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Simulator Status, FAA WJ Hughes Technical Center

This report discusses the impact of core heating on bypass airflow in a high bypass ratio turbofan simulator. Details include installation of inlet duct and core heating assembly, along with ongoing work on hot plates and simulant procedures.

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Simulator Status, FAA WJ Hughes Technical Center

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  1. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Simulator Status,FAA WJ Hughes Technical Center • Completed since the April 1999, Seattle meeting : • Simulator Inlet : • A 22 foot long, 22 inch diameter inlet duct has been installed to feed the blower • Transducer to measure airflow installed • hot wire anemometer in duct center line • treat inlet flow as "classic" parabolic distribution and derate velocity by 10% to determine mass flow rates • calibration curve still being worked out • Air flow heating : • core heating assembly installed • in-line duct heaters are wired • locked out, not serviceable • incorrect part installed; replacement expected within the week • On-going : • hot plates • ALL hot plate materials on-site • assembly for plate #1 completed this week • plate #2 expected by the end of October • will require testing exterior to the simulator prior to placement (control software and final assembly validation) • dry ice; looking to produce on-site • Work to date : • hot-agent simulant work • developing/learning simulator procedures and behavior

  2. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 High Bypass Ratio Turbofan Simulator - Core Heating Impact on ByPass Air Flow

  3. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 HFC-125 Distribution Comparison, Simulator Environment, 30Jul99 HFC-125 Distribution Comparison, Average Distribution Comparisons, 30Jul99

  4. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 HFC-125 - h125.99.730.05.ambient.c Bottle volume = 600 in^3 Agent weight = 5.44 lbf Agent storage pressure = 650 psig Agent storage temp = 200 °F Air flow temp = 92°F Air flow = 4.3 lbm/s HFC-125 - h125.99.730.02.hot.c Bottle volume = 600 in^3 Agent weight = 5.44 lbf Agent storage pressure = 650 psig Agent storage temp = 200 °F Air flow temp = 215°F Air flow = 3.5 lbm/s

  5. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Simulating the Distribution of Halon 1301 in an Aircraft Engine Nacelle with HFC-125 • 1994-1995. Actions sought to minimize the release of Halon 1301 unnecessarily • DoD (U.S. Navy) sponsors work through the National Institute of Standards and Technology (NIST) to develop or discover a simulant for Halon 1301 for use in nacelle discharge testing • The cumulative effort also involves Boeing, Walter Kidde Aerospace (WKA), and Shorts Brothers, PLC • NIST reviewed existing material data bases for materials having : • characteristics commensurate with the application of nacelle discharge testing • characteristics comparable to Halon 1301 during discharge in this application • Jakob number • Saturated vapor pressure • Experimental history • Atmospheric lifetime (ODP and ALT) • 3 candidates selected : • CHClF2 • SF6 • C2HF5 (HFC-125, pentafluoroethane)

  6. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Simulating the Distribution of Halon 1301 in an Aircraft Engine Nacelle with HFC-125 • Field Work : • NIST • USN, WKA on the F-18 • Boeing on the Pratt and Whitney PW 4084 on the B777 airframe • Shorts Brothers, PLC on the Allied Signal TFE731-40 on the IAI Astra SPX airframe • Conclusions : • HFC-125 most effectively simulates a Halon 1301 discharge in these applications • US military specification Mil-E-22285 edited to reflect such procedures • Additional field work, April 1998. • FAA personnel assisting USN on agent distribution within the F-18 nacelle • As courtesy to the FAA, a simulant test pair is run • Results reflect previous results • Historical review indicates overdesign far outweighs the delta found between agents in the simulation • FAA publishes technical note on the concept • Qualitative discussion regarding limitations : • the simulation appears to be sensitive to the ventilation rate of the compartment; compare cargo and nacelle environments (forced vs. natural/gravitationally driven ventilation) • recent work at the FAATC indicates agent temperature likely plays a role in the simulation effectiveness

  7. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Simulating the Distribution of Halon 1301 in an Aircraft Engine Nacelle with HFC-125 • Procedures. • Agent Storage : • Calculate/determine required weight of Halon 1301 for application • multiply desired Halon 1301 weight by 0.77 to determine the required weight of HFC-125 for the simulation • load and superpresurize with N2 as would be done for the design Halon 1301 bottle • cold soak the bottle • perform test • Halonyzer operation : • the analyzer is configured for HFC-125 • capture the simulant test with the HFC-125 calibration curve as the analyzer reference • compare results to the certification criteria of Halon 1301 • determine success or failure • NOTE : This procedure is not intended to provide a method to determine a weight of HFC-125 for fire suppression purposes. This process delineates a method to use HFC-125 in a manner which would reasonably simulate the discharge of Halon 1301 in an aircraft engine nacelle from a gaseous distribution perspective.

