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Pyrolysis Behavior of a BMS 8-276 Carbon Fiber Composite

Pyrolysis Behavior of a BMS 8-276 Carbon Fiber Composite. Mark B. McKinnon Stanislav I. Stoliarov. Carbon Fiber Laminate Composite. Replacing traditional materials in many sectors due to several advantages Higher strength-to-weight ratio Improved fatigue and corrosion resistance

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Pyrolysis Behavior of a BMS 8-276 Carbon Fiber Composite

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  1. Pyrolysis Behavior of a BMS 8-276 Carbon Fiber Composite • Mark B. McKinnon • Stanislav I. Stoliarov

  2. Carbon Fiber Laminate Composite • Replacing traditional materials in many sectors due to several advantages • Higher strength-to-weight ratio • Improved fatigue and corrosion resistance • Easier and more expedient repairs • Uncertainty and Disadvantages • Has not been studied to the same extent as traditional materials • Inherently susceptible to thermal decomposition • Laminate structure yields quasi-isotropic or orthotropic thermo-physical properties • May be susceptible to smoldering after flaming fire hazard is removed • Relative composition of the Boeing 787. Over 50% is made of carbon fiber laminate.

  3. Objectives • Parameterize a comprehensive pyrolysis model for carbon fiber composite • Assess mass transport effects in a pyrolyzing composite • Investigate non-isotropic thermal conductivity • Assess effect of oxidation on pyrolysis process

  4. Carbon Fiber Laminate Composite • Produced by Toray Co. to meet Boeing Material Specification (BMS) 8-276 • Carbon Fiber/Epoxy Resin Laminate • [-45,0,45,90]2s orientation • 3.2 mm thick • Density 1520 kg m⁻³ • 60% carbon fiber by volume • Model developed by Quintiere et al. • Picture of BMS 8-276 Carbon Fiber Composite

  5. ThermaKin • Boundary Conditions • Sample Structure • Conservation of Mass of Component j • Conservation of Energy

  6. ThermaKin

  7. Simultaneous Thermal Analysis (STA) • Simultaneously conduct Thermogravimetric Analyses (TGA) and Differential Scanning Calorimetry (DSC) • TGA to measure mass of sample as a function of temperature. • DSC to measure heat flow to sample as a function of temperature. • Sample masses 3-10 mg. • Heating rates of 10 and 30 K min⁻¹ . • Continuously purged N₂ atmosphere.

  8. Thermal Degradation

  9. Thermal Degradation • Acceptance Criteria

  10. Thermal Degradation • Acceptance Criteria

  11. Carbon Fiber Composite

  12. Carbon Fiber Composite

  13. Validation • 30 K/min • 10 K/min

  14. Thermal Transport • Fully parameterized and validated thermal degradation submodel forms the foundation of the thermal transport submodel.

  15. Controlled Atmosphere Pyrolysis Apparatus (CAPA) • Augmentation to standard cone calorimeter • Sample size: 80 mm x 80 mm • Well-defined boundary conditions: • Typical heat flux range • Up to 80 kW m‾² • O₂ Concentration at Surface ∼ 2.3 vol.% (225 SLPM N₂) • Simultaneously measure sample temperatures and mass loss rates

  16. Thermal Transport • Gasification Tests • Back Surface Temperature • Mass Loss Rate (Validation)

  17. Carbon Fiber Composite • Back Surface Temperature Data • Collected at 40 kW m‾²

  18. 40 kW m‾² • 60 kW m‾² • 80 kW m‾²

  19. Mass Transport Effects • 40 kW m‾² • 60 kW m‾² • 80 kW m‾²

  20. Orthotropic Thermal Conductivity • Experiment designed to assess relationship between in-depth heat conduction and in-plane conduction. • CAPA test at 40 kW m‾² on composite to measure back surface temperature • 12.7 mm insulation covered half of composite surface • Experiment modeled using • ThermaKin2D

  21. Orthotropic Thermal Conductivity

  22. Effect of Oxidation • CAPA test on undegraded sample at 40 kW m‾²with 15% O₂ atmosphere

  23. Effect of Oxidation • CAPA test on partially degraded sample at 60 kW m‾²with 100% N₂ atmospherefor 10 minutes • followed by 20.9% O₂ atmospherefor 10 minutes

  24. Conclusions • A set of parameters were determined to describe the Toray Co. BMS 8-276 carbon fiber laminate composite. • The parameterized model predicted bench-scale MLR data to within approximately 20%. • MLR was affected by reduced mass transport due to the highly packed laminae. • In-plane thermal conductivity was determined as approximately 15 times greater than in-depth thermal conductivity. • Oxygen did not affect pyrolysis of the virgin composite. • Oxygen had a minor effect on pyrolysis of partially reacted composite.

  25. Acknowledgements • Thanks to: • My Research Group at UMD • Yan Ding (UMD) • Rich Lyon and Sean Crowley (FAA) • JENSEN HUGHES • Funded by: • FAA (Grant # 12-G-011) (Rich Lyon)

  26. Thank You

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