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Ground-Based Inerting Proof of Concept Flight Test in Conjunction with the Boeing Company. March 27-28, 2001 International Aircraft Systems Fire Protection Working Group Long Beach, CA. Outline. Background Instrumentation Inerting Data Ground Testing Flight Testing. Background.
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Ground-Based Inerting Proof of Concept Flight Test in Conjunction with the Boeing Company March 27-28, 2001International Aircraft Systems FireProtection Working GroupLong Beach, CA AAR-422 Fire Safety R&D
Outline • Background • Instrumentation • Inerting Data • Ground Testing • Flight Testing AAR-422 Fire Safety R&D
Background • Focus of the testing is to determine if the Existing Fleet Vented Fuel Tanks Will Maintain NEA Benefit for a Significant Amount of Time • Boeing Offered Use a Boeing B-737NG as the Test Aircraft • Air Liquide Provided an NEA Generator with Delivery Equipment at Low Cost • Boeing to Provide Aircraft NEA Manifold, Support Personnel, Data Acquisition, and Most Instrumentation. • Tech Center to Provide Oxygen Analysis Equipment AAR-422 Fire Safety R&D
Flight Test Instrumentation • Oxygen Analysis System Provides 8 Channels of Continuous Oxygen Concentration Data • Actively Controls Sample Inlet and Outlet Pressure. • Flow Through Sensor Design • Fluid Traps, Ejector/Evacuator, Flame Suppressors for Safety • Other Instrumentation • CWT Thermocouples • Flight Data (air speed, altitude, attitude) • Fuel Load • Wind Data AAR-422 Fire Safety R&D
System Block Diagram AAR-422 Fire Safety R&D
Sample Port Location Diagram AAR-422 Fire Safety R&D
Fuel Tank Inerting • Only Inerted the CWT with Properly Operating Manifold 3 Times • Fuel Clogged Lines and Prevented Equal Distribution at Different Times • Data Looks Consistent with Lab Observations • Manifold not Balanced for Optimal Delivery Distribution • Performed Non-Dimensional Analysis and Compared with Existing Models • Volumetric Tank Exchange Measured at Approximately 1.7 Tank Volumes AAR-422 Fire Safety R&D
Flight/Ground Testing Data Reduction(Preliminary) • Involved Averaging Oxygen Concentration and Ullage Temperature at the Three Primary Areas in CWT; Center Section, Left Cheek, and Right Cheek • Calculated Average of Above Three Areas • Marked Some Critical Events • Data Plotted Every 1 Minute AAR-422 Fire Safety R&D
Raw Data Presented AAR-422 Fire Safety R&D
Raw Data Presented AAR-422 Fire Safety R&D
Flight Testing Data • Due to Profound Effect of Ground Winds and some Flight Conditions, Vent System was Modified to Prevent Cross Flow After First Flight Test • Plotted Altitude with Average Bay [O2]s to Illustrate Effect of Flight • Data Plotted Every 1 Minute AAR-422 Fire Safety R&D
Flight Testing Data Comparison • Compare Overall Fuel Tank [O2] Average to Illustrate Effect of Certain Parameters • Fuel Load Effect Less Profound Then Predicted • Cross Venting Effect Very Pronounced Over a Relatively Long Cruise • Effect of Fuel Burn Appears to be the Primary Effect on CWT [O2] AAR-422 Fire Safety R&D
Summary • GBI Was Easily Accomplished by Distributing NEA into a CWT with a Basic Distribution Manifold • GBI Can Provide Significant Protection Through Takeoff and the Beginning of Cruise to a Vented CWT (No X Venting) Even with Relatively High Fuel Loads • Care Must be Taken to Ensure Minimal X Venting due to High Ground Winds and Some Flight Maneuvers AAR-422 Fire Safety R&D