  8. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Simulating the Distribution of Halon 1301 in an Aircraft Engine Nacelle with HFC-125 • References. • Kaufmann, K. J., Miller, M. P., Wozniak, G., and Mitchell, M.D., 1995, "Results of Halon 1301 and HFC-125 Concentration Tests on a Large Commercial Aircraft Engine Installation," International Halon Replacement Working Group Minutes, United States Department of Transportation, Federal Aviation Administration, W.J. Hughes Technical Center, Atlantic City, NJ. • Ingerson, D. A., "Simulating the Distribution of Halon 1301 in an Aircraft Engine Nacelle with HFC-125," DOT/FAA/AR-TN99/64, United States Department of Transportation, Federal Aviation Administration, W.J. Hughes Technical Center, Atlantic City International Airport, NJ. • Military Specification MIL-E-22285(AS), Amendment 3, 1996, "Extinguishing System, Fire, Aircraft, High-Rate-Discharge Type. Installation and Test of," United States Department of Defense, Department of the Navy, Naval Air Systems Command, Washington, D.C. • Mitchell, M. D., 1994, "Methodology for Halon 1301 Simulant Testing and Concentration Equivalence Verification," Report No. R-5102, Kidde Technologies, Wilson, NC. • Mitchell, M. D., 1995, "Full Scale Halon Simulant Testing of F-18D Aircraft Using Bromotrifluoromethane and Pentafluoroethane," Report No. R-5127, Kidde Technologies, Wilson, NC. • Riordan, D., 1995, "Engine Fire Extinguisher Agent Concentration Testing," International Halon Replacement Working Group Minutes, United States Department of Transportation, Federal Aviation Administration, W.J. Hughes Technical Center, Atlantic City, NJ. • Womeldorf, C. A., Grosshandler, W. L., 1995, "Selection of a CF3Br Simulant for Use in Engine Nacelle Certification Tests," Fire Suppression System Performance of Alternative Agents in Aircraft Engine and Dry Bay Laboratory Simulations, SP890, Vol. 2, p.591-621, National Institutes of Standards and Technology, Gaithersburg, MD.

  9. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Simulating the Distribution of Halon 1301 in an Aircraft Engine Nacelle with HFC-125, Historical Example of Overdesign Lockheed C-140 Jet Star Concentration Profile at N1 = 78% (Sommers, 1970, p. 34)

  10. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Simulating the Distribution of Halon 1301 in an Aircraft Engine Nacelle with HFC-125, Historical Example of Overdesign General Dynamics F/EF-111 Agent Concentration Profile for Test 1301-8 (Chamberlain and Boris, 1988, p.57)

  11. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Halon 1301 - h1301.99.923.01.c Bottle volume = 600 in^3 Agent weight = 7.59 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 71°F Air flow = 2.3 lbm/s HFC-125 - h125.99.927.01.c Bottle volume = 600 in^3 Agent weight = 5.89 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 75°F Air flow = 2.3 lbm/s

  12. Bottle volume = 400 in^3 Agent weight = 4.58 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 73°F Air flow = 2.3 lbm/s Bottle volume = 400 in^3 Agent weight = 3.54 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 72°F Air flow = 2.3 lbm/s Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Halon 1301 - h1301.99.930.02.c HFC-125 - h125.99.930.03.c

  13. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Halon 1301 - h1301.99.a07.01.c Bottle volume = 300 in^3 Agent weight = 4.25 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 63°F Air flow = 2.3 lbm/s HFC-125 - h125.99.a07.02.c Bottle volume = 300 in^3 Agent weight = 3.28 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 64°F Air flow = 2.3 lbm/s

  14. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Halon 1301 - h1301.99.a07.04.c Bottle volume = 300 in^3 Agent weight = 4.40 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 64°F Air flow = 2.3 lbm/s HFC-125 - h125.99.a07.03.c Bottle volume = 300 in^3 Agent weight = 3.39 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 64°F Air flow = 2.3 lbm/s

  15. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 Halon 1301 - h1301.99.a06.04.c Bottle volume = 300 in^3 Agent weight = 4.00 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 70°F Air flow = 2.3 lbm/s HFC-125 - h125.99.a06.02.c Bottle volume = 300 in^3 Agent weight = 3.08 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 70°F Air flow = 2.3 lbm/s

  16. Douglas Ingerson, Federal Aviation Administration WJ Hughes Technical Center, Fire Safety Section, AAR-422 Atlantic City Int'l Airport, NJ 08405 USA International Halon Replacement Working Group Ottawa, Canada 13-14October 1999 HFC-125 - h125.99.a06.01.c Bottle volume = 300 in^3 Agent weight = 3.08 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 66°F Air flow = 2.3 lbm/s HFC-125 - h125.99.a06.03.c Bottle volume = 300 in^3 Agent weight = 3.08 lbf Agent storage pressure = 400 psig Agent storage temp = 100 °F Air flow temp = 70°F Air flow = 2.3 lbm/s

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