03-12-02IASFPWG – Seattle, WA Fuel Tank Ignition Experiments at Reduced Oxygen Concentrations...
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Transcript of 03-12-02IASFPWG – Seattle, WA Fuel Tank Ignition Experiments at Reduced Oxygen Concentrations...
![Page 1: 03-12-02IASFPWG – Seattle, WA Fuel Tank Ignition Experiments at Reduced Oxygen Concentrations International Aircraft Systems Fire Protection Working Group.](https://reader030.fdocuments.in/reader030/viewer/2022032517/56649cb85503460f9497f38d/html5/thumbnails/1.jpg)
03-12-02IASFPWG – Seattle, WA
Fuel Tank Ignition Experiments at Reduced Oxygen Concentrations
International Aircraft Systems Fire Protection Working GroupSeattle, WAMarch 12 – 13, 2002
Steve SummerProject EngineerFederal Aviation AdministrationFire Safety Section, AAR-422
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03-12-02IASFPWG – Seattle, WA
Where’s the final report?
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03-12-02IASFPWG – Seattle, WA
Where’s the final report?
After October conference, the decision was made to run some more
experiments at a near-stoichiometric concentration, as well as some other test
sets.
![Page 4: 03-12-02IASFPWG – Seattle, WA Fuel Tank Ignition Experiments at Reduced Oxygen Concentrations International Aircraft Systems Fire Protection Working Group.](https://reader030.fdocuments.in/reader030/viewer/2022032517/56649cb85503460f9497f38d/html5/thumbnails/4.jpg)
03-12-02IASFPWG – Seattle, WA
Objectives
Determine the Lower Oxygen Content (LOC) at altitudes ranging from 0 – 40 kft.• What is the O2 concentration, below which ignition of
the ullage fuel vapors will not occur?
• How does this effect fuel tank inerting requirements?
Measure ignition pressure at several ‘key’ test points.
Determine the Lower Explosion Limit (LEL) of JP-8 vapors at 0 and 38 kft.
![Page 5: 03-12-02IASFPWG – Seattle, WA Fuel Tank Ignition Experiments at Reduced Oxygen Concentrations International Aircraft Systems Fire Protection Working Group.](https://reader030.fdocuments.in/reader030/viewer/2022032517/56649cb85503460f9497f38d/html5/thumbnails/5.jpg)
03-12-02IASFPWG – Seattle, WA
Facilities – Pressure Chamber
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03-12-02IASFPWG – Seattle, WA
Facilities – Pressure Chamber353 ft3 pressure vessel
• Working pressure of 650 psi.• Attached vacuum pump used to
evacuate chamber to reduced pressures seen at altitude.
• Not capable of simulating temperatures seen at altitude.
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03-12-02IASFPWG – Seattle, WA
Facilities - LOC Test Article 9 ft3 simulated fuel tank placed inside of
vessel equipped with:• Bottom surface heaters.• 12 thermocouples.• 2 piezoresistive pressure transducers mounted
behind sintered porous metal discs.• Interchangeable pressure relief mechanism.
¼-in. aluminum plate. Foil diaphragm.
• Ignition source. 2 tungsten electrodes powered by 10 kV transformer
operating at ~20 mA, providing 200 J/s
![Page 8: 03-12-02IASFPWG – Seattle, WA Fuel Tank Ignition Experiments at Reduced Oxygen Concentrations International Aircraft Systems Fire Protection Working Group.](https://reader030.fdocuments.in/reader030/viewer/2022032517/56649cb85503460f9497f38d/html5/thumbnails/8.jpg)
03-12-02IASFPWG – Seattle, WA
Apparatus – LOC Testing
TH C A nalyzer
R igh t Test Track
Left Test Track
1 0 m P ressu re Vesse l
3 Ana lyze r Byp a ss
Sa m p le Line O A nalyzer
2
H eaterH eater
Spark Source
Fan
= Therm ocouple Feed through
N L ines2
H ouse A ir L ine
![Page 9: 03-12-02IASFPWG – Seattle, WA Fuel Tank Ignition Experiments at Reduced Oxygen Concentrations International Aircraft Systems Fire Protection Working Group.](https://reader030.fdocuments.in/reader030/viewer/2022032517/56649cb85503460f9497f38d/html5/thumbnails/9.jpg)
03-12-02IASFPWG – Seattle, WA
Apparatus – LOC Testing
R ig h t T /C T re eL e ft T /C T re e
L iq u id J P -8 F u e lF u e l P a n
= T h e rm o c o u p le B e a d
6.0"
6.0"
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03-12-02IASFPWG – Seattle, WA
Ullage Vapor Sampling
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03-12-02IASFPWG – Seattle, WA
Ullage Vapor Sampling
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03-12-02IASFPWG – Seattle, WA
Test Program JP-8 LOC Tests
• Mass Loading ~ 4.5 kg/m3
• Ambient pressure corresponding to altitudes of 0, 10, 20, 30 and 38 kft
• Ullage oxygen concentrations ranging from 21% to below the determined LOC
• Tests conducted with two different pressure relief mechanisms
¼-in. aluminum plate– Ignition = movement of plate
Foil diaphragm – Ignition = rupture of foil
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03-12-02IASFPWG – Seattle, WA
Results – LOC Tests (Al. Plate)
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03-12-02IASFPWG – Seattle, WA
Results – LOC Tests (Foil Diaphragm)
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03-12-02IASFPWG – Seattle, WA
Results – LOC Tests (Foil Diaphragm)
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03-12-02IASFPWG – Seattle, WA
Test ProgramIgnition Pressure Tests
• Tests with pressure relief (i.e. foil diaphragm)Piezoresistive transducer placed behind sintered
porous metal discs.O2 concentrations 1 – 1.5% above LOC. Pressure corresponding to 0, 10, 20 & 30 kft.
• Tests without pressure relief (i.e. full vessel)Diaphragm type transducer placed behind flash
arrestor.O2 concentrations ~1.5% above LOC. Pressure corresponding to 20 & 38 kft.
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03-12-02IASFPWG – Seattle, WA
Results – Pressure Tests with Pressure Relief
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03-12-02IASFPWG – Seattle, WA
Results – Pressure Tests with Pressure Relief
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03-12-02IASFPWG – Seattle, WA
Results – Pressure Tests without Pressure Relief
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03-12-02IASFPWG – Seattle, WA
Test Program
LEL Tests• Oxygen Concentration of 21%• Altitudes of 0 and 38 kft• THC concentration varied to the point of non-
ignition (LEL)
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03-12-02IASFPWG – Seattle, WA
LEL Tests - Results
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03-12-02IASFPWG – Seattle, WA
Conclusions
LOC is a linear function of altitude, going from ~12% at 0 kft to ~16% at 38 kft.
Peak pressure rise decreases in an exponential trend as a function of altitude.
Oxygen concentration has a slight effect on ignition pressure.
Time duration to reach peak pressure increases in an exponential trend as a function of altitude.
LEL shifted slightly to the right as altitude was increased from 0 to 38 kft.
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03-12-02IASFPWG – Seattle, WA
Future Plans
Conduct ignition pressure tests without pressure relief at lower altitudes.
Conduct a thorough investigation of the LEL dependence on O2 concentration and altitude.
A paper detailing the LOC tests will be composed and published shortly.