Ug carbon carbon composite

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Ug carbon carbon composite

  1. 1. What are Carbon-Carbon Composites?• Amorphous carbon matrix composite• Carbon matrix reinforced by graphitic carbon fibers• First developed in 1958, but not intensively researched until the Space Shuttle Program
  2. 2. What are C/C Composites? C/C composites are lightweight, high- high- strength composite materials capable of withstanding temperatures over 3000°C. 3000° C/C composites use the strength and modulus of carbon fibers to reinforce a carbon matrix to resist the rigors of extreme environments.
  3. 3. Carbon-Carbon Composites• Carbon-Carbon Composites are the woven mesh of Carbon-fibers.• Carbon-Carbon Composites are used for their high strength and modulus of rigidity.• Carbon-Carbon Composites structure can be tailored to meet requirements.• Carbon-Carbon Composites are light weight material which can withstand temperatures up to 3000°C
  4. 4. Properties of C/C Composites• Excellent Thermal Shock Resistance(Over 2000oC)• Low Coefficient of Thermal Expansion• High Modulus of Elasticity ( 200 GPa )• High Thermal Conductivity ( 100 W/m*K )• Low Density ( 1830 Kg/m^3 )• High Strength• Low Coefficient of Friction ( in Fiber direction )• Thermal Resistance in non-oxidizing atmosphere• High Abrasion Resistance• High Electrical Conductivity• Non-Brittle Failure
  5. 5. Production of C/C•Three dimensional woven carbon fiber structure•Pressure impregnation with liquid•Heat treated at 2550°C•Impregnation, DENSIFICATION andgraphitization cycle repeated
  6. 6. Representative Weave Constructions
  7. 7. Fabrication of C/C Composites• Liquid Phase Infiltration• Chemical Vapor Deposition
  8. 8. PAN-based carbon fibers (the most popular type of carbon fibers).• In this method carbon fibers are produced by conversion of polyacrylonitrile (PAN) precursor through the following stages: Stretching filaments from polyacrylonitrile precursor and their thermal oxidation at 200°C.• The filaments are held in tension.Carbonization in Nitrogen atmosphere at a temperature about 1200°C for several hours.• During this stage non-carbonelements (O,N,H) volatilize resulting in enrichment of the fibers with carbon.Graphitization at about 2500°C.
  9. 9. Carbon-Carbon Composites• porous carbon-carbon composites (carbon bonded carbon fiber (CBCF)) Porosity content 70~90% ⇒high temperature insulation
  10. 10. Liquid Phase Infiltration• Preparation of C/C fiber pre-form of desired shape and structure• Liquid pre-cursor : Petroleum pitch/ Phenolic resin/ Coal tar• Pyrolysis (Chemical deposition by heat in absence of O2• It is processed at 540–1000°C under high pressure• Pyrolysis cycle is repeated 3 to 10 times for desired density• Heat Treatment converts amorphous C into crystalline C• Temperature range of treatment :1500-3000°C• Heat treatment increases Modulus of Elasticity and Strength
  11. 11. Manufacturing Process :
  12. 12. • Processing of CBCF Discontinuous fibers (mm in length) Ground recycled CBCF (rework) mixer slurry moulding binder (phenolic resin) water 50% carbon yield porous & from phenolic anisotropic vacuum Carbonization High temp heat low pressure Product drying (950℃) treatment 99.9%℃ water (fiber alignment) gaseous impurities
  13. 13. Chemical Vapor Deposition• Preparation of C/C fiber pre-form of desired shape and structure• Densification of the composite by CVD technique• Infiltration from pressurized hydrocarbon gases (Methane /Propane)at 990-1210°C• Gas is pyrolyzed from deposition on fibre surface• Process duration depends on thickness of pre-form• Heat treatment increases Modulus of Elasticity and Strength• This process gives higher strength and modulus of elasticity
  14. 14. • Dense carbon-carbon composites Discontinuous fibers Impregnation with pyrolysis Carbonization Continuous fibers  thermosetting resins 2500℃ (phenolic, furan polyimide)  pitch (polynuclear aromatic hydrocarbons) Chemical vapour Dense deposition Thick enough? product
  15. 15. Limitation of CVD• Hydrocarbon Gases Infiltrating into interfilament surfaces and cracks , sometimes these gases deposite on outer cracks and leave lot of pores• Reinfiltration and densification required• Month long process(for specific applications)
  16. 16. – Stress-strain curve process dependent: Fig 4.30 Form of fiber reinforcement: Fig 4.31
  17. 17. – Fatigue property
  18. 18. Properties of Carbon-Carbonhttp://www.hitco.com/products/corrosion/chemical/index.html
  19. 19. Uses of Carbon-Carbon Composites http://www.fibermateri• Aircraft, F-1 racing alsinc.com/frSW.htm cars and train brakes• Space shuttle nose tip and leading edges• Rocket nozzles and tips http://www.futureshuttle.com/conference/Th ermalProtectionSystem/Curry_73099.pdf http://www.fibermaterialsinc.com/frSW.htm
  20. 20. Optical MicroscopySample 3:
  21. 21. SEM ImagesSample 3:
  22. 22. Application• High Performance Braking System• Refractory Material• Hot-Pressed Dies(brake pads)• Turbo-Jet Engine Components• Heating Elements• Missile Nose-Tips• Rocket Motor Throats• Leading Edges(Space Shuttle, Agni missile)• Heat Shields• X-Ray Targets
  23. 23. Applications• NASA thermal protection systems• Nozzle throat inserts• Nosetips & leading edges• Space motor nozzles
  24. 24. Products• Variety of high temperature applications.
  25. 25. Heat Shields • Baffle Heat Shield• Flexi Heat Shield
  26. 26. Disadvantage :• Low oxidation resistance• Reacts with Oxygen at temperature above 490°C
  27. 27. Protection Method:• Ceramic coatings(Carbides/ Nitrides/oxides of Si,Zr,Ta,Al etc.)• Physical vapor deposition• Plasma spraying• Injecting with inorganic salts , borate & silicate glass.• Replacement of C/C matrix material by Si-C.(inhibitors of B, Si, Zr compounds)

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