
EXPERIMENTAL AND COMPUTATIONAL RESULTS
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Altitude Chamber Test Setup
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Experimental Results
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Experimental Results
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Experimental Results
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Experimental Results
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Experimental Results
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Wind Tunnel Experimental Setup
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Wind Tunnel Test
Test Type
•Aluminum Wing Tank
•Mass Loading:40%
•Heat Setting: 1
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Wind Tunnel Test
Test Type
•Aluminum Wing Tank
•Mass Loading:40%
•Heat Setting: 2
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Wind Tunnel Test
Test Type
•Aluminum Wing Tank
•Mass Loading:60%
•Heat Setting: 1
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Wind Tunnel Test
Test Type
•Aluminum Wing Tank
•Mass Loading:80%
•Heat Setting: 1
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Flight Test NASA 747 Experimental Setup
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Flight Test
Experimental THC values not recorded after about 10,000 seconds.
Altitude Chamber correlations used.
Normal input data set used.
Flight test THC data was measured using NDIR
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Flight Test
Altitude Chamber correlations used.
Normal input data set used.
Data does not match computational data once the plane ascends.
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Flight Test
Altitude Chamber correlations used.
Normal input data set used.
Data does not match computational data once the plane ascends.
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Flight Test
Difference between the fuel temperature and bottom surface temperature.
Bottom surface temperatures used as in put instead of fuel temperature
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Flight Test
Altitude Chamber correlations used.
Bottom surface temperature used in the input instead of fuel temperature.
Computational data follows the trend of the experimental data.
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Flight Test
Altitude Chamber correlations used.
Bottom surface temperature used in the input instead of fuel temperature.
Computational data follows the trend of the experimental data.
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Conclusion
Computational model validated by three different experimental tests.
Computational model follows the general trend of the experimental results.
Disagreement in flash point value of fuel in experimental cases caused due to model assumption.
Disagreement in results in the flight testDue to cold spots in the wing and thermal layering of the fuel.
Due to difference in measurement techniques. NDIR vs. FID
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Questions?