Vaporization of JP-8 Jet Fuel in a Simulated Aircraft Fuel Tank ...

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Fuel to Air Mass Ratio 0.06 0.05 0.04 0.03 0.02 0.01 0 LFL Range Increasing Liquid Temperature 0 2000 4000 6000 8000 10000 12000 Time, seconds TLIQ TLIQ+5 TLIQ+10 Figure 6.13. Liquid fuel temperature effects on flammability using the FAR rule [26]; flight profile test up to 30,000’ altitude. Le Chatelier's Ratio 1.8 1.6 1.4 1.2 1 0.8 0.6 0.4 0.2 0 Le Chatelier's Flammability Limit Increasing Liquid Temperature 0 2000 4000 6000 8000 10000 12000 14000 Time, seconds TLIQ TLIQ+5 TLIQ+10 Figure 6.14. Liquid fuel temperature effects on flammability using Le Chatelier’s flammability rule [27]; flight profile test up to 30,000’ altitude. 61
Fuel to Air Mass Ratio 0.05 0.04 0.03 0.02 0.01 0 LFL Range Increasing Mass Loading 0 2000 4000 6000 8000 10000 12000 Time, seconds M.L.=300 kg/m3 M.L.=31.5 kg/m3 M.L.=0.5 kg/m3 Figure 6.15. Mass loading effects on flammability using the FAR rule [26]; flight profile test up to 30,000’ altitude. Le Chatelier's Ratio 1.2 1 0.8 0.6 0.4 0.2 0 Le Chatelier's Flammability Limit Increasing Mass Loading 0 2000 4000 6000 8000 10000 12000 14000 Time, seconds M.L.=300 kg/m3 M.L.=31.5 kg/m3 M.L.=0.5 kg/m3 Figure 6.16. Mass loading effects on flammability using Le Chatelier’s flammability rule [27]; flight profile test up to 30,000’ altitude. 62
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DOT/FAA/AR-TT09/42 Air Traffic Orga
Page 3 and 4:
1. Report No. DOT/FAA/AR-TT09/42 4.
Page 5 and 6:
ABSTRACT OF THE THESIS VAPORIZATION
Page 7 and 8:
DEDICATION This thesis is dedicated
Page 9 and 10:
5.0 RESULTS 32 5.1 Validation Tests
Page 11 and 12:
5.7 JP-8 fuel vaporization at sea l
Page 13 and 14:
LIST OF TABLES Table Page 2.1 Compa
Page 15 and 16:
develop procedures to lessen the li
Page 17 and 18:
When it was determined that a CWT e
Page 19 and 20:
1.3 Objectives of the Thesis The ul
Page 21 and 22:
has more additives, such as an anti
Page 23 and 24: equilibrium is dynamic in nature, b
Page 25 and 26: factor in making these calculations
Page 27 and 28: Volume Fraction, % 30 25 20 15 10 5
Page 29 and 30: 0.035±0.004 at 0°C [26]. The publ
Page 31 and 32: Raleigh numbers which were of order
Page 33 and 34: loading of fuel and be subjected to
Page 35 and 36: pressures. The heaters in the pump
Page 37 and 38: Figure 3.1. View of top surface of
Page 39 and 40: the tank and the ullage vapor conce
Page 41 and 42: attempted, but provided inaccurate
Page 43 and 44: pump that could draw samples from a
Page 45 and 46: 5.0 RESULTS When inputting the expe
Page 47 and 48: etween measured and predicted value
Page 49 and 50: 5.1.2 Isooctane Fuel Vaporization T
Page 51 and 52: higher altitudes, as continuous sam
Page 53 and 54: Temperature, Deg. F. 140 120 100 80
Page 55 and 56: Temperature, Deg. F. 70 60 50 40 30
Page 57 and 58: % Propane Equivalent 2 1.5 1 0.5 0
Page 59 and 60: % Propane Equivalent 3 2.5 2 1.5 1
Page 61 and 62: liquid fuel the mass of fuel evapor
Page 63 and 64: In the beginning of the test, the l
Page 65 and 66: 6.2 Flammability Assessment 6.2.1 F
Page 67 and 68: average measured liquid temperature
Page 69 and 70: Fuel to Air Mass Ratio 0.05 0.045 0
Page 71 and 72: 6.2.2 Fuel Tank Under Varying Ambie
Page 73: Fuel to Air Mass Ratio 0.045 0.04 0
Page 77 and 78: temperature measurements would be r
Page 79 and 80: Which is appropriate for Raleigh nu
Page 81 and 82: d dt ( mg c pgTg ) = hb Ab ( Tb −
Page 83 and 84: APPENDIX C: EXPERIMENTAL FUEL FLASH
Page 85 and 86: 13. Fuel Flammability Task Group, A
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